Gas turbine, and method and device for controlling combustion chamber of gas turbine

文档序号：1918860 发布日期：2021-12-03 浏览：21次中文

阅读说明：本技术 燃气轮机及其燃烧室的控制方法和控制装置 (Gas turbine, and method and device for controlling combustion chamber of gas turbine ) 是由郭庆波张馨桐韩冰于 2021-09-06 设计创作，主要内容包括：本发明公开了一种燃气轮机及其燃烧室的控制方法和控制装置,所述控制方法,包括以下步骤：获取燃气轮机燃烧室所处过程,并获取燃烧室的转子转速和燃烧室的热负荷；根据燃烧室的所处过程、燃烧室的转子转速和燃烧室的热负荷,对燃烧室的外围预混燃料通道的喷嘴、外围半预混燃料通道的喷嘴、中心预混燃料通道的喷嘴和中心半预混燃料通道的喷嘴进行控制。由此,该方法能够提高燃烧室燃烧的稳定性,使得火焰筒受热均匀,避免了局部热应力过高导致的燃烧室局部变形,提高了燃气轮机燃烧室的寿命。(The invention discloses a control method and a control device for a gas turbine and a combustion chamber thereof, wherein the control method comprises the following steps: acquiring the process of a combustion chamber of the gas turbine, and acquiring the rotor speed of the combustion chamber and the heat load of the combustion chamber; and controlling the nozzles of the peripheral premixed fuel channel, the nozzles of the peripheral semi-premixed fuel channel, the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel of the combustion chamber according to the process of the combustion chamber, the rotor speed of the combustion chamber and the heat load of the combustion chamber. Therefore, the method can improve the combustion stability of the combustion chamber, so that the flame tube is uniformly heated, the local deformation of the combustion chamber caused by overhigh local thermal stress is avoided, and the service life of the combustion chamber of the gas turbine is prolonged.)

1. A method of controlling a gas turbine combustor, comprising the steps of:

acquiring the process of a combustion chamber of a gas turbine, and acquiring the rotor speed of the combustion chamber and the heat load of the combustion chamber;

and controlling the nozzles of the peripheral premixed fuel channel, the nozzles of the peripheral semi-premixed fuel channel, the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel of the combustion chamber according to the process of the combustion chamber, the rotor speed of the combustion chamber and the heat load of the combustion chamber.

2. The method for controlling a gas turbine combustor according to claim 1, wherein the controlling of the nozzles of the peripheral premixed fuel passage, the nozzles of the peripheral semi-premixed fuel passage, the nozzles of the central premixed fuel passage, and the nozzles of the central semi-premixed fuel passage of the combustor according to the process of the combustor, the rotor speed of the combustor, and the heat load of the combustor includes:

if the process of the combustion chamber is an ignition starting process, controlling the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be opened and controlling the nozzles of the peripheral premixed fuel channel and the nozzles of the peripheral semi-premixed fuel channel to be closed in the process from ignition to the first rotor rotating speed so as to provide fuel for the combustion chamber through the central premixed fuel channel and the central semi-premixed fuel channel;

controlling the nozzles of the central premix fuel passage and the nozzles of the central semi-premix fuel passage to be kept open, controlling the nozzles of the peripheral semi-premix fuel passages to be kept closed, and controlling the nozzles of the peripheral semi-premix fuel passages to be opened in the process from the first rotor speed to the first heat load so as to supply fuel to the combustion chamber through the central premix fuel passage, the central semi-premix fuel passage and the peripheral semi-premix fuel passages;

controlling the nozzles of the central premix fuel passage, the nozzles of the central semi-premix fuel passage and the nozzles of the peripheral semi-premix fuel passage to be kept open during the process of increasing from the first heat load to the second heat load, and controlling the nozzles of the peripheral premix fuel passage to be opened so as to supply fuel to the combustion chamber through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage and the central semi-premix fuel passage of the combustion chamber;

controlling the nozzles of the central premix fuel passage and the nozzles of the peripheral premix fuel passages to be kept open and controlling the nozzles of the peripheral semi-premix fuel passages and the nozzles of the central semi-premix fuel passages to be closed in the process of increasing from the second heat load to the target heat load so as to supply fuel to the combustion chamber through the central premix fuel passage and the peripheral premix fuel passages; wherein the content of the first and second substances,

the first heat load is less than the second heat load, and the second heat load is less than the target heat load.

3. The method of controlling a gas turbine combustor according to claim 2, wherein the raising from the first heat load to the second heat load controls nozzles of the central premix fuel passage, nozzles of the central semi-premix fuel passage, and nozzles of the peripheral semi-premix fuel passage to remain open, and controls nozzles of the peripheral premix fuel passage to open to supply fuel to the combustor through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage, and the central semi-premix fuel passage of the combustor, and includes:

controlling the nozzles of the central premix fuel passage, the nozzles of the central semi-premix fuel passage and the nozzles of the peripheral semi-premix fuel passage to be kept open during the process of increasing from the first heat load to a third heat load, and controlling the nozzles of the peripheral premix fuel passage to be opened so as to supply fuel to the combustion chamber through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage and the central semi-premix fuel passage of the combustion chamber;

controlling the nozzles of the peripheral semi-premixed fuel passages and the nozzles of the central semi-premixed fuel passage to be gradually closed and controlling the nozzles of the central premixed fuel passage and the nozzles of the peripheral premixed fuel passage to be kept open in the process of increasing from the third heat load to the second heat load, and continuously supplying fuel to the combustion chamber through the peripheral premixed fuel passages, the peripheral semi-premixed fuel passages, the central premixed fuel passages and the central semi-premixed fuel passages of the combustion chamber; wherein the content of the first and second substances,

the first heat load is less than the third heat load, which is less than the second heat load.

