CN111780164A - Flame tube head structure, flame tube and gas turbine engine - Google Patents
Flame tube head structure, flame tube and gas turbine engine Download PDFInfo
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- CN111780164A CN111780164A CN202010528962.XA CN202010528962A CN111780164A CN 111780164 A CN111780164 A CN 111780164A CN 202010528962 A CN202010528962 A CN 202010528962A CN 111780164 A CN111780164 A CN 111780164A
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- wall body
- head
- head wall
- rotational flow
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Spray-Type Burners (AREA)
Abstract
The invention discloses a flame tube head structure, a flame tube and a gas turbine engine, which comprise a head wall body which is arranged at the inlet end of the flame tube and used for isolating internal gas and external air, and a rotational flow structure which is arranged at the inlet end of the head wall body and used for leading airflow into the head wall body after forming rotational flow, wherein a plurality of diverging holes are arranged on the head wall body, the central axes of the diverging holes are inclined towards the rotational direction of the rotational flow, and part of air outside the head wall body is guided into the head wall body through the diverging holes to form jet flow inclined towards the rotational direction of the rotational flow, so that the jet flow and the rotational flow in the head wall body are mutually acted on the inner wall surface of the head wall body to rotate to form a wall surface rotating air film attached to the inner wall surface of the head wall. According to the flame tube head structure, the wall surface rotating gas film is used for isolating hot combustion gas from being in direct contact with the head wall body and absorbing heat of the head wall body, so that the head wall body is cooled and protected.
Description
Technical Field
The invention relates to the technical field of gas turbine engines, in particular to a flame tube head structure, a flame tube and a gas turbine engine.
Background
The flame tube is a key part of a combustion chamber of a gas turbine engine, fuel oil is combusted in the flame tube, the average temperature of the fuel gas in a main combustion area close to the head of the flame tube is as high as (2000-.
Among the prior art, generally adopt the guide plate to carry out the heat protection to the flame tube head, the guide plate is fixed at the head wall body inboard, plays isolated main combustion area high temperature radiation's effect, is equipped with on the head wall body to be used for the refrigerated impact hole of cooling air impingement cooling to protection flame tube head wall body. One side of the guide plate is contacted with the jet flow of the impact holes to reduce the temperature of the guide plate, and the other side of the guide plate is directly contacted with high-temperature fuel gas. However, with the development of the combustion chamber, the temperature of the main combustion area is higher and higher, and the problems of deformation, ablation, cracks and the like inevitably occur to the head structure of the flame tube due to the limitation of the cooling structure. The deformation will deteriorate the head flow field, affecting the performance of the combustion chamber; the ablation and cracks will likely further form chipping and damage to the turbine component. In addition, in order to prolong the service life of the flame tube, the guide plate needs to be replaced after working for a period of time, and the maintenance cost is improved.
Disclosure of Invention
The invention provides a flame tube head structure, a flame tube and a gas turbine engine, and aims to solve the technical problems that the existing flame tube head structure is easy to deform and damage at high temperature to influence the flow field of the flame tube head and the maintenance cost is high.
According to one aspect of the invention, the head structure of the flame tube comprises a head wall body which is arranged on an inlet end of the flame tube and used for isolating internal fuel gas and external air, and a rotational flow structure which is arranged on the inlet end of the head wall body and used for leading airflow into the head wall body after forming rotational flow, wherein a plurality of diverging holes are formed in the head wall body, the central axes of the diverging holes are inclined towards the rotational direction of the rotational flow, a part of air outside the head wall body is guided by the diverging holes to be jetted into the head wall body to form jet flow inclined towards the rotational direction of the rotational flow, the jet flow and the rotational flow in the head wall body are enabled to interact with each other at the inner wall surface of the head wall body to rotate to form a wall surface rotating air film attached to the inner wall surface.
Furthermore, the central axis of the divergent hole is inclined towards the rotational direction of the rotational flow on the normal section of the divergent hole, and the included angle between the central axis of the divergent hole and the normal line of the head wall body at the divergent hole is 50-70 degrees.
