CN112377946B - Large bent pipe structure of axial floating type backflow annular combustion chamber - Google Patents
Large bent pipe structure of axial floating type backflow annular combustion chamber Download PDFInfo
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- CN112377946B CN112377946B CN202011282071.7A CN202011282071A CN112377946B CN 112377946 B CN112377946 B CN 112377946B CN 202011282071 A CN202011282071 A CN 202011282071A CN 112377946 B CN112377946 B CN 112377946B
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- large elbow
- return bend
- floating type
- axial floating
- cooling
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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
- F23R3/52—Toroidal combustion chambers
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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
- F23R3/60—Support structures; Attaching or mounting means
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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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
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- Engineering & Computer Science (AREA)
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a large elbow structure of an axial floating type backflow annular combustion chamber, belongs to the field of aviation power, and particularly relates to the field of a microminiature backflow annular combustion chamber, which aims to overcome the defect that the temperature of the inner wall of the large elbow cannot be automatically adjusted according to different working conditions of an engine. Big return bend and flame section of thick bamboo subassembly components of a whole that can function independently set up, and elastic support spare and big return bend are surface contact simultaneously, make to form cooling gap between big return bend and the flame section of thick bamboo subassembly, and the cooling air that different clearance values got into is different, and the cooling effect is different, has realized the effect of the temperature of independently adjusting big return bend inner wall, has increased the life of big return bend simultaneously.
Description
Technical Field
The invention discloses a large elbow structure of an axial floating type backflow annular combustion chamber, belongs to the technical field of aviation power, and particularly relates to the technical field of a microminiature backflow annular combustion chamber of a gas turbine engine.
Background
In order to meet the future development needs of gunships, weaponry, and auxiliary power units, the performance of aircraft turbine engines has also increased. The combustion chamber of small engines has generally been the reverse flow combustion chamber since the 80 s. In the once-through combustion chamber, air flows through the flame tube in a straight way, and the flowing direction from the inlet to the outlet is basically unchanged. Whereas in the reverse flow combustor the flow path of the gases is quite different, figure 1 shows a schematic gas flow diagram for the reverse flow annular combustor. High-pressure air from the compressor enters a secondary flow channel between the outer ring of the flame tube and the outer sleeve of the combustion chamber from the tail end of the combustion chamber, flows to the head of the flame tube, meanwhile, one part of air enters the flame tube through the air inlet holes and the cooling holes in the outer ring of the flame tube, the other part of air needs to bypass the head of the flame tube, and can enter the flame tube through the air inlet holes and the cooling holes in the inner ring of the flame tube after rotating for 180 degrees. In addition, the combustion products also need to be turned 180 ° within the gas duct before finally entering the turbine. Referring to fig. 1, the backflow combustion chamber comprises a small elbow, a large elbow, an outer casing, a flame tube outer ring, a fuel nozzle, a flame tube inner ring, a combustion chamber inner casing, an inner two-strand channel and a high-pressure turbine, wherein cold air enters the two-strand channel through an air inlet, then enters the flame tube to be heated and combusted along with fuel oil, then is changed into high-temperature fuel gas, and enters the high-pressure turbine to expand and do work after passing through a flame tube outlet and an exhaust elbow.
The large bent pipe is used as a special structure of the backflow combustion chamber, the large bent pipe needs to bear direct impact of high-temperature gas in the flame tube, the gas temperature is high, the speed is high, the problem of severe high-temperature ablation is solved, and due to special thermal impact and positions of the large bent pipe, the cooling of the large bent pipe needs to be carefully designed. The cooling mode of the large elbow of the common backflow combustion chamber comprises a double-wall structure, a divergent cooling structure, a film cooling structure, an impingement cooling structure, a divergent cooling structure and the like. With impact + cooling structure of dispersing, as shown in fig. 2, its double-walled is the impact pore wall outside the gas and the inboard pore wall that disperses of gas, and big return bend outside cold air gets into big return bend inner chamber through the impact hole on the impact pore wall, carries out impingement cooling to dispersing the hole wall, and there are a large amount of holes of dispersing in the hole wall, and the cooling gas of big return bend inside forms one deck cooling gas film through dispersing the hole at big return bend gas side wall for cool off big return bend.