4. The method for controlling a gas turbine combustor according to claim 1, wherein the controlling of the nozzles of the peripheral premixed fuel passage, the nozzles of the peripheral semi-premixed fuel passage, the nozzles of the central premixed fuel passage, and the nozzles of the central semi-premixed fuel passage of the combustor according to the process of the combustor, the rotor speed of the combustor, and the heat load of the combustor includes:

if the combustor is in the flameout shutdown process, in the process that the target heat load is reduced to a second heat load, controlling the nozzles of the central premixed fuel passage and the peripheral premixed fuel passage to be opened, and controlling the nozzles of the peripheral semi-premixed fuel passage and the nozzles of the central semi-premixed fuel passage to be closed so as to provide fuel for the combustor through the central premixed fuel passage and the peripheral premixed fuel passage;

controlling the nozzles of the central premix fuel passage and the nozzles of the peripheral semi-premix fuel passages to be kept open and controlling the nozzles of the peripheral semi-premix fuel passages and the nozzles of the central semi-premix fuel passage to be opened in the process of reducing from the second heat load to the first heat load so as to supply fuel to the combustion chamber through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage and the central semi-premix fuel passage of the combustion chamber;

controlling the nozzles of the central pre-mixing fuel passage, the nozzles of the central semi-pre-mixing fuel passage and the nozzles of the peripheral semi-pre-mixing fuel passage to be kept open and controlling the nozzles of the peripheral semi-pre-mixing fuel passage to be closed in the process from the first heat load to the first rotor speed so as to provide fuel for the combustion chamber through the central pre-mixing fuel passage, the central semi-pre-mixing fuel passage and the peripheral semi-pre-mixing fuel passage;

and controlling the nozzles of the central premixing fuel passage and the nozzles of the central semi-premixing fuel passage to be kept open, controlling the nozzles of the peripheral premixing fuel passages to be kept closed, and controlling the nozzles of the peripheral semi-premixing fuel passages to be closed in the process from the first rotor speed to flameout so as to supply fuel to the combustor through the central premixing fuel passage and the central semi-premixing fuel passage.

5. The method of controlling a gas turbine combustor according to claim 4, wherein the step of controlling the nozzles of the central premix fuel passage and the nozzles of the peripheral premix fuel passages to remain open and the nozzles of the peripheral semi-premix fuel passages and the nozzles of the central semi-premix fuel passage to open during the process of decreasing from the second heat load to the first heat load, so as to supply fuel to the combustor through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage, and the central semi-premix fuel passage of the combustor, includes:

controlling the nozzles of the peripheral semi-premixed fuel passages and the nozzles of the central semi-premixed fuel passage to be gradually opened and controlling the nozzles of the central premixed fuel passage and the nozzles of the peripheral premixed fuel passage to be kept opened in the process of reducing from the second heat load to a third heat load so as to supply fuel to the combustion chamber through the peripheral premixed fuel passage, the peripheral semi-premixed fuel passage, the central premixed fuel passage and the central semi-premixed fuel passage of the combustion chamber;

and in the process of reducing from the third heat load to the first heat load, controlling the nozzles of the peripheral semi-premixed fuel passages and the nozzles of the central semi-premixed fuel passage to be fully opened, controlling the nozzles of the central premixed fuel passage and the nozzles of the peripheral premixed fuel passage to be kept open, and continuing to supply fuel to the combustion chamber through the peripheral premixed fuel passages, the peripheral semi-premixed fuel passages, the central premixed fuel passage and the central semi-premixed fuel passage of the combustion chamber.

6. The gas turbine combustor control method of any one of claims 1 to 5, where the first rotor speed is 90% of the target speed, the first heat load is 20% of the target heat load, the second heat load is 50% of the target heat load, and the third heat load is 40% of the target heat load.

7. A control device for a gas turbine combustor, comprising:

the system comprises an acquisition module, a control module and a control module, wherein the acquisition module is used for acquiring the process of a combustion chamber of a gas turbine, and acquiring the rotor speed of the combustion chamber and the heat load of the combustion chamber;

and the control module is used for controlling the nozzles of the peripheral premixed fuel channel, the nozzles of the peripheral semi-premixed fuel channel, the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel of the combustion chamber according to the process of the combustion chamber, the rotor speed of the combustion chamber and the heat load of the combustion chamber.

8. The control device for a gas turbine combustor according to claim 7, wherein the control module comprises:

the first control unit is used for controlling the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be opened and controlling the nozzles of the peripheral premixed fuel channel and the nozzles of the peripheral semi-premixed fuel channel to be closed in the process from ignition to the first rotor rotating speed when the process of the combustion chamber is the ignition starting process, so that fuel is provided for the combustion chamber through the central premixed fuel channel and the central semi-premixed fuel channel;

a second control unit, configured to control the nozzles of the central premix fuel passage and the nozzles of the central semi-premix fuel passage to remain open, control the nozzles of the peripheral semi-premix fuel passage to remain closed, and control the nozzles of the peripheral semi-premix fuel passage to remain open during a period from the first rotor speed to a first thermal load, so as to supply fuel to the combustion chamber through the central premix fuel passage, the central semi-premix fuel passage, and the peripheral semi-premix fuel passage;

a third control unit, configured to control the nozzles of the central premix fuel passage, the nozzles of the central semi-premix fuel passage, and the nozzles of the peripheral semi-premix fuel passage to remain open during a rise from the first heat load to a second heat load, and control the nozzles of the peripheral premix fuel passage to open, so as to supply fuel to the combustor through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage, and the central semi-premix fuel passage of the combustor;

a fourth control unit, configured to control the nozzles of the central premix fuel passage and the nozzles of the peripheral premix fuel passages to remain open and control the nozzles of the peripheral semi-premix fuel passages and the nozzles of the central semi-premix fuel passage to close during a process of increasing from the second heat load to a target heat load, so as to supply fuel to the combustor through the central premix fuel passage and the peripheral premix fuel passages; wherein the content of the first and second substances,

the first heat load is less than the second heat load, and the second heat load is less than the target heat load.

9. The control device for a gas turbine combustor according to claim 7, wherein the third control unit includes:

a first sub-control unit, configured to control nozzles of the central premix fuel passage, the central semi-premix fuel passage, and the peripheral semi-premix fuel passage to remain open during a rise from the first heat load to a third heat load, and control nozzles of the peripheral premix fuel passage to open, so as to supply fuel to the combustor through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage, and the central semi-premix fuel passage of the combustor;

a second sub-control unit, configured to control gradual closing of the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel, and control the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to remain open in a process of increasing from the third heat load to the second heat load, and continue to supply fuel to the combustor through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel, and the central semi-premixed fuel channel of the combustor; wherein the content of the first and second substances,

the first heat load is less than the third heat load, which is less than the second heat load.