Further, the plurality of diverging holes are uniformly arranged from the boundary of the head wall body and the swirling structure to the edge of the head wall body along the extending direction of the head wall body; the plurality of the divergence holes are uniformly distributed on the wall body of the head in the circumferential direction, and the radius of the inscribed circle of the cross section of the plurality of the divergence holes is the distance from the axial line of the divergence holes to the center of the rotational flow structure.
Further, the diverging hole is a circular hole or a horn-shaped hole with the aperture gradually becoming larger along the emission direction of the jet flow.
Further, the swirl structure comprises a first-stage swirler, the first-stage swirler comprises a plurality of first-stage blades which are arranged at intervals along the circumferential direction, and the plurality of first-stage blades are sequentially twisted towards the same rotation direction to form a first swirl channel so that the airflow is introduced into the wall body of the head after forming the first swirl.
Furthermore, the rotational flow structure also comprises a secondary vortex device arranged between the air outlet end of the primary vortex device and the head wall body, the secondary vortex device comprises a plurality of secondary blades arranged at intervals along the circumferential direction, and the plurality of secondary blades are sequentially twisted towards the same rotation direction to form a second rotational flow channel, so that the air flow is introduced into the head wall body after forming a second rotational flow; the second swirling flow is closer to the inner wall surface of the head wall body than the first swirling flow.
Further, the second swirling flow has a swirling direction opposite to that of the first swirling flow, and the center axis of the diverging hole is inclined to the swirling direction of the second swirling flow.
Furthermore, the rotational flow structure also comprises a venturi tube arranged between the first-stage vortex device and the second-stage vortex device, and the venturi tube is used for guiding the first rotational flow generated by the first rotational flow channel to be conveyed to the central area in the head wall body and the second rotational flow to be conveyed to the edge area in the head wall body, so that the second rotational flow generated by the second rotational flow channel is more attached to the inner wall surface of the head wall body.
According to another aspect of the invention, the flame tube comprises the flame tube head structure.
According to another aspect of the invention, there is also provided a gas turbine engine comprising the combustor basket described above.
The invention has the following beneficial effects:
the flame tube head structure of the invention introduces airflow into the head wall body through the rotational flow structure to form rotational flow, leads a part of air outside the head wall body to be injected into the head wall body to form jet flow inclined towards the rotational flow direction of the rotational flow by arranging the divergence hole on the head wall body and inclining the central axis of the divergence hole towards the rotational flow direction of the rotational flow, further leads the jet flow and the rotational flow in the head wall body to rotate at the inner wall surface of the head wall body to form a wall surface rotating gas film attached to the inner wall surface of the head wall body under the interaction of the jet flow and the rotational flow, isolates hot gas from being directly contacted with the head wall body through the wall surface rotating gas film and absorbs the heat of the head wall body, thereby carrying out cooling protection on the head wall body, avoiding the high-temperature radiation of a main combustion area directly acting on the head wall body to cause the high-temperature deformation damage of the head wall body to influence the flow field of the flame tube, and in addition, reducing, and a part of rotational flow or a divergence hole of the wall surface rotating air film is ejected to form jet flow which inclines towards the rotational direction of the rotational flow to wash away carbon deposit on the inner wall surface of the head wall body, and most of rotational flow of the wall surface rotating air film which absorbs heat is uniformly mixed with fuel oil drops in the head wall body after leaving the outer wall surface of the head wall body to generate combustion reaction, so that the utilization rate of air flow is improved, the air flow is prevented from being gathered in the central area of the head wall body, and the edge area of the head wall body forms a high oil-gas ratio area, and the pollution emission is favorably reduced.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic structural view of a flame tube head configuration according to a preferred embodiment of the invention;
FIG. 2 is a schematic structural view of the head wall according to the preferred embodiment of the present invention;
fig. 3 is a schematic structural view of a divergent hole of a preferred embodiment of the present invention on a normal section of a head wall.