The double wall is complicated to process, and a large number of diverging holes and cooling holes increase the processing cost. And the double-wall structure has poor cooling effect at the starting end, and the temperature distribution is 'front hot and back cold'. For a microminiature backflow combustion chamber, if a traditional large bent pipe cooling mode is adopted, the manufacturing cost and the processing complexity are increased, and the microminiature backflow combustion chamber is not suitable for increasing the temperature rise of the combustion chamber.
Aiming at the micro-miniature backflow combustion chamber, the existing large elbow cooling mode has the defects that firstly, the temperature of the inner wall of the large elbow cannot be automatically adjusted according to different working conditions of an engine, the service life of the large elbow is short, secondly, the processing is complex, the manufacturing cost is high, thirdly, the cooling effect of the starting end of the double-wall structure is poor, and the temperature distribution is 'front hot and back cold'.
Disclosure of Invention
The invention aims to: the utility model provides a big return bend structure of axial floating backward flow annular combustion chamber to solve current cooling method and can not realize the temperature of the big return bend inner wall of autonomic regulation according to the different work condition of engine, the short defect of life of big return bend.
The technical scheme adopted by the invention is as follows:
the utility model provides a big return bend structure of axial floating backward flow annular combustion chamber, includes the diffuser subassembly, flame section of thick bamboo subassembly, turbine director subassembly, be provided with a plurality of elastic support spare on the diffuser subassembly, elastic support spare with be provided with big return bend between the flame section of thick bamboo subassembly, big return bend is fixed on the turbine director subassembly, big return bend with form cooling gap between the flame section of thick bamboo subassembly.
In the technical scheme of the application, an elastic supporting part is installed on a diffuser component, a large elbow is installed on a turbine guider component, the elastic supporting part is not fixedly connected with the large elbow and only contacts with the surface of the large elbow and is used for limiting the axial extension and contraction of the large elbow, the supporting force provided by the extension and contraction amount is similar to or consistent with the aerodynamic force change of high-temperature gas of a flame tube, the large elbow is used for limiting the axial movement by the turbine guider component and the elastic supporting part, a cooling gap between the large elbow and the flame tube component is formed under the combined action of the supporting force provided by the elastic supporting part and the aerodynamic force formed by the large elbow with gas impulse force in the flame tube component, the aerodynamic force formed by high-temperature gas impact is different under different working conditions of an engine, cooling gaps with different sizes are formed between the large elbow and the flame tube component, and the air forms wall-attached jet flow on the gas side wall of the large elbow through the cooling gaps, the function of the wall-attached jet flow is to prevent the high-temperature fuel gas from directly contacting the wall surface of the large elbow pipe and to perform heat convection with the wall surface, so that the temperature of the fuel gas near the wall surface of the large elbow pipe is reduced, the heat radiation of the high-temperature fuel gas is reduced, the service life of the large elbow pipe is prolonged, the cooling air entering at different clearance values is different, and the cooling effect is different; the large elbow and the flame tube assembly are arranged in a split mode, meanwhile, the large elbow and the elastic supporting piece are also arranged in a split mode, no fixed connection exists, the large elbow is formed and processed independently, the processing technology is simplified, and the manufacturing cost can be reduced. The split type setting through big return bend and flame section of thick bamboo subassembly, there is not fixed connection between the two, there is not fixed connection simultaneously between elastic support spare and the big return bend, only be surface contact with big return bend, be used for restricting big return bend axial motion, make and form the cooling clearance between big return bend and the flame section of thick bamboo subassembly, under the different operating mode of engine, the gas impact aerodynamic force is different, elastic support spare's holding power changes along with the compression volume change, two power formation dynamic balance, the not cooling clearance of equidimension appears thereupon, the cooling air that different clearance values got into is different, the cooling effect is different, the effect of independently adjusting the temperature of big return bend inner wall has been realized, the life of big return bend has been increased simultaneously.
