阅读说明：本技术 一种燃烧室喷嘴 (Combustion chamber nozzle ) 是由 苏国振 荆菲 龙碧海 王彦博 苑波 于 2021-09-03 设计创作，主要内容包括：本发明涉及燃烧室技术领域,公开了一种燃烧室喷嘴,用以解决现有技术中存在的预燃级旋流器周向进气不均匀的问题。该燃烧室喷嘴包括底座、主燃级径向旋流器,主燃级径向旋流器与底座之间设有支撑部,支撑部内设置有预燃级进风通道、第一主燃级燃料通道,其中,预燃级进风通道与预燃级气流通道连通,主要起到通风的作用,第一主燃级燃料通道在底座的空腔与主燃级径向旋流器之间起到连通的作用,使得主燃级燃料可以从送料管路输送到主燃级径向旋流器中,从而与空气进行混合。(The invention relates to the technical field of combustion chambers, and discloses a combustion chamber nozzle which is used for solving the problem of uneven circumferential air intake of a pre-combustion stage swirler in the prior art. This combustion chamber nozzle includes the base, mainly fire a level radial swirler, be equipped with the supporting part between main level radial swirler and the base of firing, be provided with in the supporting part and fire the wind passageway in advance, first main level fuel passageway that fires, wherein, fire a level air inlet passageway and fire a level air current passageway intercommunication in advance, mainly play the effect of ventilation, first main level fuel passageway that fires plays the effect of intercommunication between the cavity of base and main level radial swirler that fires, make main level fuel that fires can follow the conveying line and carry main level radial swirler in, thereby mix with the air.)

1. A combustor nozzle, comprising:

the base is internally provided with a cavity, and the surface of the base is provided with a main combustion stage fuel joint which is communicated with the cavity;

the main combustion stage radial swirler is arranged in a clearance with the base along the axis direction of the main combustion stage radial swirler;

the pre-combustion stage sleeve is arranged on one side, away from the base, of the main combustion stage swirler, and an internal space of the pre-combustion stage sleeve forms a pre-combustion stage airflow channel;

the main combustion stage inner sleeve and the main combustion stage outer sleeve are sequentially sleeved outside the pre-combustion stage sleeve, a main combustion stage airflow channel is formed in a gap between the main combustion stage inner sleeve and the main combustion stage outer sleeve and is communicated with the main combustion stage radial swirler;

the supporting part is arranged between the base and the main combustion stage radial swirler; the supporting part is provided with a pre-combustion progressive air inlet channel and a first main combustion stage fuel channel, the pre-combustion progressive air inlet channel is communicated with the pre-combustion stage airflow channel, and two ends of the first main combustion stage fuel channel are respectively communicated with the cavity in the base and the main combustion stage radial swirler;

a pre-stage nozzle extending through the base and into the pre-stage airflow passage;

and the pre-burning stage swirler is arranged in the pre-burning stage airflow channel and sleeved outside the pre-burning stage nozzle.

2. The combustor nozzle of claim 1, wherein the support portion comprises a plurality of support cells, gaps between the plurality of support cells forming the pre-stage air intake passage;

at least part of the support single body is internally provided with the first main combustion stage fuel channel.

3. The combustor nozzle of claim 2, wherein the support monolith is a support plate, the support plate being radially disposed;

or, the support monomer is a support column.

4. The combustor nozzle of claim 2, wherein the support cell is a first vane having a set rotational direction and rotational angle.

5. The combustor nozzle of claim 1, wherein said support portion is an annular plate-like structure having a plurality of air inlet holes therein, said air inlet holes being radially disposed, respectively;

the plurality of air inlet holes form the pre-combustion progressive air inlet channel;

the first primary fuel stage fuel passage is disposed within the plate-like structure.

6. The combustor nozzle of claim 1, wherein said support portion is a circular plate-like structure having a plurality of air inlet holes therein, said plurality of air inlet holes having a set rotation direction and a rotation angle;

the plurality of air inlet holes form the pre-combustion progressive air inlet channel;

the first primary fuel stage fuel passage is disposed within the plate-like structure.

7. The combustor nozzle of any one of claims 1 to 6, wherein the primary stage radial swirler comprises a first sidewall, a second sidewall, and a plurality of second vanes disposed between the first sidewall and the second sidewall;

the supporting part is positioned between the base and the first side wall;

the first side wall is provided with through holes which correspond to the first main combustion stage fuel channels one to one.

8. The combustor nozzle of any one of claims 1 to 6, wherein the primary stage radial swirler comprises a first sidewall, a second sidewall, and a plurality of second vanes disposed between the first sidewall and the second sidewall;

the supporting part is positioned between the base and the first side wall;

the surface of the second blade is provided with a fuel outlet, and the inner part of the second blade is provided with a second main combustion stage fuel channel communicated with the fuel outlet;

the second primary stage fuel passage extends through a thickness of the first sidewall and communicates with the first primary stage fuel passage.

9. The combustor nozzle as in any one of claims 1 to 6, further comprising a nozzle rod fixedly connected to the base, wherein a main combustion stage feed passage and a pre-combustion stage feed passage are arranged in the nozzle rod along the axis direction of the nozzle rod;

the main combustion stage feed channel is communicated with the main combustion stage fuel joint;

the pre-burning stage feeding channel is communicated with the pre-burning stage nozzle.