Illustration of the drawings:
100. a flame tube; 200. a fuel nozzle; 1. a head wall body; 11. a diverging aperture; 2. a rotational flow structure; 21. a primary swirler; 22. a secondary swirler; 3. a venturi.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
FIG. 1 is a schematic structural view of a flame tube head configuration according to a preferred embodiment of the invention; FIG. 2 is a schematic structural view of the head wall according to the preferred embodiment of the present invention; fig. 3 is a schematic structural view of a divergent hole of a preferred embodiment of the present invention on a normal section of a head wall.
As shown in fig. 1 (part of the diverging holes 11 are not shown), the flame tube head structure of the present embodiment includes a head wall 1 installed on the inlet end of the flame tube 100 for isolating the internal combustion gas from the external air and a swirling structure 2 installed on the inlet end of the head wall 1 for swirling the air flow and introducing the air flow into the head wall 1, the head wall 1 is provided with the diverging holes 11, the central axis of the diverging holes 11 is inclined toward the swirling direction, a part of the air outside the head wall 1 is guided by the diverging holes 11 to be jetted into the head wall 1 to form a swirling jet flow, the swirling jet flow is inclined toward the swirling direction, the jet flow and the swirling flow in the head wall 1 interact with each other at the inner wall surface of the head wall 1 to form a wall surface rotating air film attached to the inner wall surface of the head wall 1, and thereby protecting the head wall. The flame tube head structure of the invention introduces airflow into the head wall body 1 through the rotational flow structure 2 to form rotational flow, leads a part of air outside the head wall body 1 to be injected into the head wall body 1 to form jet flow inclined towards the rotational flow direction by arranging the diverging hole 11 on the head wall body 1 and inclining the central axis of the diverging hole 11 towards the rotational flow direction, further leads the jet flow and the rotational flow in the head wall body 1 to mutually act on the inner wall surface of the head wall body 1 to rotate to form a wall surface rotating gas film attached to the inner wall surface of the head wall body 1, isolates hot gas from directly contacting the head wall body through the wall surface rotating gas film and absorbs the heat of the head wall body 1, thereby carrying out cooling protection on the head wall body 1, avoiding the high-temperature radiation of a main combustion area directly acting on the head wall body 1 to cause high-temperature deformation damage of the head wall body 1 to influence the head flow field of the, in addition, the phenomenon that fuel drops on the inner wall surface of the head wall body 1 to be carbonized due to the fact that the temperature of the head wall body 1 is too high can be reduced, part of rotational flow of the wall surface rotating air film and the diverging holes 11 are ejected to form jet flow inclining towards the rotational direction of the rotational flow to wash away carbon deposit on the inner wall surface of the head wall body, most of rotational flow of the wall surface rotating air film which absorbs heat is evenly mixed with fuel oil drops in the head wall body 1 after leaving the wall surface of the head wall body 1 to generate combustion reaction, the utilization rate of air flow is improved, the air flow is prevented from being gathered in the central area of the head wall body 1, and the edge area of the head wall body 1 forms a high oil-gas ratio area, and pollution emission is reduced.
As shown in fig. 3, the central axis of the divergent hole 11 is inclined to the rotational direction of the rotational flow on the normal section of the divergent hole 11, and the angle between the central axis of the divergent hole 11 and the normal of the head wall 1 at the divergent hole 11 is 50 to 70 degrees. The normal cross section of the head wall 1 at the divergent hole 11 is a plane formed by a tangent line at the center point of the through divergent hole 11 centered on the swirling structure 2 and a normal line of the head wall 1 at the center point of the through divergent hole 11. The jet flow direction can be divided into a tangential component vector along the head wall body 1 and an axial component vector vertical to the head wall body 1, the tangential component vector of the jet flow direction is consistent with the rotating direction of the rotational flow, and the axial component vector of the jet flow direction is consistent with the advancing direction of the rotational flow. Optionally, the center axis of the diverging opening 11 is inclined in the radial direction of the swirling flow in the radial cross section of the head wall 1.