10. The control device for a gas turbine combustor according to claim 7, wherein the control module comprises:

a fifth control unit, configured to control the nozzles of the central premix fuel passage and the nozzles of the peripheral semi-premix fuel passages to be opened and the nozzles of the peripheral semi-premix fuel passages to be closed in a process from a target heat load to a second heat load when the combustor is in a flameout and shutdown process, so as to provide fuel for the combustor through the central premix fuel passage and the peripheral premix fuel passages;

a sixth control unit, configured to control the nozzles of the central premix fuel passage and the nozzles of the peripheral premix fuel passages to remain open and control the nozzles of the peripheral semi-premix fuel passages and the nozzles of the central semi-premix fuel passage to open during a process of decreasing from the second heat load to the first heat load, so as to supply fuel to the combustor through the peripheral premix fuel passages, the peripheral semi-premix fuel passages, the central premix fuel passages, and the central semi-premix fuel passages of the combustor;

a seventh control unit, configured to control the nozzles of the central premix fuel passage, the nozzles of the central semi-premix fuel passage, and the nozzles of the peripheral semi-premix fuel passage to remain open and control the nozzles of the peripheral premix fuel passage to close during a period from the first heat load to a first rotor speed, so as to supply fuel to the combustion chamber through the central premix fuel passage, the central semi-premix fuel passage, and the peripheral semi-premix fuel passage;

and the eighth control unit is used for controlling the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be kept open, controlling the nozzles of the peripheral semi-premixed fuel channels to be kept closed and controlling the nozzles of the peripheral semi-premixed fuel channels to be closed in the process from the first rotor speed to flameout so as to provide fuel for the combustion chamber through the central premixed fuel channel and the central semi-premixed fuel channels.

11. The control device for a gas turbine combustor according to claim 7, characterized in that the seventh control unit includes:

a third sub-control unit, configured to control the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be gradually opened and control the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to be kept open in a process of decreasing from the second heat load to a third heat load, so as to provide fuel for the combustor through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel, and the central semi-premixed fuel channel of the combustor;

and the fourth sub-control unit is used for controlling the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be fully opened, controlling the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to be kept opened, and continuously supplying fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber in the process of reducing the third heat load to the first heat load.

12. The control device for a gas turbine combustor according to any one of claims 7 to 11, where the first rotor rotation speed is 90% of the target rotation speed, the first heat load is 20% of the target heat load, the second heat load is 50% of the target heat load, and the third heat load is 40% of the target heat load.

13. A gas turbine, characterized by comprising a control device of a gas turbine combustor according to any one of claims 7 to 12.

14. A computer device, comprising:

at least one processor; and

a memory communicatively coupled to the at least one processor; wherein the content of the first and second substances,

the memory stores instructions executable by the at least one processor to enable the at least one processor to perform the method of controlling a gas turbine combustor of any one of claims 1-6.

15. A non-transitory computer-readable storage medium, on which a computer program is stored, wherein the program, when executed by a processor, implements a method of controlling a gas turbine combustor according to any one of claims 1 to 6.

Technical Field

The invention relates to the technical field of gas turbines, in particular to a control method of a gas turbine combustion chamber, a control device of the gas turbine combustion chamber and a gas turbine with the control device.

Background

The Gas Turbine (Gas Turbine) is an internal combustion type power machine which takes continuously flowing Gas as a working medium to drive an impeller to rotate at a high speed and converts the energy of fuel into useful work, and is a rotary impeller type heat engine.

At present, the combustion instability is easily generated in the operation process of a combustion chamber of a gas turbine, and when only a few nozzles work under partial load, the problems of non-uniform temperature of a flame tube, local deformation of the combustion chamber and the like are caused, so that the service life of the combustion chamber of the gas turbine is influenced.

Disclosure of Invention

The present invention is directed to solving at least one of the problems in the art to some extent.

Therefore, an object of the present invention is to provide a method for controlling a gas turbine combustor, which can improve the stability of combustion in the combustor, so that the flame tube is heated uniformly, thereby avoiding local deformation of the combustor caused by too high local thermal stress, and improving the service life of the gas turbine combustor.

A second object of the invention is to propose a control device for a gas turbine combustion chamber.

A third object of the invention is to propose a gas turbine.

A fourth object of the invention is to propose a computer device.

A fifth object of the invention is to propose a non-transitory computer-readable storage medium.

In order to achieve the above object, a first aspect of the present invention provides a method for controlling a gas turbine combustor, the method comprising the steps of: acquiring the process of a combustion chamber of a gas turbine, and acquiring the rotor speed of the combustion chamber and the heat load of the combustion chamber; and controlling the nozzles of the peripheral premixed fuel channel, the nozzles of the peripheral semi-premixed fuel channel, the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel of the combustion chamber according to the process of the combustion chamber, the rotor speed of the combustion chamber and the heat load of the combustion chamber.

According to the control method of the gas turbine combustor, the process of the gas turbine combustor is obtained, the rotor speed of the combustor and the heat load of the combustor are obtained, and then the nozzle of the peripheral premixed fuel channel, the nozzle of the peripheral semi-premixed fuel channel, the nozzle of the central premixed fuel channel and the nozzle of the central semi-premixed fuel channel of the combustor are controlled according to the process of the combustor, the rotor speed of the combustor and the heat load of the combustor. Therefore, the method can improve the combustion stability of the combustion chamber, so that the flame tube is uniformly heated, the local deformation of the combustion chamber caused by overhigh local thermal stress is avoided, and the service life of the combustion chamber of the gas turbine is prolonged.

In addition, the control method for the gas turbine combustor proposed according to the above embodiment of the present invention may further have the following additional technical features:

according to an embodiment of the present invention, the controlling of the nozzles of the peripheral premix fuel channels, the nozzles of the peripheral semi-premix fuel channels, the nozzles of the central premix fuel channels and the nozzles of the central semi-premix fuel channels of the combustor according to the process of the combustor, the rotor speed of the combustor and the thermal load of the combustor comprises: if the process of the combustion chamber is an ignition starting process, controlling the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be opened and controlling the nozzles of the peripheral premixed fuel channel and the nozzles of the peripheral semi-premixed fuel channel to be closed in the process from ignition to the first rotor rotating speed so as to provide fuel for the combustion chamber through the central premixed fuel channel and the central semi-premixed fuel channel; controlling the nozzles of the central premix fuel passage and the nozzles of the central semi-premix fuel passage to be kept open, controlling the nozzles of the peripheral semi-premix fuel passages to be kept closed, and controlling the nozzles of the peripheral semi-premix fuel passages to be opened in the process from the first rotor speed to the first heat load so as to supply fuel to the combustion chamber through the central premix fuel passage, the central semi-premix fuel passage and the peripheral semi-premix fuel passages; controlling the nozzles of the central premix fuel passage, the nozzles of the central semi-premix fuel passage and the nozzles of the peripheral semi-premix fuel passage to be kept open during the process of increasing from the first heat load to the second heat load, and controlling the nozzles of the peripheral premix fuel passage to be opened so as to supply fuel to the combustion chamber through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage and the central semi-premix fuel passage of the combustion chamber; controlling the nozzles of the central premix fuel passage and the nozzles of the peripheral premix fuel passages to be kept open and controlling the nozzles of the peripheral semi-premix fuel passages and the nozzles of the central semi-premix fuel passages to be closed in the process of increasing from the second heat load to the target heat load so as to supply fuel to the combustion chamber through the central premix fuel passage and the peripheral premix fuel passages; wherein the first heat load is less than the second heat load, which is less than the target heat load.