Preferably, the flame tube assembly comprises a flame tube outer shell and a flame tube inner shell, and the large bent tube is matched with the wall surface of the tail part of the flame tube outer shell and forms the cooling gap. The large bent pipe is partially attached to the wall surface of the tail part of the flame tube shell, and the shape of the attached part is consistent.
Preferably, the cooling gap is in the range of 0-1.5 mm. More preferably, the cooling gap may be 0mm, 0.2mm, 0.4mm, 0.6mm, 0.8mm, 1mm, 1.2mm, 1.3mm, 1.5 mm.
Preferably, the farthest end of the outer ring of the large elbow is provided with a small flanging. The large elbow is partially attached to the wall surface of the tail part of the flame tube shell, the shape of the attached part is consistent, and a small flanging structure is arranged at the farthest end of the outer ring of the large elbow and used for efficiently introducing cooling airflow.
Preferably, one side of the large elbow close to the turbine guider component is provided with a plurality of rows of small holes, and each row of small holes are distributed along the circumferential direction of the large elbow.
More preferably, the interval of the small holes on the wall surface of the large elbow is 4-8mm, and the jet angle of each small hole is 0-20 degrees.
More preferably, the interval of each row of small holes on the wall surface of the large elbow is 6mm, and the jet angle of each small hole is 10 degrees. Preferably, three rows of small holes are formed, and the intervals of the small holes in each row are consistent along the wall surface, so that cooling air is introduced to cool the rear section of the large bent pipe and the turbine guide vane root.
Preferably, the number of the elastic supporting members is 3 to 6.
Preferably, the central axis of each elastic supporting element passes through the maximum point of the curvature of the large elbow, and the central axis of each elastic supporting element passes through the maximum point of the curvature of the large elbow, so that the large elbow can axially extend and retract, and the supporting force provided by the extension and retraction amount is similar to or consistent with the aerodynamic force change of the high-temperature gas of the flame tube.
The large elbow pipe of the invention is applied to a backflow combustion chamber, and the combustion chamber is provided with a combustion chamber inlet, a nozzle and the like which are conventional in the field.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. the large elbow pipe and the flame tube assembly and the large elbow pipe and the elastic supporting piece are arranged in a split mode, so that a cooling gap is formed between the large elbow pipe and the flame tube assembly, under different working conditions of an engine, gas impact aerodynamic force is different, supporting force of the elastic supporting piece changes along with the change of compression amount, dynamic balance is formed by the two forces, cooling gaps with different sizes are formed, cooling air entering different gap values is different, the cooling effect is different, the effect of automatically adjusting the temperature of the inner wall of the large elbow pipe is achieved, and meanwhile the service life of the large elbow pipe is prolonged;
2. the large elbow is axially acted by two forces, namely a supporting force provided by the elastic supporting piece and a pneumatic force formed by high-temperature gas impacting the large elbow, the gas impacting pneumatic force is different under different working conditions of the engine, the supporting force of the elastic supporting piece changes along with the change of the compression amount, the two forces form dynamic balance, and then cooling gaps with different sizes are formed, so that cooling air matched with the high-temperature gas is obtained;
4. the large bent pipe is partially attached to the wall surface of the tail part of the flame tube shell, the shape of the attached part is consistent, and a small flanging structure is arranged at the farthest end of the outer ring of the large bent pipe and used for efficiently introducing cooling airflow;
5. the wall-attached air flow formed by the cooling gap between the large elbow and the flame tube assembly is gradually weakened along with the increase of the jet depth, the cooling effect on the rear section of the large elbow is poor, the temperature distribution of front cooling and rear heating is easy to generate, three rows of small holes are formed to introduce cooling air, the rear section of the large elbow and the vortex guide blade root which cannot provide effective cooling effect by wall-attached jet flow are cooled, the integral temperature gradient of the large elbow is reduced, and the service life of the large elbow is prolonged;
6. when the large elbow pipe is applied to the backflow combustion chamber, the large elbow pipe has good wall surface cooling effect and high-temperature fuel gas mixing effect, the temperature gradient of the wall surface of the large elbow pipe can be effectively reduced, and the problem of high-temperature ablation is solved, so that the strength and the service life of the large elbow pipe are improved, and meanwhile, the large elbow pipe is simple in structure, high in strength, simple and convenient to machine and low in cost.
