CN102788699A - Flame tube structure of thrust combustion chamber used for supercharger test - Google Patents
Flame tube structure of thrust combustion chamber used for supercharger test Download PDFInfo
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- CN102788699A CN102788699A CN2012102531148A CN201210253114A CN102788699A CN 102788699 A CN102788699 A CN 102788699A CN 2012102531148 A CN2012102531148 A CN 2012102531148A CN 201210253114 A CN201210253114 A CN 201210253114A CN 102788699 A CN102788699 A CN 102788699A
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- 238000012360 testing method Methods 0.000 title claims abstract description 20
- 238000002485 combustion reaction Methods 0.000 title abstract description 7
- 230000007704 transition Effects 0.000 claims abstract description 33
- 238000001816 cooling Methods 0.000 claims abstract description 24
- 238000010790 dilution Methods 0.000 claims description 18
- 239000012895 dilution Substances 0.000 claims description 18
- 239000011229 interlayer Substances 0.000 claims description 6
- 238000007789 sealing Methods 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 abstract description 2
- 229910052799 carbon Inorganic materials 0.000 abstract description 2
- 230000000694 effects Effects 0.000 abstract description 2
- 239000000446 fuel Substances 0.000 abstract description 2
- 230000015572 biosynthetic process Effects 0.000 abstract 1
- 230000008021 deposition Effects 0.000 abstract 1
- 230000017525 heat dissipation Effects 0.000 abstract 1
- 239000000203 mixture Substances 0.000 abstract 1
- 238000010304 firing Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 238000013021 overheating Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
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Abstract
The invention discloses a flame tube structure of a thrust combustion chamber used for a supercharger test. The flame tube structure includes two parts, namely a flame tube outer casing (1) and a flame tube inner casing (2), and further includes functional structures such as an air film cooling tank structure (3), a nozzle swirler and a second-stage diffuser, wherein a main combustion zone (11), a mixture zone (12), a cooling transition zone I (13) and a cooling transition zone II (14) all of the flame tube inner casing (2) are connected with one another through the novel air film cooling tank structure (3) which is a curve rectangular hole provided with diversion trenches, and the proportion of the air inlet passage sectional area in the sectional area of the film cooling tank structure is larger; the proportion of the air circulation sectional areas of the four zones in the sectional areas of corresponding positions of the flame tube outer casing (1) is larger; and the thickness of both the flame tube outer casing (1) and the flame tube inner casing (2) is 4.5 mm. According to the invention, the structural strength of the flame tube is increased, the formation of carbon deposition is reduced, the economic efficiency of the fuel is improved, the heat dissipation effect of the wall of the flame tube is improved, and the tolerance temperature of the combustion chamber and the flame tube as a whole is improved.
Description
Technical field
The invention belongs to test and use the thrust chamber technical field, be specifically related to a kind of supercharger test with thrust chamber burner inner liner structure.
Background technology
Thrust chamber is the important component part in the turbocharger test; The unreasonable power performance that will directly influence thrust chamber of burner inner liner design; And then the reliability of data in the serviceable life that influences the firing chamber and the test, restricted the research and development and the verification experimental verification demand of turbosupercharger.
Thrust chamber is used in present test, generally adopts retired aeroengine combustor buring chamber to convert, even the new thrust chamber of making, the burner inner liner structure of also generally continuing to use aeromotor processes.Because receive the restriction of difficulty of processing and structure, its burner inner liner generally adopts the thin-walled heat-resistance stainless steel to process.The burner inner liner barrel adopts the air film cooling, and cooling duct and by-pass ratio have been continued to use the proportion structure of aeromotor, in the conventional fail-test of turbosupercharger, comprise overtemperature, overspeed test, can form big vapour lock in this test.The burner inner liner of this structure very easily forms local overheating, causes the heated plastic distortion of burner inner liner, thereby causes the integral body of final firing chamber to scrap.
According to external domestic interrelated data report and patent inquiry, all have only the invention and the design of aeroengine combustor buring chamber burner inner liner structure both at home and abroad, but also do not report improvement design and the invention of overtesting with the thrust chamber burner inner liner.