According to an embodiment of the present invention, in the process of increasing from the first heat load to the second heat load, controlling the nozzles of the central premix fuel passage, the nozzles of the central semi-premix fuel passage, and the nozzles of the peripheral semi-premix fuel passage to remain open, and controlling the nozzles of the peripheral premix fuel passage to open to supply fuel to the combustor through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage, and the central semi-premix fuel passage of the combustor, comprises: controlling the nozzles of the central premix fuel passage, the nozzles of the central semi-premix fuel passage and the nozzles of the peripheral semi-premix fuel passage to be kept open during the process of increasing from the first heat load to a third heat load, and controlling the nozzles of the peripheral premix fuel passage to be opened so as to supply fuel to the combustion chamber through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage and the central semi-premix fuel passage of the combustion chamber; controlling the nozzles of the peripheral semi-premixed fuel passages and the nozzles of the central semi-premixed fuel passage to be gradually closed and controlling the nozzles of the central premixed fuel passage and the nozzles of the peripheral premixed fuel passage to be kept open in the process of increasing from the third heat load to the second heat load, and continuously supplying fuel to the combustion chamber through the peripheral premixed fuel passages, the peripheral semi-premixed fuel passages, the central premixed fuel passages and the central semi-premixed fuel passages of the combustion chamber; wherein the first heat load is less than the third heat load, which is less than the second heat load.

According to an embodiment of the present invention, the controlling of the nozzles of the peripheral premix fuel channels, the nozzles of the peripheral semi-premix fuel channels, the nozzles of the central premix fuel channels and the nozzles of the central semi-premix fuel channels of the combustor according to the process of the combustor, the rotor speed of the combustor and the thermal load of the combustor comprises: if the combustor is in the flameout shutdown process, in the process that the target heat load is reduced to a second heat load, controlling the nozzles of the central premixed fuel passage and the peripheral premixed fuel passage to be opened, and controlling the nozzles of the peripheral semi-premixed fuel passage and the nozzles of the central semi-premixed fuel passage to be closed so as to provide fuel for the combustor through the central premixed fuel passage and the peripheral premixed fuel passage; controlling the nozzles of the central premix fuel passage and the nozzles of the peripheral semi-premix fuel passages to be kept open and controlling the nozzles of the peripheral semi-premix fuel passages and the nozzles of the central semi-premix fuel passage to be opened in the process of reducing from the second heat load to the first heat load so as to supply fuel to the combustion chamber through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage and the central semi-premix fuel passage of the combustion chamber; controlling the nozzles of the central pre-mixing fuel passage, the nozzles of the central semi-pre-mixing fuel passage and the nozzles of the peripheral semi-pre-mixing fuel passage to be kept open and controlling the nozzles of the peripheral semi-pre-mixing fuel passage to be closed in the process from the first heat load to the first rotor speed so as to provide fuel for the combustion chamber through the central pre-mixing fuel passage, the central semi-pre-mixing fuel passage and the peripheral semi-pre-mixing fuel passage; and controlling the nozzles of the central premixing fuel passage and the nozzles of the central semi-premixing fuel passage to be kept open, controlling the nozzles of the peripheral premixing fuel passages to be kept closed, and controlling the nozzles of the peripheral semi-premixing fuel passages to be closed in the process from the first rotor speed to flameout so as to supply fuel to the combustor through the central premixing fuel passage and the central semi-premixing fuel passage.

According to an embodiment of the present invention, in the process of decreasing from the second heat load to the first heat load, controlling the nozzles of the central premix fuel passage and the nozzles of the peripheral premix fuel passages to be kept open, and controlling the nozzles of the peripheral semi-premix fuel passages and the nozzles of the central semi-premix fuel passage to be opened, so as to supply fuel to the combustor through the peripheral premix fuel passages, the peripheral semi-premix fuel passages, the central premix fuel passages and the central semi-premix fuel passages of the combustor, includes: controlling the nozzles of the peripheral semi-premixed fuel passages and the nozzles of the central semi-premixed fuel passage to be gradually opened and controlling the nozzles of the central premixed fuel passage and the nozzles of the peripheral premixed fuel passage to be kept opened in the process of reducing from the second heat load to a third heat load so as to supply fuel to the combustion chamber through the peripheral premixed fuel passage, the peripheral semi-premixed fuel passage, the central premixed fuel passage and the central semi-premixed fuel passage of the combustion chamber; and in the process of reducing from the third heat load to the first heat load, controlling the nozzles of the peripheral semi-premixed fuel passages and the nozzles of the central semi-premixed fuel passage to be fully opened, controlling the nozzles of the central premixed fuel passage and the nozzles of the peripheral premixed fuel passage to be kept open, and continuing to supply fuel to the combustion chamber through the peripheral premixed fuel passages, the peripheral semi-premixed fuel passages, the central premixed fuel passage and the central semi-premixed fuel passage of the combustion chamber.

According to one embodiment of the invention, the first rotor speed is 90% of the target speed, the first heat load is 20% of the target heat load, the second heat load is 50% of the target heat load, and the third heat load is 40% of the target heat load.

In order to achieve the above object, a second aspect of the present invention provides a control apparatus for a gas turbine combustor, the apparatus including: the system comprises an acquisition module, a control module and a control module, wherein the acquisition module is used for acquiring the process of a combustion chamber of a gas turbine, and acquiring the rotor speed of the combustion chamber and the heat load of the combustion chamber; and the control module is used for controlling the nozzles of the peripheral premixed fuel channel, the nozzles of the peripheral semi-premixed fuel channel, the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel of the combustion chamber according to the process of the combustion chamber, the rotor speed of the combustion chamber and the heat load of the combustion chamber.

According to the control device of the gas turbine combustor, the obtaining module is used for obtaining the process of the gas turbine combustor, and obtaining the rotor speed of the combustor and the heat load of the combustor, so that the control module can control the nozzles of the peripheral premixed fuel channel, the nozzles of the peripheral semi-premixed fuel channel, the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel of the combustor according to the process of the combustor, the rotor speed of the combustor and the heat load of the combustor. Therefore, the device can improve the combustion stability of the combustion chamber, the flame tube is heated uniformly, the local deformation of the combustion chamber caused by overhigh local thermal stress is avoided, and the service life of the combustion chamber of the gas turbine is prolonged.