10. The combustor nozzle of claim 9, wherein the angle between the axis of the nozzle stem and the axis of the head is obtuse.

Technical Field

The invention relates to the technical field of combustion chambers, in particular to a combustion chamber nozzle.

Background

At present, the structure of the commonly adopted central staged lean-burn premixing nozzle is shown in fig. 1, and includes a main combustion stage 01 and a pre-combustion stage 02, the main combustion stage 01 and the pre-combustion stage 02 are coaxially arranged and are located at the periphery of the pre-combustion stage 02, the main combustion stage 01 includes a main combustion stage inner wall 011, a main combustion stage outer wall 012 and a main combustion stage radial swirler 013, the pre-combustion stage 02 includes a pre-combustion stage wall 021 and a pre-combustion stage swirler 022, and the pre-combustion stage swirler 022 is a radial swirler; the main burning stage 01 and the pre-burning stage 02 are respectively communicated with the nozzle rod 03, two branches are arranged at the end of the nozzle rod 03 to form a main burning stage nozzle 031 and a pre-burning stage nozzle 032, the main burning stage nozzle 031 is used for providing fuel for the main burning stage, and the pre-burning stage nozzle 032 is used for injecting fuel to the pre-burning stage.

With continued reference to fig. 1, the main part of the main combustion stage nozzle 031 and the pre-combustion stage nozzle 032 is bent relative to the nozzle rod 03, and a part of the air inlet of the pre-combustion stage swirler 022 is located between the main combustion stage nozzle 031 and the pre-combustion stage nozzle 032, then the pre-combustion stage nozzle 032 which is bent and arranged will form a barrier on the air inlet channel of this part of the air inlet, thereby resulting in non-uniformity of circumferential air inlet of the pre-combustion stage swirler 022, and also reducing the swirl strength of the air flow passing through the pre-combustion stage swirler 022, thereby causing adverse effects on combustion of the pre-combustion stage fuel and stability of the flame.

Disclosure of Invention

The invention provides a combustion chamber nozzle which is used for solving the problem of uneven circumferential air inlet of a pre-combustion stage swirler in the prior art.

An embodiment of the present invention provides a combustor nozzle, including:

the base is internally provided with a cavity, and the surface of the base is provided with a main combustion stage fuel joint which is communicated with the cavity;

the main combustion stage radial swirler is arranged in a clearance with the base along the axis direction of the main combustion stage radial swirler;

the pre-combustion stage sleeve is arranged on one side, away from the base, of the main combustion stage swirler, and an internal space of the pre-combustion stage sleeve forms a pre-combustion stage airflow channel;

the main combustion stage inner sleeve and the main combustion stage outer sleeve are sequentially sleeved outside the pre-combustion stage sleeve, a main combustion stage airflow channel is formed in a gap between the main combustion stage inner sleeve and the main combustion stage outer sleeve and is communicated with the main combustion stage radial swirler;

the supporting part is arranged between the base and the main combustion stage radial swirler; the supporting part is provided with a pre-combustion progressive air inlet channel and a first main combustion stage fuel channel, the pre-combustion progressive air inlet channel is communicated with the pre-combustion stage airflow channel, and two ends of the first main combustion stage fuel channel are respectively communicated with the cavity in the base and the main combustion stage radial swirler;

a pre-stage nozzle passing through the base and extending into the pre-stage airflow passage.

And the pre-burning stage swirler is arranged in the pre-burning stage airflow channel and sleeved outside the pre-burning stage nozzle.

In the above embodiment, the external air is divided into two parts when entering the nozzle, and one part is fed into the flame tube through the main combustion stage radial swirler and the main combustion stage airflow channel; the other part of the air enters the flame tube through the pre-combustion stage air inlet channel, the pre-combustion stage airflow channel and the pre-combustion stage swirler in the supporting part, and the pre-combustion stage air inlet channel is arranged between the base and the main combustion stage radial swirler, so that the air can uniformly enter the pre-combustion stage airflow channel from the pre-combustion stage air inlet channel along the circumferential direction and forms rotational flow under the action of the pre-combustion stage swirler, and the circulation of the air at the air inlet cannot be influenced by the feeding pipeline.

Optionally, the support part comprises a plurality of support single bodies, and gaps among the support single bodies form the pre-combustion stage air inlet channel;

at least part of the support single body is internally provided with the first main combustion stage fuel channel.

In the above alternative embodiment, the support single bodies play a role in supporting and connecting between the base and the main combustion stage radial swirler on one hand, and on the other hand, a gap between two adjacent support single bodies forms a pre-combustion stage air inlet channel to provide air for combustion of the pre-combustion stage fuel; furthermore, the support elements also serve as a carrier for the first main stage fuel passages, which can deliver the main stage fuel into the main stage radial swirler so that the main stage fuel is premixed with air.

Optionally, the support units are support plates, and the support plates are arranged in the radial direction;

or, the support monomer is a support column.

In the above alternative embodiment, the gap between the support units functions as ventilation, so that after external air enters the pre-combustion stage airflow channel through the gap, a rotational flow is formed under the action of the pre-combustion stage swirler, so as to provide air for the pre-combustion stage fuel, and a rotational flow is formed in the flame tube, so as to stabilize the flame.

Optionally, the supporting unit is a first blade, and the first blade has a set rotation direction and a set rotation angle.