Summary of the invention
The present invention be exactly for solve present test with thrust chamber because unreasonable structure causes burner inner liner very easily to form local overheating, cause the burner inner liner heated plastic to be out of shape, thus the problem that causes the integral body of final firing chamber to scrap.The objective of the invention is to test with thrust chamber burner inner liner structure and proposed a kind of supercharger in order to improve a kind of serviceable life and usable range of testing with the thrust chamber burner inner liner.
Technical scheme of the present invention:
A kind of supercharger test comprises burner inner liner shell, burner inner liner inner casing two parts with thrust chamber burner inner liner structure, also comprises functional structures such as air film cooling tank structure, nozzle cyclone and secondary diffuser;
Burner inner liner shell and burner inner liner inner casing, all with same central shaft symmetry, each section of burner inner liner shell radius is greater than each section of burner inner liner inner casing correspondence position radius;
The burner inner liner shell is the continuous spindle in surface, can be divided into 4 sections according to shape: first section and the 3rd section is cylindrical, and second section and the 4th section is conical (cross section can be isosceles triangle, also can be curvilinear triangle); The 3rd section radius is greater than first section; Second section is diffuser, and radius increases gradually; The 4th section radius reduces gradually;
Burner inner liner shell front end is with the sealing of flange disk, and nozzle is positioned at first section sidewall of burner inner liner shell; Burner inner liner shell front end rear end is with the sealing of flange annulus, and interior annulus is the outlet of burner inner liner inner casing cooled transition district II fixedly;
The burner inner liner inner casing is positioned at and also is the continuous spindle in surface; Can be divided into 5 sections according to position and function: first section diffuser is positioned at the correspondence position of second section diffuser of burner inner liner shell; The taper shape that also increases gradually for similar radius; In establish a fog rotating device; One end through a root portion be positioned on the central shaft, the conduit of part vertical curve is connected with nozzle, the other end is connected with second section primary zone through a littler conical structure, the nozzle cyclone promptly is made up of the two conduit of nozzle, fog rotating device and connection;
Second section primary zone, the 3rd section dilution zone, the 4th section cooled transition district I all are positioned at the cylindrical of the 3rd section on burner inner liner shell, and wherein primary zone and dilution zone are identical cylindrical of radius, and cooled transition district I is the taper shape that radius reduces gradually; The 5th section cooled transition district II is positioned at the correspondence position of the 4th section on burner inner liner shell, the taper shape that also reduces gradually for similar radius; The secondary diffuser promptly is made up of a littler conical structure in second section diffuser of burner inner liner shell, first section diffuser of burner inner liner inner casing, connection fog rotating device and primary zone;
Burner inner liner inner casing forward end seal is only established a conduit and is connected with nozzle on central shaft; Burner inner liner inner casing rear end is the outlet of cooled transition district II, is positioned at the annulus of flange annulus;
In the 3rd section on burner inner liner shell is cylindrical; And the interlayer between second section primary zone of burner inner liner inner casing and the 3rd section dilution zone; Be provided with several flange annulus and be fixedly connected burner inner liner shell and burner inner liner inner casing, form the rigid unitary of a no relative motion by the two; Outside the 3rd section on burner inner liner shell is cylindrical, also is provided with several and is used to reinforce and the fixing flange annulus of rigid unitary;
Lighting-up tuyere is positioned at second section primary zone one side of burner inner liner inner casing, is communicated with the interlayer of primary zone and burner inner liner shell, burner inner liner inner casing; The lighter seat that is used to light a fire is positioned at the 3rd section cylindrical and corresponding position of lighting-up tuyere of burner inner liner shell; Lighting-up tuyere, lighter seat all are positioned at the nozzle homonymy;
Second section primary zone of burner inner liner inner casing, the 3rd section dilution zone, the 4th section cooled transition district I, the 5th section cooled transition district II are not smooth seamless link between any two, but connect through a kind of novel air film cooling tank structure; The air film cooling tank structure is the curve oblong aperture structure of band diversion trench, and wherein to account for air film cooling tank structure sectional area ratio bigger for oblong aperture inlet channel sectional area;
The gas communication sectional area of second section primary zone of burner inner liner inner casing, the 3rd section dilution zone, the 4th section cooled transition district I, the 5th section cooled transition district II accounts for the large percentage of burner inner liner shell relevant position sectional area;
In addition, this supercharger test is with thrust chamber burner inner liner structure, and it is thick that burner inner liner shell and burner inner liner inner casing are 4.5 mm.