As shown in fig. 2, a plurality of diverging holes 11 are uniformly arranged from the boundary between the head wall 1 and the swirling structure 2 to the edge of the head wall 1 in the extending direction of the head wall 1; the plurality of diverging holes 11 are uniformly distributed on the head wall body 1 in the circumferential direction, and the radius of the inscribed circle of the normal section of the plurality of diverging holes 11 is the distance between the axial line of the diverging holes 11 and the center of the rotational flow structure 2. The distribution center of the divergent holes 11 is the center of the rotational flow structure 2. A plurality of diverging holes 11 are evenly distributed in the center of the swirling structure 2 on the head wall 1. The air outside the head wall 1 enters the head wall 1 from the plurality of divergent holes 11 to form jet flow, and the wall surface rotating air film formed by rotating under the interaction of the rotational flow in the head wall 1 uniformly wraps the whole inner wall surface of the head wall 1. Optionally, the diverging holes 11 are circular holes. Since the diverging holes 11 are inclined in the direction of the swirling flow in the normal cross section of the head wall 1, both the air inlet and the air outlet of the diverging holes 11 are elliptical. Alternatively, the diverging hole 11 is a trumpet-shaped hole having an aperture gradually larger in the emission direction of the jet. Alternatively, the arrangement pitch of the diverging holes 11 becomes gradually smaller from the inlet end of the head wall 1 to the outlet end of the head wall 1. Alternatively, the aperture ratio (the number of divergent holes 11 per unit area) of each region of the head wall 1 is 3% to 6%. Optionally, the diameter of the diverging hole 11 is 0.35mm to 0.65 mm.
As shown in fig. 1, the swirling structure 2 includes a first-stage swirler 21, the first-stage swirler 21 includes a plurality of first-stage blades arranged at intervals in the circumferential direction, and the plurality of first-stage blades are sequentially twisted towards the same rotating direction to form a first swirling channel, so that the airflow is introduced into the head wall 1 after forming a first swirling flow. The rotational flow structure 2 further comprises a secondary vortex device 22 arranged between the air outlet end of the primary vortex device 21 and the head wall body 1, the secondary vortex device 22 comprises a plurality of secondary blades arranged at intervals along the circumferential direction, and the plurality of secondary blades are sequentially twisted towards the same rotational direction to form a second rotational flow channel, so that the airflow is introduced into the head wall body 1 after forming a second rotational flow; the second swirling flow is closer to the inner wall surface of the head wall 1 than the first swirling flow. The swirling flow structure 2 further comprises a venturi tube 3 arranged between the first-stage swirler 21 and the second-stage swirler 22 and used for guiding the first swirling flow generated by the first swirling flow channel to be conveyed to a central region in the head wall body 1 and the second swirling flow to be conveyed to an edge region in the head wall body 1, so that the second swirling flow generated by the second swirling flow channel is more attached to the inner wall surface of the head wall body 1. The jet flow entering the head wall 1 through the diverging hole 11 and the second swirling flow attached to the inner wall surface of the head wall 1 rotate by interaction to form a wall surface rotating air film.
As shown in fig. 2, the second swirling flow has a direction opposite to the first swirling flow, and the center axis of the diverging hole 11 is inclined to the direction of the second swirling flow. The fuel nozzle 200 is inserted along the axial direction of the rotational flow structure 2, the insertion depth does not exceed the venturi 3, the fuel nozzle 200 atomizes fuel and then sprays the atomized fuel into the flame tube head structure to form conical oil mist, and the oil mist in the central area directly enters the central area in the head wall body 1 along with the first rotational flow to generate combustion reaction; the oil mist in the peripheral area is driven by the first rotational flow to rotate and flow along the inner side wall surface of the venturi tube 3 to form an oil film, then is cut at a high speed by the second rotational flow rotating towards the opposite direction when flowing to the outlet end of the venturi tube 3, is further broken into fine oil drops and enters the edge area in the head wall body 1 along with the second rotational flow, and therefore more uniform oil mist distribution is formed in the whole space in the head wall body 1. Part of the rotational flow of the wall surface rotating film is uniformly mixed with oil drops in the inner edge area of the head wall body 1 after absorbing the heat of the head wall body 1, and then a combustion reaction is carried out.