In the above alternative embodiment, since the first vane has a set rotation direction and a set rotation angle, the external air may form a rotational flow after passing through the first vane, the first vane functions as a swirler, and the first vane and the pre-combustion stage swirler form a two-stage series structure.

Optionally, the supporting portion is a circular plate-shaped structure, a plurality of air inlet holes are formed in the plate-shaped structure, and the air inlet holes are respectively arranged along the radial direction;

the plurality of air inlet holes form the pre-combustion progressive air inlet channel;

the first primary fuel stage fuel passage is disposed within the plate-like structure.

In the above alternative embodiment, the air inlet holes function as ventilation to provide air for the combustion of the pre-combustion stage fuel.

Optionally, the support portion is a circular plate-shaped structure, a plurality of air inlet holes are formed in the plate-shaped structure, and the air inlet holes have a set rotation direction and a set rotation angle;

the plurality of air inlet holes form the pre-combustion progressive air inlet channel;

the first primary fuel stage fuel passage is disposed within the plate-like structure.

In the above alternative embodiment, since the air inlet holes have a set rotation direction and a set rotation angle, external air can form a rotational flow after passing through the air inlet holes, the air inlet holes function as a cyclone, and the air inlet holes and the pre-combustion stage cyclone form a two-stage series structure.

Optionally, the primary combustion stage radial swirler comprises a first sidewall, a second sidewall, and a plurality of second vanes disposed between the first sidewall and the second sidewall;

the supporting part is positioned between the base and the first side wall;

the first side wall is provided with through holes which correspond to the first main combustion stage fuel channels one to one.

In the above optional embodiment, the main combustion stage fuel firstly enters the cavity in the base through the feeding pipeline, then enters the first main combustion stage fuel channel arranged in the supporting part through the cavity, and finally is ejected through the through hole arranged on the first side wall of the main combustion stage swirler, and after being ejected, the main combustion stage fuel is primarily mixed with the air flowing through the surface of the first side wall, and further mixed in the main combustion stage airflow channel, and then enters the flame tube.

Optionally, the primary combustion stage radial swirler comprises a first sidewall, a second sidewall, and a plurality of second vanes disposed between the first sidewall and the second sidewall;

the supporting part is positioned between the base and the first side wall;

the surface of the second blade is provided with a fuel outlet, and the inner part of the second blade is provided with a second main combustion stage fuel channel communicated with the fuel outlet;

the second primary stage fuel passage extends through a thickness of the first sidewall and communicates with the first primary stage fuel passage.

In the above optional embodiment, the main combustion stage fuel sequentially passes through the feeding pipeline, the cavity in the base, the first main combustion stage fuel channel in the supporting portion and the second main combustion stage fuel channel in the second vane, and is finally ejected from the fuel outlet.

Optionally, the fuel injection device further comprises a nozzle rod, the nozzle rod is fixedly connected with the base, and a main combustion stage feeding channel and a pre-combustion stage feeding channel are arranged in the nozzle rod along the axis direction of the nozzle rod;

the main combustion stage feed channel is communicated with the main combustion stage fuel joint;

the pre-burning stage feeding channel is communicated with the pre-burning stage nozzle.

In the above optional embodiment, the main combustion stage feeding channel and the pre-combustion stage feeding channel are arranged along the axial direction of the nozzle rod and can be directly connected with the main combustion stage fuel joint and the pre-combustion stage nozzle on the base.

Optionally, the included angle formed between the axis of the nozzle rod and the axis of the head is an obtuse angle.

In the alternative embodiment described above, the extension of the nozzle bar may be close to the outer wall of the combustion chamber, saving space outside the combustion chamber.

Drawings

FIG. 1 is a half-sectional view of a combustor nozzle as used in the prior art;

FIG. 2 is a schematic structural view of a combustor nozzle provided in accordance with an embodiment of the present invention;

FIG. 3 is a schematic view of the combustor nozzle shown in FIG. 2 from another perspective;

FIG. 4 is a half-sectional view of the combustor nozzle shown in FIG. 2;

FIG. 5 is a cross-sectional view 1/4 of the combustor nozzle tip shown in FIG. 2;

FIG. 6 is a schematic structural view of a support portion of the combustor nozzle shown in FIG. 2;

FIG. 7 is a schematic structural diagram of another supporting portion according to an embodiment of the present invention;

FIG. 8 is a schematic structural diagram of another supporting portion according to an embodiment of the present invention;

FIG. 9 is a schematic structural diagram of another supporting portion according to an embodiment of the present invention;

FIG. 10 is a schematic structural diagram of another supporting portion according to an embodiment of the present invention;

FIG. 11 is a schematic illustration of the relative positions of the first and second blades illustrated in FIG. 2;

fig. 12 is a schematic diagram of relative positions of a first blade and a second blade according to another embodiment of the present invention.