Beneficial effect of the present invention:
1. through changing traditional burner inner liner structure optimization and thin-walled into heavy wall, thereby increase the structural strength of burner inner liner, make whole its tolerable temperature that improves of burner inner liner;
2. through improving the air inlet ratio in burner inner liner primary zone, can make the firing chamber when exhaust resistance is big, avoid fuel-rich combustion, reduce the generation of carbon distribution;
3. through improving the air inlet ratio of dilution zone, can make the secondary combustion of flame combustion chamber more abundant, improve the economy of its fuel oil;
4. change the oblong aperture of band diversion trench into and increase circulation area through circular hole traditional burner inner liner cooling air film; Can make flame tube wall cooling air film guidance quality better; Length prolongs, and has effectively improved the radiating effect of flame tube wall, makes the tolerable temperature of firing chamber higher.
Description of drawings
Fig. 1 is a structural representation of the present invention;
Fig. 2 is the structural representation of novel air film cooling bath;
Each mark of accompanying drawing is represented respectively:
1-burner inner liner shell
2-burner inner liner inner casing
3-air film cooling tank structure
4-diffuser (part of burner inner liner shell)
5-flange disk
6-flange annulus
7-diffuser (part of burner inner liner inner casing)
The 8-fog rotating device
The 9-nozzle
10-conduit (part be positioned on the central shaft, part vertical curve)
The 11-primary zone
The 12-dilution zone
13-cooled transition district I
14-cooled transition district II
15-flange annulus
The 16-lighting-up tuyere
17-lighter seat.
Embodiment
A kind of supercharger test comprises burner inner liner shell, burner inner liner inner casing two parts with thrust chamber burner inner liner structure, also comprises functional structures such as air film cooling tank structure, nozzle cyclone and secondary diffuser;
Burner inner liner shell and burner inner liner inner casing, all with same central shaft symmetry, each section of burner inner liner shell radius is greater than each section of burner inner liner inner casing correspondence position radius;
The burner inner liner shell is the continuous spindle in surface, can be divided into 4 sections according to shape: first section and the 3rd section is cylindrical, and second section and the 4th section is conical (cross section can be isosceles triangle, also can be curvilinear triangle); The 3rd section radius is greater than first section; Second section is diffuser, and radius increases gradually; The 4th section radius reduces gradually;
Burner inner liner shell front end is with the sealing of flange disk, and nozzle is positioned at first section sidewall of burner inner liner shell; Burner inner liner shell front end rear end is with the sealing of flange annulus, and interior annulus is the outlet of burner inner liner inner casing cooled transition district II fixedly;
The burner inner liner inner casing is positioned at and also is the continuous spindle in surface; Can be divided into 5 sections according to position and function: first section diffuser is positioned at the correspondence position of second section diffuser of burner inner liner shell; The taper shape that also increases gradually for similar radius; In establish a fog rotating device; One end through a root portion be positioned on the central shaft, the conduit of part vertical curve is connected with nozzle, the other end is connected with second section primary zone through a littler conical structure, the nozzle cyclone promptly is made up of the two conduit of nozzle, fog rotating device and connection;
Second section primary zone, the 3rd section dilution zone, the 4th section cooled transition district I all are positioned at the cylindrical of the 3rd section on burner inner liner shell, and wherein primary zone and dilution zone are identical cylindrical of radius, and cooled transition district I is the taper shape that radius reduces gradually; The 5th section cooled transition district II is positioned at the correspondence position of the 4th section on burner inner liner shell, the taper shape that also reduces gradually for similar radius; The secondary diffuser promptly is made up of a littler conical structure in second section diffuser of burner inner liner shell, first section diffuser of burner inner liner inner casing, connection fog rotating device and primary zone;