As shown in fig. 1 and 2, a part of the flame tube head structure in fig. 2 is not shown, and the flame tube 100 of the present embodiment includes the above-described flame tube head structure. The plurality of flame tube head structures are uniformly distributed on the inlet end of an annular inner cavity formed by the inner ring of the flame tube 100 and the outer ring of the flame tube 100 along the circumferential direction. Absorb the heat of head wall body 1 through the rotatory gas film of wall, isolated hot gas and head wall body 1 direct contact to cooling protection to head wall body 1 avoids head wall body 1 to warp. The gas turbine engine of the present embodiment includes the combustor basket 100 described above. The flame tube head structure is not easy to deform, does not need frequent replacement, and has long service life and low maintenance cost.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A flame tube head structure, which is characterized in that,
comprises a head wall body (1) which is arranged on the inlet end of a flame tube (100) and is used for isolating internal gas from external air, and a rotational flow structure (2) which is arranged on the inlet end of the head wall body (1) and is used for leading airflow into the head wall body (1) after forming rotational flow,
the head wall body (1) is provided with a divergence hole (11), the central axis of the divergence hole (11) inclines towards the rotating direction of the rotational flow,
a part of air outside the head wall body (1) is guided by the divergence hole (11) to be injected into the head wall body (1) to form jet flow inclined towards the rotational direction of the rotational flow, so that the jet flow and the rotational flow in the head wall body (1) mutually act on the inner wall surface of the head wall body (1) to form a wall surface rotating air film attached to the inner wall surface of the head wall body (1), and the protection of the head wall body (1) is realized.
2. The liner head structure according to claim 1,
the central axis of the divergent hole (11) is inclined to the rotational direction of the rotational flow on the normal section of the divergent hole (11), and the included angle between the central axis of the divergent hole (11) and the normal of the head wall body (1) at the divergent hole (11) is 50-70 degrees.
3. The liner head structure according to claim 1,
a plurality of diverging holes (11) are uniformly arranged from the boundary of the head wall body (1) and the rotational flow structure (2) to the edge of the head wall body (1) along the extending direction of the head wall body (1);
the plurality of the divergence holes (11) are uniformly distributed on the head wall body (1) in the circumferential direction, and the radius of the tangent circle of the normal section of the plurality of the divergence holes (11) is the distance between the axial line of the divergence holes (11) and the center of the rotational flow structure (2).
4. The liner head structure according to claim 1,
the diverging hole (11) is a circular hole or a horn-shaped hole with the aperture gradually becoming larger along the emission direction of the jet flow.
5. The liner head structure according to claim 1,
the swirl structure (2) comprises a first-stage swirler (21), the first-stage swirler (21) comprises a plurality of first-stage blades arranged at intervals along the circumferential direction, and the plurality of first-stage blades are sequentially twisted towards the same rotation direction to form a first swirl channel so that airflow is introduced into the head wall body (1) after forming a first swirl.
6. The liner head structure according to claim 5,
the swirl structure (2) further comprises a secondary swirler (22) arranged between the air outlet end of the primary swirler (21) and the head wall body (1), the secondary swirler (22) comprises a plurality of secondary blades arranged at intervals along the circumferential direction, and the plurality of secondary blades are sequentially twisted towards the same rotation direction to form a second swirl channel so that the air flow is introduced into the head wall body (1) after forming a second swirl;
the second swirling flow is closer to the inner wall surface of the head wall body (1) than the first swirling flow.
7. The liner head structure according to claim 6,
the direction of rotation of the second rotational flow is opposite to that of the first rotational flow, and the central axis of the divergent hole (11) is inclined to the direction of rotation of the second rotational flow.