Reference numerals:

01-main burning stage 011-main burning stage inner wall

012-main combustion stage outer wall 013-main combustion stage radial swirler

02-precombustion stage 021-precombustion stage wall 022-precombustion stage swirler

03-nozzle rod 031-main combustion stage nozzle 032-precombustion stage nozzle

10-base 101-main combustion stage fuel joint

20-main combustion stage radial swirler 201-main combustion stage air inlet channel

21-first sidewall 211-through hole 22-second sidewall

23-second vane 231-fuel outlet 232-second main combustion stage fuel channel

30-support part 301-precombustion progressive air inlet channel

302-first main combustion stage fuel channel 303-air inlet hole

31-support plate 32-support column 33-first blade

40-precombustion stage sleeve 401-precombustion stage airflow passage

50 a-inner primary fuel stage sleeve 50 b-outer primary fuel stage sleeve 501-primary fuel stage airflow passage

60-stage section cooling channel 70-precombustion stage nozzle 80-precombustion stage swirler

90-nozzle rod 901-main combustion stage feeding channel 902-precombustion stage feeding channel

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings, and it is apparent that the described embodiments are only a part of the embodiments of the present invention, not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Before describing embodiments of the present invention, several concepts involved in the specific embodiments will be explained first:

axial swirler: the blades form a certain rotation angle with the axial direction, so that the entering air rotates, and the rotating air is favorable for mixing fuel and air and forming a backflow zone to stabilize flame;

radial swirler: the vanes are at a certain rotation angle with the tangential/radial direction, so that the entering air is rotated, and the rotating air is favorable for mixing fuel and air and forming a backflow zone to stabilize flame;

the invention provides a combustion chamber nozzle which is used for solving the problem of uneven circumferential air inlet of a pre-combustion stage swirler in the prior art.

Referring collectively to fig. 2-5, the combustor nozzle includes:

the base 10 is internally provided with a cavity, the surface of the base is provided with a main combustion stage fuel joint 101, and the main combustion stage fuel joint 101 is communicated with the cavity;

the main combustion stage radial swirler 20 is arranged in a clearance with the base 10 along the axis direction of the main combustion stage radial swirler;

the pre-combustion stage sleeve 40 is arranged on one side of the main combustion stage radial swirler 20, which is far away from the base 10, and the inner space of the pre-combustion stage sleeve 40 forms a pre-combustion stage airflow channel 401;

the main combustion stage inner sleeve 50a and the main combustion stage outer sleeve 50b are sequentially sleeved outside the pre-combustion stage sleeve 40, a main combustion stage airflow channel 501 is formed in a gap between the main combustion stage inner sleeve 50a and the main combustion stage outer sleeve 50b, and the main combustion stage airflow channel 501 is communicated with the main combustion stage radial swirler 20;

a support part 30 provided between the base 10 and the main combustion stage radial swirler 20; the base is provided with a pre-combustion stage air inlet channel 301 and a first main combustion stage fuel channel 302, the pre-combustion stage air inlet channel 301 is communicated with a pre-combustion stage airflow channel 401, and two ends of the first main combustion stage fuel channel 302 are respectively communicated with a cavity in the base 10 and the main combustion stage radial swirler 20;

and the pre-combustion stage nozzle 70 penetrates through the base 10 and extends into the pre-combustion stage airflow passage 401.

The pre-combustion stage swirler 80 is arranged in the pre-combustion stage airflow channel 401 and sleeved outside the pre-combustion stage nozzle 70.

In the nozzle, the surface of the base 10 is provided with a main combustion stage fuel joint 101, the main combustion stage fuel joint 101 is used for communicating with a pipeline for conveying main combustion stage fuel, and the main combustion stage fuel joint 101 is communicated with a cavity inside the base 10.

As shown in fig. 4 and 5, the main stage radial swirler 20 is disposed coaxially with the base 10, and the main stage radial swirler 20 is located on a side of the base 10 facing away from the main stage fuel joint 101. A gap is formed between the main combustion stage radial swirler 20 and the base 10 along the axis direction of the main combustion stage radial swirler 20, and the support portion 30 is located in the gap, on one hand, the support portion 3030 can play a role in supporting and connecting between the main combustion stage radial swirler 20 and the base 10, and on the other hand, as the pre-combustion stage air inlet passage 301 is arranged in the support portion 30, external air can enter the flame tube through the pre-combustion stage air inlet passage 301, the pre-combustion stage air flow passage 401 and the pre-combustion stage swirler 80 to provide air for combustion of pre-combustion stage fuel; furthermore, a first main stage fuel passage 301 is provided within support portion 30, and first main stage fuel passage 301 may deliver main stage fuel to main stage radial swirler 20 such that the main stage fuel is premixed with air.

With continued reference to fig. 4 and 5, the nozzle includes, in addition to the base 10, the main combustion stage radial swirler 20, and the support portion 3030, a pre-combustion stage sleeve 40, a main combustion stage inner sleeve 50a, and a main combustion stage outer sleeve 50b, which are sequentially disposed from inside to outside, and all of the three are disposed coaxially with the main combustion stage radial swirler 20, wherein an inner space of the pre-combustion stage sleeve 40 forms a pre-combustion stage airflow passage 401, the pre-combustion stage airflow passage 401 communicates with the pre-combustion stage airflow passage 301, a gap between the main combustion stage inner sleeve 50a and the main combustion stage outer sleeve 50b forms a main combustion stage airflow passage 501, the main combustion stage airflow passage 501 communicates with the main combustion stage radial swirler 20, and air and main combustion stage fuel can be premixed in the main combustion stage airflow passage 501, thereby improving the combustion efficiency of fuel.