Drawings
FIG. 1 is a schematic view of a prior art reverse flow combustor;
FIG. 2 is a schematic diagram of a prior art impingement + transpiration cooling configuration;
FIG. 3 is a schematic structural view of a large elbow structure according to the present invention;
FIG. 4 is an enlarged view of I of FIG. 3 according to the present invention;
FIG. 5 is a schematic view of the cooling gap of the present invention;
FIG. 6 is a schematic view of the structure of three rows of small holes on the large elbow pipe of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Example 1
As shown in fig. 3-5, a large elbow structure of an axial floating type backflow annular combustor comprises a diffuser assembly, a flame tube assembly and a turbine guider assembly, wherein a plurality of elastic supporting elements are arranged on the diffuser assembly, a large elbow is arranged between the elastic supporting elements and the flame tube assembly, the central axis of each elastic supporting element passes through the maximum point of the curvature of the large elbow, the large elbow is fixed on the turbine guider assembly, and a cooling gap is formed between the large elbow and the flame tube assembly.
In the technical scheme of the application, an elastic supporting part is installed on a diffuser component, a large elbow is installed on a turbine guider component, the elastic supporting part is not fixedly connected with the large elbow and only contacts with the surface of the large elbow and is used for limiting the axial extension and contraction of the large elbow, the supporting force provided by the extension and contraction amount is similar to or consistent with the aerodynamic force change of high-temperature gas of a flame tube, the large elbow is used for limiting the axial movement by the turbine guider component and the elastic supporting part, a cooling gap between the large elbow and the flame tube component is formed under the combined action of the supporting force provided by the elastic supporting part and the aerodynamic force formed by the large elbow with gas impulse force in the flame tube component, the aerodynamic force formed by high-temperature gas impact is different under different working conditions of an engine, cooling gaps with different sizes are formed between the large elbow and the flame tube component, and the air forms wall-attached jet flow on the gas side wall of the large elbow through the cooling gaps, the function of the wall-attached jet flow is to prevent the high-temperature fuel gas from directly contacting the wall surface of the large elbow pipe and to perform heat convection with the wall surface, so that the temperature of the fuel gas near the wall surface of the large elbow pipe is reduced, the heat radiation of the high-temperature fuel gas is reduced, the service life of the large elbow pipe is prolonged, the cooling air entering at different clearance values is different, and the cooling effect is different; the large elbow and the flame tube assembly are arranged in a split mode, meanwhile, the large elbow and the elastic supporting piece are also arranged in a split mode, no fixed connection exists, the large elbow is formed and processed independently, the processing technology is simplified, and the manufacturing cost can be reduced. The split type setting through big return bend and flame section of thick bamboo subassembly, there is not fixed connection between the two, there is not fixed connection simultaneously between elastic support spare and the big return bend, only be surface contact with big return bend, be used for restricting big return bend axial motion, make and form the cooling clearance between big return bend and the flame section of thick bamboo subassembly, under the different operating mode of engine, the gas impact aerodynamic force is different, elastic support spare's holding power changes along with the compression volume change, two power formation dynamic balance, the not cooling clearance of equidimension appears thereupon, the cooling air that different clearance values got into is different, the cooling effect is different, the effect of independently adjusting the temperature of big return bend inner wall has been realized, the life of big return bend has been increased simultaneously.
