阅读说明：本技术 燃气轮机的运行方法以及燃气轮机 (Method for operating a gas turbine and gas turbine ) 是由 武田洋树 横山乔 七泷健治 松井智之 于 2019-12-17 设计创作，主要内容包括：本发明的目的在于,有效地抑制在每次燃气轮机的启动停止时状态变化的旋转失速。一种燃气轮机,其由压缩机(1)、燃烧器(2)、涡轮(3)、发电机(4)、以及控制装置(18)构成,压缩机具有抽气阀(14)、入口导向叶片(15)、以及位于压缩机最后一级的多个车厢抽气阀(16),根据作为状态参数的压缩机金属温度,将叶片振动应力值作为指标,进行作为控制参数的抽气阀的开度、入口导向叶片的开度、以及车厢抽气阀的开放数中的至少一个的控制。(The purpose of the present invention is to effectively suppress rotating stall that changes in state each time the gas turbine is started and stopped. A gas turbine is composed of a compressor (1), a combustor (2), a turbine (3), a generator (4), and a control device (18), wherein the compressor has an extraction valve (14), an inlet guide vane (15), and a plurality of car extraction valves (16) located at the last stage of the compressor, and at least one of the opening degree of the extraction valve, the opening degree of the inlet guide vane, and the opening number of the car extraction valve as a control parameter is controlled by using a vane vibration stress value as an index based on a compressor metal temperature as a state parameter.)

1. A method for operating a gas turbine having a compressor, a combustor, a turbine, and a generator, wherein the compressor has an air extraction valve, a plurality of inlet guide vanes, and a plurality of car air extraction valves,

it is characterized in that the preparation method is characterized in that,

and controlling at least one of the opening degree of the extraction valve, the opening degree of the inlet guide vane, and the opening number of the car extraction valve as a control parameter of the gas turbine based on a state parameter of the gas turbine including at least a compressor metal temperature.

2. The method of operating a gas turbine according to claim 1,

and predicting a blade vibration stress value of a blade of a predetermined stage of the compressor based on the state parameter of the gas turbine, and controlling at least one of an opening degree of the extraction valve, an opening degree of the inlet guide blade, and an opening number of the car extraction valve so that the blade vibration stress value does not exceed a blade vibration stress allowable value.

3. Method for operating a gas turbine according to claim 1 or 2,

the compressor metal temperature refers to the compressor shell metal temperature or the compressor rotor metal temperature.

4. Method for operating a gas turbine according to claim 1 or 2,

when the state parameter exceeds a threshold value, the opening degree of the air extraction valve is increased when the control parameter is the opening degree of the air extraction valve, the opening degree of the inlet guide vane is decreased when the control parameter is the opening degree of the inlet guide vane, and the opening number of the cabin air extraction valve is increased when the control parameter is the opening number of the cabin air extraction valve.

5. The method of operating a gas turbine according to claim 3,

when the state parameter exceeds a threshold value, the opening degree of the air extraction valve is increased when the control parameter is the opening degree of the air extraction valve, the opening degree of the inlet guide vane is decreased when the control parameter is the opening degree of the inlet guide vane, and the opening number of the cabin air extraction valve is increased when the control parameter is the opening number of the cabin air extraction valve.

6. The method of operating a gas turbine according to claim 2,

at least one of the opening degree of the suction valve, the opening degree of the inlet guide vane, and the opening number of the car suction valve is controlled so that the vane vibration stress value of each of the predetermined plurality of stages of the vanes of the compressor does not exceed the allowable vane vibration stress value.

7. The method of operating a gas turbine according to claim 6,

the predetermined multistage vane is a first-stage vane and a second-stage vane, and changes in the vane oscillating stress values when the control parameter is changed tend to be opposite in the first-stage vane and the second-stage vane.