Further, as shown in fig. 4, a gap between the pre-combustion stage sleeve 40 and the main combustion stage inner sleeve 50a forms a stage section cooling channel 60, a wall surface of the stage section cooling channel 60 is provided with stage section cooling holes, and after a part of air flow enters the stage section cooling channel 60, air film cooling can be formed on the surface of the stage section cooling holes, so that the wall surface is isolated from high-temperature gas, and a part of high-temperature gas is taken away, thereby achieving a good cooling protection effect on the wall surface.

It can be seen that the external air is divided into two parts when entering the nozzle, one part of the air enters the main combustion stage radial swirler 20 and forms a main combustion stage air rotational flow, and the main combustion stage air rotational flow and the main combustion stage fuel enter the flame tube after being premixed in the main combustion stage airflow channel 501; another part of the air enters the pre-combustion stage air inlet channel 301 in the supporting part 30, the majority of the air enters the flame tube through the pre-combustion stage airflow channel 401, and a small amount of air enters the stage section cooling channel 60 and forms film cooling on the surface of the stage section cooling holes, so that the influence of high temperature on the tube wall is reduced.

In the nozzle, because the pre-combustion stage air inlet channel 301 is positioned between the base 10 and the main combustion stage radial swirler 20, the pre-combustion stage air inlet channel 301 is not shielded by a feeding pipeline, air can uniformly flow into the pre-combustion stage air inlet channel 301 from the periphery, and a stable rotational flow is formed under the action of the pre-combustion stage swirler 80, so that the part of air flow can ensure the combustion of pre-combustion stage fuel on one hand, and on the other hand, a backflow area can be formed in a flame tube to stabilize flame.

In the nozzle, a pre-combustion stage air inlet channel 301 and a first main combustion stage fuel channel 302 are arranged in the support part 30, wherein the pre-combustion stage air inlet channel 301 mainly plays a role in ventilation, and the first main combustion stage fuel channel 302 plays a role in communication between the cavity of the base 10 and the main combustion stage radial swirler 20, so that the main combustion stage fuel can be conveyed to the main combustion stage radial swirler 20 from a feeding pipeline so as to be mixed with air.

In particular, the support 30 has various configurations, and several specific examples will be described.

As shown in fig. 6, 7 and 8, the supporting portion 30 includes a plurality of supporting single bodies, and gaps between the supporting single bodies form a precombustion stage air intake passage 301;

at least a portion of the support monolith has a first primary fuel stage fuel passage 302 disposed therein.

Specifically, the support units serve to support and connect between the base 10 and the main combustion stage radial swirler 20, and a gap between two adjacent support units forms a pre-combustion stage air inlet channel 301, and external air enters the pre-combustion stage air flow channel 401 through the pre-combustion stage air inlet channel 301, and forms a swirling flow under the action of the pre-combustion stage swirler 80, so as to provide air for combustion of the pre-combustion stage fuel, and form a backflow zone in the flame tube, so as to stabilize flame.

In addition, the supporting single bodies are also used as carriers of the first main combustion stage fuel passage 302, specifically, the first main combustion stage fuel passage 302 may be provided in a part of the supporting single bodies, or a first main combustion stage fuel passage 302 may be provided in each supporting single body, the first main combustion stage fuel passage 302 is respectively communicated with a cavity in the base 10 and the main combustion stage radial swirler 20, the main combustion stage fuel sequentially passes through the feeding pipeline, the cavity in the base 10 and the first main combustion stage fuel passage 302 and then enters the main combustion stage radial swirler 20, the main combustion stage fuel is premixed in a flowing process along with air swirling flow, and finally enters the flame tube for fuel.

For example, as shown in fig. 7, the support plates 31 are support plates 31, the support plates 31 are respectively arranged in a radial direction, a gap between the support plates 31 forms a pre-combustion stage air intake passage 301, and a first main combustion stage fuel passage 302 is arranged in at least a part of the support plates 31.

In practice, these support plates 31 are disposed between the main combustion stage radial swirler 20 and the base 10, and are disposed in the radial direction, respectively, so that the external air can pass through the gap between two adjacent support plates 31 and enter the precombustion stage airflow channel 401, thereby providing air for the combustion of the precombustion stage fuel.

Specifically, the plurality of support plates 31 are uniformly distributed along the circumference, the number of the support plates 31 is not limited, and the number of the support plates 31 shown in fig. 7 is only an example and is not intended to be limiting.

For another example, as shown in fig. 8, the supporting single body is a supporting column 32, gaps between the supporting columns 32 form a pre-combustion stage air intake channel 301, and at least a part of the supporting columns 32 is provided with a first main-combustion stage fuel channel 302.

Specifically, the plurality of support pillars 32 are uniformly distributed along the circumference, the number of the support pillars 32 is not limited, and the number of the support pillars 32 shown in fig. 8 is only an example and is not intended to be limiting.

In the above two embodiments, the pre-combustion stage air intake channel 301 formed by the gap between the support plate 31 and the support column 32 only plays a role of ventilation for providing air for the combustion of the pre-combustion stage fuel, and after the external air enters the pre-combustion stage air flow channel 401 from the pre-combustion stage air intake channel 301, a swirling flow is formed under the action of the pre-combustion stage swirler 80, so that a backflow zone is formed in the flame tube to stabilize the flame.