8. The liner head structure according to claim 6,
the rotational flow structure (2) further comprises a venturi tube (3) arranged between the first-stage vortex device (21) and the second-stage vortex device (22) and used for guiding the first rotational flow generated by the first rotational flow channel to be conveyed to a central area in the head wall body (1) and the second rotational flow to be conveyed to an edge area in the head wall body (1), so that the second rotational flow generated by the second rotational flow channel is attached to the inner wall surface of the head wall body (1).
9. A flame tube comprising the flame tube head structure of any of claims 1-8.
10. A gas turbine engine, characterized in comprising a combustor basket (100) as claimed in claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010528962.XA CN111780164B (en) | 2020-06-11 | 2020-06-11 | Flame tube head structure, flame tube and gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010528962.XA CN111780164B (en) | 2020-06-11 | 2020-06-11 | Flame tube head structure, flame tube and gas turbine engine |
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| Publication Number | Publication Date |
|---|---|
| CN111780164A true CN111780164A (en) | 2020-10-16 |
| CN111780164B CN111780164B (en) | 2022-05-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010528962.XA Active CN111780164B (en) | 2020-06-11 | 2020-06-11 | Flame tube head structure, flame tube and gas turbine engine |
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| Country | Link |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113137629A (en) * | 2021-04-19 | 2021-07-20 | 中国航发湖南动力机械研究所 | Double-stage integral swirler and flame tube head structure |
| CN113154450A (en) * | 2021-04-15 | 2021-07-23 | 中国航发湖南动力机械研究所 | Novel fuel atomization device and flame tube head structure with same |
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| GB1130371A (en) * | 1964-10-20 | 1968-10-16 | Rolls Royce | Improvements in boundary wall structures for hot fluid streams |
| CN202419701U (en) * | 2011-12-28 | 2012-09-05 | 中航商用航空发动机有限责任公司 | Flame tube wall plate with multiple inclined holes, flame tube and gas turbine combustion chamber |
| CN103292356A (en) * | 2013-06-19 | 2013-09-11 | 北京航空航天大学 | Beveling main combustion hole rotation aiding low-pollution backflow combustion chamber |
| CN109210570A (en) * | 2018-09-25 | 2019-01-15 | 厦门大学 | For cooling down the composite cooling apparatus of RQL head of combustion chamber |
| CN109990309A (en) * | 2019-03-05 | 2019-07-09 | 南京航空航天大学 | A kind of compound cooling structure of combustion chamber wall surface and turboshaft engine reverse flow type combustor |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1130371A (en) * | 1964-10-20 | 1968-10-16 | Rolls Royce | Improvements in boundary wall structures for hot fluid streams |
| CN202419701U (en) * | 2011-12-28 | 2012-09-05 | 中航商用航空发动机有限责任公司 | Flame tube wall plate with multiple inclined holes, flame tube and gas turbine combustion chamber |
| CN103292356A (en) * | 2013-06-19 | 2013-09-11 | 北京航空航天大学 | Beveling main combustion hole rotation aiding low-pollution backflow combustion chamber |
| CN109210570A (en) * | 2018-09-25 | 2019-01-15 | 厦门大学 | For cooling down the composite cooling apparatus of RQL head of combustion chamber |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113154450A (en) * | 2021-04-15 | 2021-07-23 | 中国航发湖南动力机械研究所 | Novel fuel atomization device and flame tube head structure with same |
| CN113154450B (en) * | 2021-04-15 | 2022-08-09 | 中国航发湖南动力机械研究所 | Fuel oil atomization device and flame tube head structure with same |
| CN113137629A (en) * | 2021-04-19 | 2021-07-20 | 中国航发湖南动力机械研究所 | Double-stage integral swirler and flame tube head structure |
| CN113137629B (en) * | 2021-04-19 | 2022-11-04 | 中国航发湖南动力机械研究所 | Double-stage integral swirler and flame tube head structure |
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| Publication number | Publication date |
|---|---|
| CN111780164B (en) | 2022-05-17 |
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