The large elbow pipe of the invention is applied to a backflow combustion chamber, and the combustion chamber is provided with a combustion chamber inlet, a nozzle and the like which are conventional in the field.
Example 2
As shown in fig. 3 to 5, in the embodiment 1, the liner assembly includes a liner outer shell and a liner inner shell, and the large bent pipe is fitted to a wall surface of a tail portion of the liner outer shell and forms the cooling gap. The large bent pipe is partially attached to the wall surface of the tail part of the flame tube shell, and the shape of the attached part is consistent.
Example 3
As shown in fig. 3 to 5, the cooling gap ranges from 0 to 1.5mm based on embodiment 1 or 2. More preferably, the cooling gap may be 0mm, 0.2mm, 0.4mm, 0.6mm, 0.8mm, 1mm, 1.2mm, 1.3mm, 1.5 mm.
Example 4
4-5, on the basis of embodiment 1 or 2, the outer ring of the large elbow is provided with a small flange at the farthest end. The large elbow is partially attached to the wall surface of the tail part of the flame tube shell, the shape of the attached part is consistent, and a small flanging structure is arranged at the farthest end of the outer ring of the large elbow and used for efficiently introducing cooling airflow.
Example 5
As shown in fig. 6, on the basis of embodiment 1 or 2, a plurality of rows of small holes are arranged on one side of the large elbow close to the turbine guider component, and each row of small holes is distributed along the circumference of the large elbow.
Example 6
As shown in fig. 6, on the basis of the embodiment 5, the interval of the small holes on the wall surface of the large elbow is 4-8mm, and the jet angle of each small hole is 0-20 °.
Example 7
As shown in fig. 6, on the basis of example 6, the interval of the small holes in each row on the wall surface of the large elbow is 6mm (distance between the small holes in each row), and the jet angle of each small hole is 10 °. Preferably, three rows of small holes are formed, and the intervals of the small holes in each row are consistent along the wall surface, so that cooling air is introduced to cool the rear section of the large bent pipe and the turbine guide vane root.
Example 8
As shown in fig. 3, on the basis of embodiment 1, 3 to 6 elastic supporting members are provided.
Example 9
As shown in fig. 3, based on embodiment 1, the central axis of each elastic supporting element passes through the maximum curvature point of the large elbow, and the central axis of each elastic supporting element passes through the maximum curvature point of the large elbow, so that the large elbow can axially extend and contract, and the supporting force provided by the amount of extension and contraction is similar to or consistent with the aerodynamic force change of the high-temperature gas of the flame tube.
The large elbow pipe of the invention is applied to a backflow combustion chamber, and the combustion chamber is provided with a combustion chamber inlet, a nozzle and the like which are conventional in the field.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (9)
1. The utility model provides a big bent pipe structure of axial floating backward flow annular combustion chamber which characterized in that: including the diffuser subassembly, flame section of thick bamboo subassembly, turbine director subassembly, be provided with a plurality of elastic support spare on the diffuser subassembly, elastic support spare with be provided with big return bend between the flame section of thick bamboo subassembly, big return bend is fixed on the turbine director subassembly, big return bend with form cooling gap between the flame section of thick bamboo subassembly.
2. The large elbow structure of axial floating type backflow annular combustor according to claim 1, characterized in that: the flame tube assembly comprises a flame tube outer shell and a flame tube inner shell, and the large bent tube is matched with the wall surface of the tail part of the flame tube outer shell and forms the cooling gap.
3. The large elbow structure of axial floating type backflow annular combustor in claim 1 or 2, wherein: the cooling gap is in the range of 0-1.5 mm.
4. The large elbow structure of axial floating type backflow annular combustor in claim 1 or 2, wherein: the farthest end of the outer ring of the large elbow is provided with a small flanging.
5. The large elbow structure of axial floating type backflow annular combustor in claim 1 or 2, wherein: one side of the large elbow close to the turbine guider component is provided with a plurality of rows of small holes, and each row of small holes are distributed along the circumferential direction of the large elbow.