In addition, the structure of the support single body is designed, so that air can form rotational flow after passing through the pre-combustion stage air inlet channel 301, and the function of a cyclone is achieved, so that the pre-combustion stage air inlet channel 301 and the pre-combustion stage cyclone 80 arranged outside the pre-combustion stage nozzle 70 form a series structure, and the strength of the rotational flow can be adjusted by selecting proper structural parameters.

For example, the supporting single body is a first vane 33, the first vane 33 has a set rotation direction and a set rotation angle, and a gap between two adjacent first vanes 33 forms a precombustion stage air intake passage 301;

a first main stage fuel passage 302 is provided in at least a portion of the first vane 33.

Specifically, the first blade 33 may have a flat plate structure or a streamline structure.

As shown in fig. 6, in a plan view of the support portion 30, the first vane 33 has a flat plate structure, the first vane 33 has a set rotation direction and a set rotation angle, and the external air may form a rotational flow after passing through the first vane 33, so that the first vane 33 may function as a cyclone.

In the nozzle, the first blades 33 and the pre-combustion stage swirler 80 form a two-stage series structure, and in design, parameters of the two stages of swirlers are matched, so that the swirling flow formed after air passes through the air inlet holes 303 can be further strengthened under the action of the pre-combustion stage swirler 80, or the swirling flow strength can be weakened according to requirements.

Specifically, the first main stage fuel passage 302 may be provided in a part of the first vanes 33, or the first main stage fuel passage 302 may be provided in each of the first vanes 33.

It should be noted that the supporting unit may also adopt other structural forms besides the structural form of the supporting plate 31, the supporting column 32 and the first blade 33, which are not described one by one here.

In the support 30, in addition to providing the support 30 as a plurality of support units, forming the pre-stage air inlet passage 301 by using the gap between the support units, and providing the first main stage fuel passage 302 in the support unit to communicate the cavity in the base 10 and the main stage radial swirler 20, the support 30 may be provided as a circular plate-shaped structure in which the pre-stage air inlet passage 301 and the first main stage fuel passage 302 are formed by providing through holes.

For example, the support portion 30 is a circular plate-shaped structure, a plurality of air inlet holes 303 are formed in the plate-shaped structure, and the air inlet holes 303 are respectively arranged along the radial direction;

the plurality of air inlet holes 303 form a pre-combustion progressive air inlet channel 301;

a first main stage fuel passage 302 is provided in the plate-like structure.

Specifically, as shown in fig. 9, which is a top view of the supporting portion 30, wherein the air inlet holes 303 are radially disposed and penetrate through the inner annular surface and the outer annular surface of the supporting portion 30, external air can enter the precombustion stage airflow passage 401 along the air inlet holes 303 to provide air for the fuel of the precombustion stage fuel; first main stage fuel passage 302 is axially disposed and extends through the bottom and top surfaces of support portion 30, and first main stage fuel passage 302 communicates with the cavity in base 10 and main stage radial swirler 20, respectively, to deliver main stage fuel to main stage radial swirler 20 such that the main stage fuel is premixed with air.

Further, the air inlet holes 303 do not intersect the first main stage fuel passage 302.

The air inlet holes 303 may be uniformly distributed along the circumference, the first main stage fuel passages 302 may also be uniformly distributed along the circumference, the number of the air inlet holes 303 and the first main stage fuel passages 302 is not limited, and fig. 9 is only used as an example and is not intended to be particularly limited.

In the support portion 30, the air inlet holes 303 only play a role of ventilation and are used for providing air for the combustion of the pre-combustion stage fuel, and after external air enters the pre-combustion stage airflow channel 401 from the pre-combustion stage air inlet channel 301, a rotational flow is formed under the action of the pre-combustion stage swirler 80, so that a backflow zone is formed in the flame tube to stabilize flame.

Further, by setting the air inlet holes 303 to have a set rotation direction and a set rotation angle, the air can form a rotational flow after passing through the pre-combustion stage air inlet channel 301, and thus, the pre-combustion stage air inlet channel 301 and the pre-combustion stage swirler 80 arranged outside the pre-combustion stage nozzle 70 form a series structure, and by selecting appropriate structural parameters, the two stages of swirlers can adjust the strength of the rotational flow.

Specifically, the support portion 30 is a circular plate-shaped structure, a plurality of air inlet holes 303 are formed in the plate-shaped structure, and the plurality of air inlet holes 303 have a set rotation direction and a set rotation angle;

the plurality of air inlet holes 303 form a pre-combustion progressive air inlet channel 301;

the first main stage fuel passages 302 are provided in a plate-like structure.

As shown in fig. 10, the top view of the support 30 shows, the air inlet holes 303 have a set direction of rotation and a set angle of rotation, and the external air can form a rotational flow after passing through the air inlet holes 303, so that the air inlet holes 303 can function as a cyclone.

In the nozzle, the pre-combustion stage swirler 80 is arranged outside the pre-combustion stage nozzle 70, so that the air inlet hole 303 and the pre-combustion stage swirler 80 form a two-stage series structure, and in design, parameters of the two-stage swirler are matched, so that the strength of the swirl can be further enhanced under the action of the pre-combustion stage swirler 80 by the swirl formed after the air passes through the air inlet hole 303, or the strength of the swirl can be weakened according to requirements.