8. The method of operating a gas turbine according to claim 7,

the method of operating the gas turbine described above includes:

a first step of calculating the control parameter, in which a blade vibration stress value of the first-stage blade is lower than a blade vibration stress allowable value, based on the state parameter;

a second step of calculating the control parameter, in which a blade vibration stress value of the second-stage blade is lower than a blade vibration stress allowable value, based on the state parameter, subsequent to the first step; and

a third step of determining whether or not the blade vibration stress value of the second-stage blade is lower than a permissible blade vibration stress value when the control is performed using the control parameter calculated in the first step, and determining whether or not the blade vibration stress value of the first-stage blade is lower than a permissible blade vibration stress value when the control is performed using the control parameter calculated in the second step,

the first step comprises: a first-stage blade vibration stress calculation step of calculating a blade vibration stress value of the first-stage blade; a first-stage blade vibration stress determination step of determining whether the calculated blade vibration stress value is lower than a first-stage blade vibration stress allowable value; and a first control parameter adjustment step of, when the calculated blade vibration stress value is lower than a first-stage blade vibration stress allowable value, shifting to the second step, and when the calculated blade vibration stress value is not lower than the first-stage blade vibration stress allowable value, changing a value so as to increase the number of openings of the car extraction valve, changing a value so as to increase the opening of the extraction valve, or changing a value so as to decrease the opening of the inlet guide vane, and shifting to the first-stage blade vibration stress determination step,

the second step includes: a second-stage blade vibration stress calculation step of calculating a blade vibration stress value of the second-stage blade using the control parameter in which the blade vibration stress value of the first-stage blade is lower than the allowable blade vibration stress value in the first-stage blade vibration stress determination step; a second-stage blade vibration stress determination step of determining whether the calculated blade vibration stress value is lower than a blade vibration stress allowable value; and a second control parameter adjustment step of, when the calculated blade vibration stress value is lower than the allowable blade vibration stress value, shifting to the third step, and when the calculated blade vibration stress value is not lower than the allowable blade vibration stress value, changing the value so as to decrease the number of openings of the car suction valve, changing the value so as to decrease the opening degree of the suction valve, or changing the value so as to increase the opening degree of the inlet guide vane, and shifting to the second-stage blade vibration stress determination step,

in the third step, it is determined whether or not the control parameter has been numerically changed in the second step, and if the control parameter has been changed, the operation proceeds to the first step, and if the control parameter has not been changed, the operation is performed using the control parameter in which the blade vibration stress values of the first-stage blade and the second-stage blade are lower than the allowable blade vibration stress value in the first-stage blade vibration stress determination step and the second-stage blade vibration stress determination step.

9. The method of operating a gas turbine according to claim 1,

the number of the car extraction valves is 4, and 2 valves adjacent to each other among the 4 car extraction valves are opened by rotation at the time of stopping.

10. A method for operating a gas turbine having a compressor, a combustor, a turbine, and a generator, wherein the compressor has an air extraction valve, a plurality of inlet guide vanes, and a plurality of car air extraction valves,

it is characterized in that the preparation method is characterized in that,

when the metal temperature of the compressor exceeds a threshold value, at least any one of the following controls is performed: increasing the opening degree of the air extraction valve, decreasing the opening degree of the inlet guide vane, and increasing the number of openings of the cabin air extraction valve.

11. A gas turbine engine, characterized in that,

the gas turbine includes a compressor, a combustor, a turbine, a generator, and a control device, the compressor includes an air extraction valve, a plurality of inlet guide vanes, and a plurality of car air extraction valves,

the control device controls at least one of the opening degree of the extraction valve, the opening degree of the inlet guide vane, and the opening number of the car extraction valve as a control parameter of the gas turbine based on a state parameter of the gas turbine including at least a compressor metal temperature.

Technical Field

The present invention relates to a method for operating a gas turbine and a gas turbine, and more particularly to compressor control at the start or stop of a gas turbine.

Background

As a conventional method for preventing rotating stall of a gas turbine, for example, methods described in patent documents 1 and 2 have been proposed. Patent document 1 describes a method of starting a turbine, including the steps of: closing more than 1 air extraction valve to convert the rotating stall domain to a higher rotating speed; partially opening the inlet guide vanes prior to reaching a position outside the rotating stall domain; partially blocking the inlet guide vanes while opening more than 1 extraction valve allows the plurality of buckets to pass through the rotating stall domain.