In addition, the control device for the gas turbine combustor according to the above embodiment of the present invention may further have the following additional features:

according to an embodiment of the invention, the control module comprises: the first control unit is used for controlling the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be opened and controlling the nozzles of the peripheral premixed fuel channel and the nozzles of the peripheral semi-premixed fuel channel to be closed in the process from ignition to the first rotor rotating speed when the process of the combustion chamber is the ignition starting process, so that fuel is provided for the combustion chamber through the central premixed fuel channel and the central semi-premixed fuel channel; a second control unit, configured to control the nozzles of the central premix fuel passage and the nozzles of the central semi-premix fuel passage to remain open, control the nozzles of the peripheral semi-premix fuel passage to remain closed, and control the nozzles of the peripheral semi-premix fuel passage to remain open during a period from the first rotor speed to a first thermal load, so as to supply fuel to the combustion chamber through the central premix fuel passage, the central semi-premix fuel passage, and the peripheral semi-premix fuel passage; a third control unit, configured to control the nozzles of the central premix fuel passage, the nozzles of the central semi-premix fuel passage, and the nozzles of the peripheral semi-premix fuel passage to remain open during a rise from the first heat load to a second heat load, and control the nozzles of the peripheral premix fuel passage to open, so as to supply fuel to the combustor through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage, and the central semi-premix fuel passage of the combustor; a fourth control unit, configured to control the nozzles of the central premix fuel passage and the nozzles of the peripheral premix fuel passages to remain open and control the nozzles of the peripheral semi-premix fuel passages and the nozzles of the central semi-premix fuel passage to close during a process of increasing from the second heat load to a target heat load, so as to supply fuel to the combustor through the central premix fuel passage and the peripheral premix fuel passages; wherein the first heat load is less than the second heat load, which is less than the target heat load.

According to an embodiment of the invention, the third control unit comprises: a first sub-control unit, configured to control nozzles of the central premix fuel passage, the central semi-premix fuel passage, and the peripheral semi-premix fuel passage to remain open during a rise from the first heat load to a third heat load, and control nozzles of the peripheral premix fuel passage to open, so as to supply fuel to the combustor through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage, and the central semi-premix fuel passage of the combustor; a second sub-control unit, configured to control gradual closing of the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel, and control the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to remain open in a process of increasing from the third heat load to the second heat load, and continue to supply fuel to the combustor through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel, and the central semi-premixed fuel channel of the combustor; wherein the first heat load is less than the third heat load, which is less than the second heat load.

According to an embodiment of the invention, the control module comprises: a fifth control unit, configured to control the nozzles of the central premix fuel passage and the nozzles of the peripheral semi-premix fuel passages to be opened and the nozzles of the peripheral semi-premix fuel passages to be closed in a process from a target heat load to a second heat load when the combustor is in a flameout and shutdown process, so as to provide fuel for the combustor through the central premix fuel passage and the peripheral premix fuel passages; a sixth control unit, configured to control the nozzles of the central premix fuel passage and the nozzles of the peripheral premix fuel passages to remain open and control the nozzles of the peripheral semi-premix fuel passages and the nozzles of the central semi-premix fuel passage to open during a process of decreasing from the second heat load to the first heat load, so as to supply fuel to the combustor through the peripheral premix fuel passages, the peripheral semi-premix fuel passages, the central premix fuel passages, and the central semi-premix fuel passages of the combustor; a seventh control unit, configured to control the nozzles of the central premix fuel passage, the nozzles of the central semi-premix fuel passage, and the nozzles of the peripheral semi-premix fuel passage to remain open and control the nozzles of the peripheral premix fuel passage to close during a period from the first heat load to a first rotor speed, so as to supply fuel to the combustion chamber through the central premix fuel passage, the central semi-premix fuel passage, and the peripheral semi-premix fuel passage; and the eighth control unit is used for controlling the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be kept open, controlling the nozzles of the peripheral semi-premixed fuel channels to be kept closed and controlling the nozzles of the peripheral semi-premixed fuel channels to be closed in the process from the first rotor speed to flameout so as to provide fuel for the combustion chamber through the central premixed fuel channel and the central semi-premixed fuel channels.

According to an embodiment of the present invention, the seventh control unit includes: a third sub-control unit, configured to control the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be gradually opened and control the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to be kept open in a process of decreasing from the second heat load to a third heat load, so as to provide fuel for the combustor through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel, and the central semi-premixed fuel channel of the combustor; and the fourth sub-control unit is used for controlling the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be fully opened, controlling the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to be kept opened, and continuously supplying fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber in the process of reducing the third heat load to the first heat load.

In order to achieve the above object, a third aspect of the present invention provides a gas turbine including the above control apparatus for a gas turbine combustor.

The gas turbine provided by the embodiment of the invention can improve the combustion stability of the combustion chamber, so that the flame tube is uniformly heated, the local deformation of the combustion chamber caused by overhigh local thermal stress is avoided, and the service life of the combustion chamber of the gas turbine is prolonged.

To achieve the above object, a fourth aspect of the present invention provides a computer device, having at least one processor; and a memory communicatively coupled to the at least one processor; wherein the memory stores instructions executable by the at least one processor to enable the at least one processor to perform the method of controlling a gas turbine combustor described above.

According to the computer equipment provided by the embodiment of the invention, by executing the control method of the gas turbine combustion chamber, the combustion stability of the combustion chamber can be improved, the flame tube is uniformly heated, the local deformation of the combustion chamber caused by overhigh local thermal stress is avoided, and the service life of the gas turbine combustion chamber is prolonged.

To achieve the above object, a fifth aspect of the present invention provides a non-transitory computer readable storage medium, on which a computer program is stored, the program, when executed by a processor, implementing the above control method for a gas turbine combustor.

The non-transitory computer readable storage medium of the embodiment of the invention can improve the combustion stability of the combustion chamber by executing the control method of the combustion chamber of the gas turbine, so that the flame tube is heated uniformly, the local deformation of the combustion chamber caused by overhigh local thermal stress is avoided, and the service life of the combustion chamber of the gas turbine is prolonged.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

The foregoing and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

FIG. 1 is a schematic illustration of fuel staging according to an embodiment of the present invention;

FIG. 2 is a schematic illustration of a fuel passage according to an embodiment of the present invention;

FIG. 3 is a schematic view of a peripheral nozzle and a central nozzle in accordance with one embodiment of the present invention;

FIG. 4 is a flow chart of a method of controlling a gas turbine combustor according to an embodiment of the present invention;

FIG. 5 is a block schematic diagram of a control arrangement for a gas turbine combustor in accordance with an embodiment of the present invention.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.

A control method of a gas turbine combustor, a control apparatus of a gas turbine combustor, a gas turbine, a computer device, and a non-transitory computer-readable storage medium according to embodiments of the present invention are described below with reference to the accompanying drawings.