With continued reference to FIG. 10, first main stage fuel passage 302 is axially disposed and extends through the bottom and top surfaces of support portion 30, first main stage fuel passage 302 communicates with the cavity in base 10 and main stage radial swirler 20, respectively, and first main stage fuel may be delivered to main stage radial swirler 20 such that the main stage fuel is premixed with air.

When the fuel inlet is specifically arranged, the air inlet holes 303 do not intersect with the first main combustion stage fuel channel 302.

The number of the air inlet holes 303 and the number of the first main stage fuel passages 302 are not limited, and fig. 10 is only an example and is not intended to be particularly limited.

In the nozzle, as shown in fig. 4 and 5, the main stage radial swirler 20 includes a first side wall 21, a second side wall 22, and a plurality of second vanes 23 disposed between the first side wall 21 and the second side wall 22, a gap between two adjacent second vanes 23 forms a main stage air inlet passage 201, and the main stage air inlet passage 201 communicates with a main stage air flow passage 501.

Regarding the first sidewall 21 and the second sidewall 22, the first sidewall 21 refers to one disposed close to the base 10, the second sidewall 22 refers to one disposed far from the base 10, the supporting portion 30 is disposed between the base 10 and the first sidewall 21, and the supporting portion 30 may adopt any one of the structural forms of the above-mentioned embodiments.

First main stage fuel passage 302 is disposed in support portion 30, and various ways may be used to communicate first main stage fuel passage 302 with main stage radial swirler 20, and two ways are specifically described as examples:

in a first mode

The first sidewall 21 of the primary combustion stage radial swirler 20 is provided with through holes 211 corresponding to the first primary combustion stage fuel passages 302 one to one.

In the main combustion stage radial swirler 20, the first side wall 21 is provided with through holes 211 corresponding to the first main combustion stage fuel passages 302 one by one, so that the main combustion stage fuel firstly enters a cavity in the base 10 through a feeding pipeline, then enters the first main combustion stage fuel passages 302 in the supporting portion 30 through the cavity, and finally is ejected through the through holes 211 arranged on the first side wall 21 of the main combustion stage radial swirler 20, and the ejected main combustion stage fuel is primarily mixed with air flowing through the surface of the first side wall 21, and further mixed in the main combustion stage airflow passage 501 and then enters the flame tube.

As shown in fig. 12, when the second vanes 23 are used as a reference, the through holes 211 may be located between the second vanes 23, specifically, one through hole 211 is provided between every two adjacent second vanes 23, and after the external air enters the gap between the second vanes 23, the external air is mixed with the main combustion stage fuel to form a swirl flow, and finally flows out from between the second vanes 23.

Alternatively, the through hole 211 may be located on a side of the second vane 23 close to the axis of the main combustion stage radial swirler 20, specifically, the through hole 211 is located between an inner edge of the second vane 23 and the axis of the main combustion stage radial swirler 20, that is, the external air is mixed with the main combustion stage fuel after forming a swirling flow by the second vane 23.

Furthermore, the through hole 211 may be located on a side of the second vane 23 away from the axis of the main combustion stage radial swirler 20, specifically, the through hole 211 is located on an outer side of an outer edge of the second vane 23, that is, the external air is primarily mixed with the main combustion stage fuel before entering into the gap of the second vane 23, and then forms a rotational flow under the action of the second vane 23.

In any of the above-described configurations of the support portion 30, the projection of the support portion 30 on the first side wall 21 covers the through hole 211, for example, as shown in fig. 12, when the support portion 30 includes the first vane 33, the projection of the first vane 33 on the first side wall 21 covers the through hole 211, and the first main stage fuel passage 302 in the first vane 33 is communicated with and coaxially disposed with the through hole 211.

In addition to providing the through-holes 211 in the first sidewall 21 and communicating the through-holes 211 with the first main stage fuel passage 302 as described above, such that main stage fuel may enter the main stage radial swirler 20 through the first main stage fuel passage 302 and mix with air in the main stage radial swirler 20, the following may be used:

mode two

Referring to fig. 4, 5 and 11 together, the surface of the second vane 23 is provided with a fuel outlet 231, and the inside of the second vane 23 is provided with a second main stage fuel passage 232 communicated with the fuel outlet 231;

the second main stage fuel passage 232 extends through the thickness of the first sidewall 21 and communicates with the first main stage fuel passage 302.

Specifically, one or more fuel outlets 231 may be provided on the surface of the second vane 23, and in the case of a plurality of fuel outlets 231, the fuel outlets 231 are provided in the height direction of the second vane 23, and the mixing effect of the main stage fuel and the air can be improved by appropriately setting the positions and the number of the fuel outlets 231.

The "surface of the second vane 23" includes a front end surface, a rear end surface, and two side surfaces between the front end surface and the rear end surface in the air intake direction for each second vane 23, and the fuel outlet 231 may be provided on either one of the side surfaces or the rear end surface.

In the present application, the trailing end surface of each second vane 23 is provided with a fuel outlet 231, and the fuel outlet 231 is located at the center of the surface.

The flow direction of the main combustion stage fuel is specifically as follows: the main combustion stage fuel sequentially passes through the feeding pipeline, the cavity in the base 10, the first main combustion stage fuel channel 302 and the second main combustion stage fuel channel 232 in the second blade 23 and is finally ejected out of the fuel outlet 231, and the fuel outlet 231 is arranged on the tail end face of the second blade 23, so that the flow direction of the main combustion stage fuel ejected out of the fuel outlet 231 is consistent with the flow direction of air, and the main combustion stage fuel can be mixed with the air in the flow process.