Burner inner liner inner casing forward end seal is only established a conduit and is connected with nozzle on central shaft; Burner inner liner inner casing rear end is the outlet of cooled transition district II, is positioned at the annulus of flange annulus;
In the 3rd section on burner inner liner shell is cylindrical; And the interlayer between second section primary zone of burner inner liner inner casing and the 3rd section dilution zone; Be provided with several flange annulus and be fixedly connected burner inner liner shell and burner inner liner inner casing, form the rigid unitary of a no relative motion by the two; Outside the 3rd section on burner inner liner shell is cylindrical, also is provided with several and is used to reinforce and the fixing flange annulus of rigid unitary;
Lighting-up tuyere is positioned at second section primary zone one side of burner inner liner inner casing, is communicated with the interlayer of primary zone and burner inner liner shell, burner inner liner inner casing; The lighter seat that is used to light a fire is positioned at the 3rd section cylindrical and corresponding position of lighting-up tuyere of burner inner liner shell; Lighting-up tuyere, lighter seat all are positioned at the nozzle homonymy;
Second section primary zone of burner inner liner inner casing, the 3rd section dilution zone, the 4th section cooled transition district I, the 5th section cooled transition district II are not smooth seamless link between any two, but connect through a kind of novel air film cooling tank structure; The air film cooling tank structure is the curve oblong aperture structure of band diversion trench, and wherein to account for air film cooling tank structure sectional area ratio bigger for oblong aperture inlet channel sectional area;
The gas communication sectional area of second section primary zone of burner inner liner inner casing, the 3rd section dilution zone, the 4th section cooled transition district I, the 5th section cooled transition district II accounts for the large percentage of burner inner liner shell relevant position sectional area;
This supercharger test is with thrust chamber burner inner liner structure, and burner inner liner shell and burner inner liner inner casing change 4.5 mm into by common way 0.75 mm～1 mm; Primary zone, dilution zone, cooled transition district I, cooled transition district II have increased the ratio that the gas communication sectional area accounts for burner inner liner shell relevant position sectional area in different proportion; The air film cooling tank structure has increased oblong aperture inlet channel sectional area ratio.
Claims (2)
1. a supercharger test comprises burner inner liner shell (1), burner inner liner inner casing (2) two parts with thrust chamber burner inner liner structure, it is characterized in that, also comprises functional structures such as air film cooling tank structure (3), nozzle cyclone and secondary diffuser; Burner inner liner shell (1) and burner inner liner inner casing (2), all with same central shaft symmetry, burner inner liner shell (1) each section radius is greater than burner inner liner inner casing (2) each section of correspondence position radius; Burner inner liner shell (1) is the continuous spindle in surface, can be divided into 4 sections according to shape: first section and the 3rd section is cylindrical, and second section and the 4th section is conical (cross section can be isosceles triangle, also can be curvilinear triangle); The 3rd section radius is greater than first section; Second section is diffuser (4), and radius increases gradually; The 4th section radius reduces gradually; Burner inner liner shell (1) front end is with flange disk (5) sealing, and nozzle (9) is positioned at (1) first section sidewall of burner inner liner shell; Burner inner liner shell (1) front end rear end is with flange annulus (6) sealing, and interior annulus is the outlet of burner inner liner inner casing (2) cooled transition district II (14) fixedly;