Before describing the control method of the gas turbine combustor according to the embodiment of the present invention, how the nozzles of the gas turbine combustor according to the embodiment of the present invention are arranged will be described.

FIG. 1 is a schematic diagram of fuel staging according to an embodiment of the invention, FIG. 2 is a schematic diagram of a fuel passage according to an embodiment of the invention, and FIG. 3 is a schematic diagram of a peripheral nozzle and a center nozzle according to an embodiment of the invention.

Referring to fig. 1 to 3, the nozzles of the gas turbine combustor according to the embodiment of the present invention include 1 central nozzle (the nozzle denoted by reference numeral 5 in fig. 3 is a central nozzle), N peripheral nozzles (for example, 6 peripheral nozzles) in which the peripheral nozzles 6 are uniformly distributed around the central nozzle 5 (the nozzle denoted by reference numeral 6 in fig. 3 is a peripheral nozzle). The central nozzle 5 and the peripheral nozzles 6 are provided with a premix fuel channel and a semi-premix fuel channel, wherein the fuel channel marked with 1 in fig. 2 is a peripheral premix fuel channel, the fuel channel marked with 2 in fig. 2 is a peripheral semi-premix fuel channel, the fuel channel marked with 3 in fig. 2 is a central premix fuel channel, the fuel channel marked with 4 in fig. 2 is a central semi-premix fuel channel, and fuel is supplied through an end cover for 4 paths of fuel. The peripheral premixed fuel channel 1 provides peripheral premixed fuel O for the combustion chamber, the peripheral semi-premixed fuel channel 1 provides peripheral semi-premixed fuel OP for the combustion chamber, the central premixed fuel channel 3 provides central premixed fuel C for the combustion chamber, and the central semi-premixed fuel channel 4 provides central semi-premixed fuel CP for the combustion chamber.

FIG. 4 is a flow chart of a method of controlling a gas turbine combustor in accordance with an embodiment of the present invention.

As shown in fig. 4, the method for controlling a gas turbine combustor according to the embodiment of the present invention includes the steps of:

and S1, acquiring the process of the combustion chamber of the gas turbine, and acquiring the rotor speed of the combustion chamber and the heat load of the combustion chamber.

The process of the combustion chamber of the gas turbine can be one of an ignition starting process, a flameout stopping process or a process from starting to stopping running; the rotating speed of a rotor of the combustion chamber is obtained through a rotating speed sensor; the heat load is acquired by a heat load acquisition module.

And S2, controlling the nozzles of the peripheral premixed fuel channel, the nozzles of the peripheral semi-premixed fuel channel, the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel of the combustion chamber according to the process of the combustion chamber, the rotor speed of the combustion chamber and the heat load of the combustion chamber.

According to one embodiment of the invention, the control of the nozzles of the peripheral premix fuel channels, the nozzles of the peripheral semi-premix fuel channels, the nozzles of the central premix fuel channels and the nozzles of the central semi-premix fuel channels of the combustion chamber as a function of the process in which the combustion chamber is located, the rotational speed of the rotor of the combustion chamber and the thermal load of the combustion chamber comprises: if the process of the combustion chamber is an ignition starting process, controlling the nozzle of the central premixed fuel channel and the nozzle of the central semi-premixed fuel channel to be opened and controlling the nozzle of the peripheral premixed fuel channel and the nozzle of the peripheral semi-premixed fuel channel to be closed in the process from ignition to the first rotor rotating speed so as to provide fuel for the combustion chamber through the central premixed fuel channel and the central semi-premixed fuel channel; in the process from the first rotor rotating speed to the first heat load, controlling the nozzle of the central premixing fuel passage and the nozzle of the central semi-premixing fuel passage to be kept open, controlling the nozzle of the peripheral premixing fuel passage to be kept closed, and controlling the nozzle of the peripheral semi-premixing fuel passage to be opened so as to provide fuel for the combustion chamber through the central premixing fuel passage, the central semi-premixing fuel passage and the peripheral semi-premixing fuel passage; in the process of increasing from the first heat load to the second heat load, controlling the nozzles of the central premixed fuel channel, the nozzles of the central semi-premixed fuel channel and the nozzles of the peripheral semi-premixed fuel channel to be kept open, and controlling the nozzles of the peripheral premixed fuel channel to be opened so as to supply fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber; in the process of increasing from the second heat load to the target heat load, controlling the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channels to be kept open, and controlling the nozzles of the peripheral semi-premixed fuel channels and the nozzles of the central semi-premixed fuel channels to be closed so as to supply fuel to the combustion chamber through the central premixed fuel channel and the peripheral premixed fuel channels; wherein the first heat load is less than the second heat load, and the second heat load is less than the target heat load.

The first rotor speed is 90% of the target speed, the first heat load is 20% of the target heat load, and the second heat load is 50% of the target heat load.

That is, from the ignition to 90% of the target rotation speed, the two channels, namely the central premixed fuel channel and the central semi-premixed fuel channel, circulate the corresponding fuel, the other fuel channels do not circulate the fuel, 90% of the target rotation speed starts, the peripheral semi-premixed fuel channel is opened to circulate the corresponding fuel, until 20% of heat load, the peripheral premixed fuel channel is opened to circulate the corresponding fuel, and when 50% of heat load is reached, the peripheral semi-premixed fuel channel and the central semi-premixed fuel channel are closed, namely, the peripheral premixed fuel channel and the central semi-premixed fuel channel are kept to circulate the corresponding fuel after the start-up (namely, after the start-up and until the stop operation process), and the full premixed combustion can be realized. Because the semi-premixing nozzle has strong combustion stability, the semi-premixing nozzle can enhance the combustion stability in the process, and the thermal load of the flame tube is uniform, so that the local heating of the flame tube of the combustion chamber, which causes the local deformation of the combustion chamber due to the overhigh thermal stress, can be avoided, and the service life of the combustion chamber of the gas turbine is prolonged.

According to an embodiment of the present invention, in a process of increasing from a first heat load to a second heat load, controlling nozzles of the central premix fuel passage, the central semi-premix fuel passage, and the peripheral semi-premix fuel passage to remain open, and controlling nozzles of the peripheral premix fuel passage to open to supply fuel to the combustor through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage, and the central semi-premix fuel passage of the combustor, comprises: in the process of increasing from the first heat load to the third heat load, controlling the nozzles of the central premixed fuel channel, the nozzles of the central semi-premixed fuel channel and the nozzles of the peripheral semi-premixed fuel channel to be kept open, and controlling the nozzles of the peripheral premixed fuel channel to be opened so as to supply fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber; in the process of increasing from the third heat load to the second heat load, controlling the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be gradually closed, controlling the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to be kept open, and continuously providing fuel for the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber; wherein the first heat load is less than the third heat load, and the third heat load is less than the second heat load.