Further, the projection of the support portion 30 on the first side wall 21 and the projection of the second vane 23 on the first side wall 21 have an overlapping portion, and the projection of the first main stage fuel passage 302 and the second main stage fuel passage 232 on the first side wall 21 are located in the overlapping portion.

The support portion 30 includes a plurality of first blades 33 as an example.

The turning direction of the first blade 33 and/or the second blade 23 may be clockwise or counterclockwise as a whole, the rotation angles of the first blade 33 and the second blade 23 may be specifically set according to actual needs as viewed individually, and the first blade 33 and the second blade 23 may be flat or streamline as viewed structurally.

The rotational direction of the first blade 33 may be the same as or different from the rotational direction of the second blade 23; the total number of the first blades 33 and the total number of the second blades 23 may be the same or different; the rotation angle of the first blade 33 may be the same as or different from the rotation angle of the second blade 23.

Because the height of the first blade 33 can influence the size of the pre-combustion stage air inlet, and similarly, the height of the second blade 23 can influence the size of the main combustion stage air inlet, and the change of the pre-combustion stage air inlet and the main combustion stage air inlet can cause the distribution proportion of the air between the main combustion stage and the pre-combustion stage to change, therefore, in the production process, the heights of the first blade 33 and the second blade 23 can be set according to actual needs, so that the distribution proportion of the air between the main combustion stage and the pre-combustion stage meets the requirement.

Specifically, the first main stage fuel passage 302 may be provided in a part of the first vanes 33, or the first main stage fuel passage 302 may be provided in each of the first vanes 33.

For the plurality of first blades 33 provided with the first main combustion stage fuel channels 302, there are one-to-one corresponding second blades 23, the surface of the second blade 23 is provided with a fuel outlet 231, and the inside of the second blade 23 is provided with a second main combustion stage fuel channel 232 communicated with the fuel outlet 231;

as shown in fig. 11, the first blade 33 is aligned with the corresponding second blade 23 on both sides of the first sidewall 21, and the projections of the two blades on the first sidewall 21 may completely overlap, in other words, the rotation direction of the first blade 33 is the same as that of the second blade 23, and the rotation angle of the first blade 33 is the same as that of the second blade 23.

Or, the first vane 33 overlaps with the projection of the correspondingly disposed second vane 23 on the first sidewall 21, for example, the rotation direction of the first vane 33 is the same as the rotation direction of the second vane 23, but the rotation angle of the first vane 33 is different from the rotation angle of the second vane 23, and the projection of the first vane 33 on the first sidewall 21 intersects with the projection of the second vane 23 on the first sidewall 21, where the intersection position is an overlapping position, and is also a position where the main combustion stage fuel passage is disposed during the processing.

Optionally, the total number of the second vanes 23 is the same as the total number of the first vanes 33, a first main combustion stage fuel passage 302 is provided in each first vane 33, and a second main combustion stage fuel passage 232 is provided in the second vane 23 corresponding to each first vane 33. The first vane 33 and the corresponding second vane 23 may be completely overlapped or intersected with each other on the projection of the first side wall 21.

As shown in fig. 2, 3 and 4, the nozzle further includes a nozzle rod 90, the nozzle rod 90 is fixedly connected to the base 10, and a main combustion stage feed passage 901 and a pre-combustion stage feed passage 902 are provided in the nozzle rod 90 along the axis direction thereof, wherein:

the main combustion stage feed channel 901 is communicated with the main combustion stage fuel joint 101;

the pre-stage feed passage 902 communicates with the pre-stage nozzle 70.

With continuing reference to fig. 2, 3 and 4, the nozzle rod 90 is straight, the main combustion stage feed channel 901 and the pre-combustion stage feed channel 902 which are arranged inside the nozzle rod 90 are both arranged along the axial direction of the nozzle rod 90 and directly communicated with the main combustion stage fuel joint 101 and the pre-combustion stage nozzle 70 on the base 10, and since the air inlet for providing air for the combustion of the pre-combustion stage fuel is arranged between the main combustion stage radial swirler 20 and the base 10, the nozzle rod 90 does not obstruct the air from entering the pre-combustion stage, and meanwhile, compared with the prior art, the end of the nozzle rod 90 does not need to be provided with a branch, the structure of the nozzle rod 90 is simple, and the processing difficulty is low.

Optionally, the included angle formed between the axis of the nozzle rod 90 and the axis of the base 10 is an obtuse angle, so that the extension part of the nozzle rod 90 can be close to the outer wall of the combustion chamber, and the outer space of the combustion chamber is saved.

As can be seen from the above description, in the nozzle provided in the embodiment of the present invention, the support portion is disposed between the main combustion stage radial swirler and the base, and the pre-combustion stage air inlet passage communicated with the pre-combustion stage air flow passage is disposed in the support portion, so that air required for combustion of the pre-combustion stage fuel can enter the pre-combustion stage air flow passage from the pre-combustion stage air inlet passage and form a swirling flow under the action of the pre-combustion stage swirler, and the swirling flow can ensure combustion of the pre-combustion stage fuel on one hand and form a backflow region in the flame tube to stabilize flame on the other hand.

It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.