Patent document 2 describes a method for starting a gas turbine including: an extraction flow path that supplies compressed air extracted from an extraction chamber of the compressor to the turbine as cooling air; an exhaust flow path that discharges the compressed air in the extraction flow path to a turbine exhaust system; and an exhaust valve provided in the exhaust flow path, wherein, in the gas turbine, before the start-up state of the gas turbine reaches a region where rotating stall occurs, the exhaust valve (third exhaust valve) provided in the exhaust flow path (third exhaust flow path) that communicates with the extraction chamber (third extraction chamber) on the highest pressure side of the compressor via the extraction flow path (third extraction flow path) is opened, and compressed air extracted from the third extraction chamber and flowing through the third extraction flow path is discharged to the turbine exhaust system through the third exhaust flow path. The following are described: according to this starting method, the load on the rotor blade is reduced, and the occurrence of rotating stall is suppressed, whereby the starting characteristics of the gas turbine can be improved.

Disclosure of Invention

In view of the above, an object of the present invention is to effectively suppress rotating stall that changes in state each time the gas turbine is stopped.

In order to solve the above object, the present invention adopts the structure described in the claims.

For example, in the method for operating a gas turbine according to the present invention, the gas turbine includes a compressor having an air extraction valve, a plurality of inlet guide vanes, and a plurality of car air extraction valves, a combustor, a turbine, and a generator, and at least one of the opening degree of the air extraction valve, the opening degree of the inlet guide vanes, and the opening number of the car air extraction valves is controlled as a control parameter by using a vane vibration stress value of the compressor as an index based on a compressor metal temperature as a state parameter of the gas turbine.

For example, a gas turbine according to the present invention includes a compressor having an extraction valve, a plurality of inlet guide vanes, and a plurality of car extraction valves, a combustor, a turbine, a generator, and a controller that controls at least one of an opening degree of the extraction valve, an opening degree of the inlet guide vane, and an opening number of the car extraction valve as control parameters of the gas turbine based on state parameters of the gas turbine including at least a compressor metal temperature.

Effects of the invention

According to the gas turbine control method of the present invention, during the start or stop of the gas turbine, the state parameter relating to the state of rotating stall is read from the gas turbine, and at least one of the opening degree of the extraction valve, the opening degree of the inlet guide vane, and the number of open cabin extraction valves is controlled as the control parameter based on the state parameter, and the amount of air flowing into and/or discharged from the compressor is adjusted, thereby suppressing rotating stall.

Drawings

Fig. 1 is a schematic view of a gas turbine as a first embodiment of the present invention.

Fig. 2 is a schematic diagram showing a flow in the control device of the first embodiment of the present invention.

Fig. 3 is a schematic diagram showing the relationship among the compressor metal temperature, the inlet guide vane opening degree, and the vane vibration stress in the first embodiment of the present invention.

Fig. 4 is a schematic view showing the relationship between the metal temperature and the load factor in the first embodiment of the present invention.

Fig. 5 is a schematic diagram showing a first example of S3 in the control device according to the first embodiment of the present invention.

Fig. 6 is a schematic diagram showing specific control of S3 in the control device of the first embodiment of the present invention.

Fig. 7 is a schematic diagram showing a second example (S3') of S3 in the control device of the first embodiment of the present invention.

Fig. 8 is a schematic diagram showing control of the cabin air suction valve in the second embodiment of the present invention.

Description of the reference numerals

1 … compressor, 2 … combustor, 3 … turbine, 4 … generator, 5 … rotor, 6 … compressor shell, 7 … compressor vane, 8 … compressor blade, 9 … bleed flow path, 10, 11 … exhaust flow path, 12 … exhaust chamber, 13a, 13b … branch, 14a, 14b … bleed valve, 15 … inlet guide blade, 16 … cabin bleed valve, 17 … working fluid, 18 … control device, 20 … compressor shell metal temperature sensor, 21 … compressor rotor metal temperature sensor, 22 … gas turbine operation data detection part.

Detailed Description

< example 1 >

Fig. 1 is a schematic view of a gas turbine according to embodiment 1 of the present invention.