Wherein the third thermal load is 40% of the target thermal load.

That is, from the ignition to the 90% target rotation speed, the two channels of the central premixed fuel channel and the central semi-premixed fuel channel circulate the corresponding fuel, the other fuel channels do not circulate the fuel, the 90% target rotation speed starts, the peripheral semi-premixed fuel channel is opened to circulate the corresponding fuel, until 20% heat load, the peripheral premixed fuel channel is opened to circulate the corresponding fuel, and when 40% heat load is reached, the peripheral semi-premixed fuel channel and the central semi-premixed fuel channel are gradually closed, and when 50% heat load is reached, the peripheral semi-premixed fuel channel and the central semi-premixed fuel channel are completely closed, and the peripheral premixed fuel channel and the central premixed fuel channel are kept to circulate the corresponding fuel, so that the full premixed combustion can be realized. The semi-premixing nozzle has strong combustion stability, so that the combustion stability can be enhanced in the process, the flame stability is kept in a mode of slowly closing the peripheral semi-premixing fuel channel and the central semi-premixing fuel channel in the process that the 40% heat load is increased to 50% heat load, and the air temperature is higher in the 50% heat load, so that the stability of premixed fuel is facilitated. In addition, in the process, the thermal load of the flame tube is uniform, so that the local deformation of the combustion chamber caused by overhigh thermal stress due to the local heating of the flame tube of the combustion chamber can be avoided, and the service life of the combustion chamber of the gas turbine is prolonged.

According to one embodiment of the invention, the control of the nozzles of the peripheral premix fuel channels, the nozzles of the peripheral semi-premix fuel channels, the nozzles of the central premix fuel channels and the nozzles of the central semi-premix fuel channels of the combustion chamber as a function of the process in which the combustion chamber is located, the rotational speed of the rotor of the combustion chamber and the thermal load of the combustion chamber comprises: if the process of the combustor is a flameout shutdown process, in the process of reducing the target heat load to a second heat load, controlling the nozzles of the central premixed fuel channel and the peripheral premixed fuel channel to be opened, and controlling the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be closed so as to provide fuel for the combustor through the central premixed fuel channel and the peripheral premixed fuel channel; in the process of reducing from the second heat load to the first heat load, controlling the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channels to be kept open, and controlling the nozzles of the peripheral semi-premixed fuel channels and the nozzles of the central semi-premixed fuel channels to be opened so as to supply fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber; in the process from the first heat load to the first rotor rotating speed, controlling the nozzle of the central premixed fuel channel, the nozzle of the central semi-premixed fuel channel and the nozzle of the peripheral semi-premixed fuel channel to be kept open, and controlling the nozzle of the peripheral premixed fuel channel to be closed so as to provide fuel for the combustion chamber through the central premixed fuel channel, the central semi-premixed fuel channel and the peripheral semi-premixed fuel channel; and in the process from the first rotor speed to flameout, controlling the nozzles of the central premixed fuel passage and the nozzles of the central semi-premixed fuel passage to be kept open, controlling the nozzles of the peripheral premixed fuel passages to be kept closed, and controlling the nozzles of the peripheral semi-premixed fuel passages to be closed so as to supply fuel to the combustion chamber through the central premixed fuel passage and the central semi-premixed fuel passage.

That is, in the process of decreasing from full load to 50% of thermal load, the peripheral premixed fuel channel and the central premixed fuel channel are kept to circulate corresponding fuel, when the thermal load reaches 50%, the peripheral semi-premixed fuel channel and the central semi-premixed fuel channel are opened to circulate corresponding fuel, when the thermal load reaches 20%, the peripheral premixed fuel channel is closed, when the target rotation speed reaches 90%, the peripheral semi-premixed fuel channel is closed, so that the fuel is circulated through the central premixed fuel channel and the central semi-premixed fuel channel until flameout. Therefore, in the process, the semi-premixing nozzle can enhance the combustion stability, and the heat load of the flame tube is uniform, so that the local heating of the flame tube of the combustion chamber, the local deformation of the combustion chamber caused by the overhigh heat stress and the service life of the combustion chamber of the gas turbine can be prolonged.

According to an embodiment of the present invention, in the process of decreasing from the second heat load to the first heat load, controlling the nozzles of the central premix fuel passage and the nozzles of the peripheral premix fuel passages to remain open, and controlling the nozzles of the peripheral semi-premix fuel passages and the nozzles of the central semi-premix fuel passage to open to supply fuel to the combustor through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage, and the central semi-premix fuel passage of the combustor, comprises: in the process of reducing from the second heat load to the third heat load, controlling the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be gradually opened, and controlling the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to be kept opened so as to supply fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber; and in the process of reducing the third heat load to the first heat load, controlling the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be fully opened, controlling the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to be kept opened, and continuously supplying fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber.

That is, in the process of decreasing from full load to 50% of thermal load, the peripheral premixed fuel channel and the central premixed fuel channel are kept to circulate corresponding fuel, when the thermal load reaches 50%, the peripheral semi-premixed fuel channel and the central semi-premixed fuel channel are gradually opened to circulate corresponding fuel, when the thermal load reaches 40%, the peripheral premixed fuel channel is closed, when the thermal load reaches 20%, the peripheral semi-premixed fuel channel is closed, when the target rotation speed reaches 90%, the fuel is circulated through the central premixed fuel channel and the central semi-premixed fuel channel, until flameout, the central premixed fuel channel and the central semi-premixed fuel channel are closed. Therefore, in the process, the semi-premixing nozzle can enhance the combustion stability, and the heat load of the flame tube is uniform, so that the local heating of the flame tube of the combustion chamber, the local deformation of the combustion chamber caused by overhigh heat stress and the service life of the combustion chamber of the gas turbine can be prolonged.

In summary, according to the control method of the gas turbine combustor in the embodiment of the present invention, the process of the gas turbine combustor is obtained, the rotor speed of the combustor and the heat load of the combustor are obtained, and then the nozzles of the peripheral premixed fuel channel, the nozzles of the peripheral semi-premixed fuel channel, the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel of the combustor are controlled according to the process of the combustor, the rotor speed of the combustor and the heat load of the combustor. Therefore, the method can improve the combustion stability of the combustion chamber, so that the flame tube is uniformly heated, the local deformation of the combustion chamber caused by overhigh local thermal stress is avoided, and the service life of the combustion chamber of the gas turbine is prolonged.

FIG. 5 is a block schematic diagram of a control arrangement for a gas turbine combustor in accordance with an embodiment of the present invention.