6. The large elbow structure of axial floating type backflow annular combustor according to claim 5, characterized in that: the small holes are arranged in three rows, the interval of each row of small holes on the wall surface of the large bent pipe is 4-8mm, and the jet angle of each small hole is 0-20 degrees.
7. The large elbow structure of axial floating type backflow annular combustor according to claim 6, characterized in that: the interval of each row of small holes on the wall surface of the large elbow is 6mm, and the jet angle of each small hole is 10 degrees.
8. The large elbow structure of axial floating type backflow annular combustor according to claim 1, characterized in that: the number of the elastic supporting pieces is 3-6.
9. The large elbow structure of axial floating type backflow annular combustor according to claim 1, characterized in that: the central axis of each elastic supporting element passes through the maximum point of the curvature of the large bent pipe.
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| CN202011282071.7A CN112377946B (en) | 2020-11-16 | 2020-11-16 | Large bent pipe structure of axial floating type backflow annular combustion chamber |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113175688B (en) * | 2021-04-15 | 2022-07-01 | 中国航发湖南动力机械研究所 | Double-wall large elbow |
| CN113137639B (en) * | 2021-04-25 | 2022-07-15 | 中国航发湖南动力机械研究所 | Turboprop engine backflow combustion chamber and turboprop engine |
| CN113154453B (en) * | 2021-05-06 | 2022-07-08 | 中国航发湖南动力机械研究所 | Tangential tilting type annular membrane diverging and cooling structure |
| CN113188154B (en) * | 2021-05-10 | 2022-10-28 | 中国航发湖南动力机械研究所 | Flame tube with cooling structure |
| CN113685844B (en) * | 2021-08-24 | 2022-11-25 | 中国航发湖南动力机械研究所 | Little return bend assembly fixture of combustion chamber full ring test spare |
| CN114413285B (en) * | 2022-01-29 | 2023-03-21 | 中国航发湖南动力机械研究所 | Big return bend seal structure |
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| CN101224381A (en) * | 2007-01-15 | 2008-07-23 | 吕延利 | Ethylene oxide exhaust gas processor |
| FR2920033B1 (en) * | 2007-08-13 | 2014-08-22 | Snecma | TURBOMACHINE WITH DIFFUSER |
| FR2952703B1 (en) * | 2009-11-19 | 2011-10-28 | Snecma | GUIDE TO AN IGNITION CANDLE IN A COMBUSTION CHAMBER OF A TURBOMACHINE |
| CN202203988U (en) * | 2011-07-21 | 2012-04-25 | 南京航空航天大学 | Backflow combustion chamber of shaft turbine |
| CN202203987U (en) * | 2011-07-21 | 2012-04-25 | 南京航空航天大学 | Backflow combustion chamber flame tube cooling structure of shaft turbine |
| KR101613096B1 (en) * | 2011-10-24 | 2016-04-20 | 제네럴 일렉트릭 테크놀러지 게엠베하 | Gas turbine |
| CN103292356B (en) * | 2013-06-19 | 2015-03-04 | 北京航空航天大学 | Beveling main combustion hole rotation aiding low-pollution backflow combustion chamber |
| US10422532B2 (en) * | 2013-08-01 | 2019-09-24 | United Technologies Corporation | Attachment scheme for a ceramic bulkhead panel |
| CN109469922B (en) * | 2018-11-09 | 2020-07-03 | 四川航天中天动力装备有限责任公司 | Miniature engine combustion chamber |
| CN109990309B (en) * | 2019-03-05 | 2020-05-15 | 南京航空航天大学 | Composite cooling structure of combustion chamber wall surface and turboshaft engine backflow combustion chamber |
| CN110671160B (en) * | 2019-11-20 | 2021-11-26 | 四川航天中天动力装备有限责任公司 | Rotor supporting and lubricating integrated structure of small turbine engine |
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