Burner inner liner inner casing (2) is the continuous spindle in surface; Can be divided into 5 sections according to position and function: first section diffuser (7) is positioned at the correspondence position of (1) second section diffuser of burner inner liner shell (4); The taper shape that increases gradually for similar radius; In establish a fog rotating device (8); One end through a root portion be positioned on the central shaft, the conduit (10) of part vertical curve is connected with nozzle (9), the other end is connected with second section primary zone (11) through a littler conical structure, the nozzle cyclone promptly is made up of nozzle (9), fog rotating device (8) and the conduit (10) that is communicated with the two; Second section primary zone (11), the 3rd section dilution zone (12), the 4th section cooled transition district I (13); All be positioned at the cylindrical of the 3rd section on burner inner liner shell (1); Wherein primary zone (11) and dilution zone (12) are identical cylindrical of radius, the taper shape that cooled transition district I (13) reduces for radius gradually; The 5th section cooled transition district II (14) is positioned at the correspondence position of the 4th section on burner inner liner shell (1), the taper shape that also reduces gradually for similar radius; The secondary diffuser promptly is made up of (1) second section diffuser of burner inner liner shell (4), (2) first sections diffusers of burner inner liner inner casing (7), a littler conical structure being communicated with fog rotating device (8) and primary zone (11); Burner inner liner inner casing (2) forward end seal is only established a conduit (10) and is connected with nozzle (9) on central shaft; Burner inner liner inner casing (2) rear end is the outlet of cooled transition district II (14), is positioned at the annulus of flange annulus (6); In the 3rd section on burner inner liner shell (1) is cylindrical; And the interlayer between (2) second sections primary zones of burner inner liner inner casing (11) and the 3rd section dilution zone (12); Be provided with several flange annulus and be fixedly connected burner inner liner shell (1) and burner inner liner inner casing (2), form the rigid unitary of a no relative motion by the two; Outside the 3rd section on burner inner liner shell (1) is cylindrical, also is provided with several and is used to reinforce and the fixing flange annulus (15) of rigid unitary; Lighting-up tuyere (16) is positioned at (2) second sections primary zone (11) one sides of burner inner liner inner casing, is communicated with the interlayer of primary zone (11) and burner inner liner shell (1), burner inner liner inner casing (2); The lighter seat (17) that is used to light a fire is positioned at the 3rd section cylindrical and corresponding position of lighting-up tuyere (16) of burner inner liner shell (1); Lighting-up tuyere (16), lighter seat (17) all are positioned at nozzle (9) homonymy; (2) second sections primary zones of burner inner liner inner casing (11), the 3rd section dilution zone (12), the 4th section cooled transition district I (13), the 5th section cooled transition district II (14) are between any two; Be not smooth seamless link, but connect through a kind of novel air film cooling tank structure (3); Said air film cooling tank structure (3) is the curve oblong aperture structure of band diversion trench, and wherein to account for air film cooling tank structure (3) sectional area ratio big for oblong aperture inlet channel sectional area; The gas communication sectional area of (2) second sections primary zones of burner inner liner inner casing (11), the 3rd section dilution zone (12), the 4th section cooled transition district I (13), the 5th section cooled transition district II (14), the ratio that accounts for burner inner liner shell (1) relevant position sectional area is big.
2. a kind of according to claim 1 supercharger test is characterized in that with thrust chamber burner inner liner structure burner inner liner shell (1) and burner inner liner inner casing (2) thickness are 4.5 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102531148A CN102788699A (en) | 2012-07-23 | 2012-07-23 | Flame tube structure of thrust combustion chamber used for supercharger test |
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| CN2012102531148A CN102788699A (en) | 2012-07-23 | 2012-07-23 | Flame tube structure of thrust combustion chamber used for supercharger test |
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| CN102788699A true CN102788699A (en) | 2012-11-21 |