As shown in fig. 5, a control device 500 for a gas turbine combustor according to an embodiment of the present invention includes: an acquisition module 501 and a control module 502.

The obtaining module 501 is configured to obtain a process of a combustion chamber of a gas turbine, and obtain a rotor speed of the combustion chamber and a thermal load of the combustion chamber. The control module 502 is configured to control nozzles of the peripheral premixed fuel channel, nozzles of the peripheral semi-premixed fuel channel, nozzles of the central premixed fuel channel, and nozzles of the central semi-premixed fuel channel of the combustor according to a process of the combustor, a rotor speed of the combustor, and a thermal load of the combustor.

According to one embodiment of the invention, the control module 502 includes: the device comprises a first control unit, a second control unit, a third control unit and a fourth control unit. The first control unit is used for controlling the nozzle of the central premixed fuel channel and the nozzle of the central semi-premixed fuel channel to be opened and controlling the nozzle of the peripheral premixed fuel channel and the nozzle of the peripheral semi-premixed fuel channel to be closed in the process from ignition to the first rotor rotating speed when the process of the combustion chamber is the ignition starting process, so that fuel is provided for the combustion chamber through the central premixed fuel channel and the central semi-premixed fuel channel; the second control unit is used for controlling the nozzle of the central premixed fuel channel and the nozzle of the central semi-premixed fuel channel to be kept open, controlling the nozzle of the peripheral premixed fuel channel to be kept closed and controlling the nozzle of the peripheral semi-premixed fuel channel to be opened in the process from the first rotor rotating speed to the first heat load so as to provide fuel for the combustion chamber through the central premixed fuel channel, the central semi-premixed fuel channel and the peripheral semi-premixed fuel channel; the third control unit is used for controlling the nozzles of the central premixed fuel channel, the nozzles of the central semi-premixed fuel channel and the nozzles of the peripheral semi-premixed fuel channel to be kept open and controlling the nozzles of the peripheral premixed fuel channel to be opened in the process of increasing from the first heat load to the second heat load so as to supply fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber; the fourth control unit is used for controlling the nozzle of the central premixed fuel channel and the nozzle of the peripheral premixed fuel channel to be kept open and controlling the nozzle of the peripheral semi-premixed fuel channel and the nozzle of the central semi-premixed fuel channel to be closed in the process of increasing from the second heat load to the target heat load so as to provide fuel for the combustion chamber through the central premixed fuel channel and the peripheral premixed fuel channel; wherein the first heat load is less than the second heat load, and the second heat load is less than the target heat load.

According to an embodiment of the invention, the third control unit comprises: a first sub-control unit and a second sub-control unit. The first sub-control unit is used for controlling the nozzle of the central premixed fuel channel, the nozzle of the central semi-premixed fuel channel and the nozzle of the peripheral semi-premixed fuel channel to be kept open and controlling the nozzle of the peripheral premixed fuel channel to be opened in the process of increasing from the first heat load to the third heat load so as to supply fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber; the second sub-control unit is used for controlling the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be gradually closed, controlling the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to be kept open, and continuously supplying fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber in the process of increasing from the third heat load to the second heat load; wherein the first heat load is less than the third heat load, and the third heat load is less than the second heat load.

According to one embodiment of the invention, the control module 502 includes: a fifth control unit, a sixth control unit, a seventh control unit, and an eighth control unit. The fifth control unit is used for controlling the nozzles of the central premixed fuel channel and the peripheral premixed fuel channel to be opened and controlling the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be closed so as to provide fuel for the combustion chamber through the central premixed fuel channel and the peripheral premixed fuel channel when the process of the combustion chamber is a flameout and shutdown process and the target heat load is reduced to the second heat load; a sixth control unit, configured to control the nozzle of the central premix fuel passage and the nozzle of the peripheral premix fuel passage to remain open and control the nozzle of the peripheral semi-premix fuel passage and the nozzle of the central semi-premix fuel passage to open in a process of decreasing from the second heat load to the first heat load, so as to supply fuel to the combustion chamber through the peripheral premix fuel passage, the peripheral semi-premix fuel passage, the central premix fuel passage, and the central semi-premix fuel passage of the combustion chamber; the seventh control unit is used for controlling the nozzle of the central premixed fuel channel, the nozzle of the central semi-premixed fuel channel and the nozzle of the peripheral semi-premixed fuel channel to be kept open and controlling the nozzle of the peripheral premixed fuel channel to be closed in the process from the first heat load to the first rotor rotating speed so as to provide fuel for the combustion chamber through the central premixed fuel channel, the central semi-premixed fuel channel and the peripheral semi-premixed fuel channel; and the eighth control unit is used for controlling the nozzles of the central premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be kept open, controlling the nozzles of the peripheral premixed fuel channels to be kept closed and controlling the nozzles of the peripheral semi-premixed fuel channels to be closed in the process from the first rotor rotating speed to flameout, so that fuel is provided for the combustion chamber through the central premixed fuel channel and the central semi-premixed fuel channel.

According to an embodiment of the present invention, a seventh control unit includes: a third sub-control unit and a fourth sub-control unit. The third sub-control unit is used for controlling the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be gradually opened and controlling the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to be kept opened in the process of reducing the second heat load to the third heat load so as to supply fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber; and the fourth sub-control unit is used for controlling the nozzles of the peripheral semi-premixed fuel channel and the nozzles of the central semi-premixed fuel channel to be completely opened, controlling the nozzles of the central premixed fuel channel and the nozzles of the peripheral premixed fuel channel to be kept opened, and continuously supplying fuel to the combustion chamber through the peripheral premixed fuel channel, the peripheral semi-premixed fuel channel, the central premixed fuel channel and the central semi-premixed fuel channel of the combustion chamber in the process of reducing the third heat load to the first heat load.

It should be noted that details not disclosed in the control apparatus of the gas turbine combustor according to the embodiment of the present invention refer to details disclosed in the control method of the gas turbine combustor according to the embodiment of the present invention, and detailed descriptions thereof are omitted here.

Based on the above embodiment, the present invention further provides a gas turbine including the above control device for a gas turbine combustor.

Based on the above embodiment, the present invention further provides a computer device, comprising at least one processor; and a memory communicatively coupled to the at least one processor; wherein the memory stores instructions executable by the at least one processor, the instructions being executable by the at least one processor to enable the at least one processor to perform the method of controlling a gas turbine combustor as described above.

Based on the above embodiments, the present invention also proposes a non-transitory computer-readable storage medium having stored thereon a computer program which, when executed by a processor, implements the above-described control method of a gas turbine combustor.

In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.

Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.

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Gas turbine, and method and device for controlling combustion chamber of gas turbine

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