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| CN2012102531148A Pending CN102788699A (en) | 2012-07-23 | 2012-07-23 | Flame tube structure of thrust combustion chamber used for supercharger test |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103592132A (en) * | 2013-10-31 | 2014-02-19 | 哈尔滨汽轮机厂有限责任公司 | Pressurization visual combustion test device of combustor of gas turbine |
| CN104864416A (en) * | 2015-04-22 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Connecting structure of combustion liner and transition section |
| CN105716121A (en) * | 2014-12-04 | 2016-06-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Novel flame tube structure |
| CN107327831A (en) * | 2017-07-18 | 2017-11-07 | 贵州大学 | A kind of burning barrel structure of shale gas well gas testing |
| CN107576502A (en) * | 2017-08-10 | 2018-01-12 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustion chamber with mixing section |
| CN108181955A (en) * | 2017-12-08 | 2018-06-19 | 中国北方发动机研究所(天津) | A kind of control method of the turbocharger test platform combustion chamber with mixing section |
| CN108224472A (en) * | 2017-12-08 | 2018-06-29 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustor exit temperature regulating mechanism |
| CN108562440A (en) * | 2017-12-26 | 2018-09-21 | 南京航空航天大学 | The combustor test device and its test method of air mass flow zonal control |
| CN109374308A (en) * | 2018-09-20 | 2019-02-22 | 中国民航大学 | An aero-engine combustion chamber simulation test bench with steady-state temperature field |
| CN110763474A (en) * | 2018-07-25 | 2020-02-07 | 中国航发商用航空发动机有限责任公司 | Combustion chamber test device |
| CN115614779A (en) * | 2022-09-08 | 2023-01-17 | 中国航发湖南动力机械研究所 | Flame tube and self-adaptive cooling air quantity adjusting method thereof |
| CN115949972A (en) * | 2023-01-29 | 2023-04-11 | 中国航发沈阳发动机研究所 | Flame tube wall cooling strengthening design method |
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Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103592132B (en) * | 2013-10-31 | 2016-01-13 | 哈尔滨汽轮机厂有限责任公司 | Gas-turbine combustion chamber pressurizes visual corrosion chamber |
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| CN104864416A (en) * | 2015-04-22 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Connecting structure of combustion liner and transition section |
| CN107327831A (en) * | 2017-07-18 | 2017-11-07 | 贵州大学 | A kind of burning barrel structure of shale gas well gas testing |
| CN107576502A (en) * | 2017-08-10 | 2018-01-12 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustion chamber with mixing section |
| CN107576502B (en) * | 2017-08-10 | 2019-11-12 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustion chamber with mixing section |
| CN108224472B (en) * | 2017-12-08 | 2020-04-10 | 中国北方发动机研究所(天津) | Turbo charger test bench combustion chamber export temperature adjustment mechanism |
| CN108181955A (en) * | 2017-12-08 | 2018-06-19 | 中国北方发动机研究所(天津) | A kind of control method of the turbocharger test platform combustion chamber with mixing section |
| CN108224472A (en) * | 2017-12-08 | 2018-06-29 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustor exit temperature regulating mechanism |
| CN108181955B (en) * | 2017-12-08 | 2020-06-19 | 中国北方发动机研究所(天津) | Control method for turbocharger test bed combustion chamber with mixing section |
| CN108562440B (en) * | 2017-12-26 | 2020-07-07 | 南京航空航天大学 | Combustion chamber test device and test method for zone control of air flow |
| CN108562440A (en) * | 2017-12-26 | 2018-09-21 | 南京航空航天大学 | The combustor test device and its test method of air mass flow zonal control |
| CN110763474A (en) * | 2018-07-25 | 2020-02-07 | 中国航发商用航空发动机有限责任公司 | Combustion chamber test device |
| CN110763474B (en) * | 2018-07-25 | 2021-08-13 | 中国航发商用航空发动机有限责任公司 | Combustion chamber test device |
| CN109374308A (en) * | 2018-09-20 | 2019-02-22 | 中国民航大学 | An aero-engine combustion chamber simulation test bench with steady-state temperature field |
| CN115614779A (en) * | 2022-09-08 | 2023-01-17 | 中国航发湖南动力机械研究所 | Flame tube and self-adaptive cooling air quantity adjusting method thereof |
| CN115949972A (en) * | 2023-01-29 | 2023-04-11 | 中国航发沈阳发动机研究所 | Flame tube wall cooling strengthening design method |
| CN115949972B (en) * | 2023-01-29 | 2024-09-06 | 中国航发沈阳发动机研究所 | Flame tube wall cooling strengthening design method |
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Application publication date: 20121121 |