CN204100296U - A kind of aeroengine combustor buring room adopting variable cross-section step type effusion wall cooling structure - Google Patents
A kind of aeroengine combustor buring room adopting variable cross-section step type effusion wall cooling structure Download PDFInfo
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- CN204100296U CN204100296U CN201420486337.3U CN201420486337U CN204100296U CN 204100296 U CN204100296 U CN 204100296U CN 201420486337 U CN201420486337 U CN 201420486337U CN 204100296 U CN204100296 U CN 204100296U
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- 238000001816 cooling Methods 0.000 title claims abstract description 58
- 238000002485 combustion reaction Methods 0.000 claims abstract description 32
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- 238000011144 upstream manufacturing Methods 0.000 claims description 33
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- 230000000694 effects Effects 0.000 description 9
- 238000005516 engineering process Methods 0.000 description 7
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- 238000013461 design Methods 0.000 description 5
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- 238000004378 air conditioning Methods 0.000 description 1
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- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 239000012809 cooling fluid Substances 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
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- 238000010790 dilution Methods 0.000 description 1
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- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
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Abstract
The utility model discloses a kind of aeroengine combustor buring room adopting variable cross-section step type effusion wall cooling structure.The utility model comprises combustion box, calotte, cyclone, linkage section, splash pan, burner inner liner internal ring wall, burner inner liner external annulus, its technical scheme is that burner inner liner internal ring wall and external annulus all adopt straight wall, and internal ring wall and external annulus arrange variable cross-section stepped ramp type effusion wall.Adopt the combustion chamber of above-mentioned cooling structure efficient hardening wall internal impact to cool, effectively heat insulation and cooling is formed to the wall of aeroengine combustor buring room, reduces cold gas consumption simultaneously, increase and organize gas consumption, improve combustion chamber temperature rise.The utility model structure is simple, is easy to realize, and has good engineer applied and is worth.
Description
Technical field
The utility model relates to aero-engine field, in particular a kind of aeroengine combustor buring room adopting variable cross-section step type effusion wall cooling structure.
Background technology
Along with the continuous lifting of aero-engine performance index, also day by day harsh to the requirement of burner inner liner performance, current burner inner liner cooling is faced with two large difficult points: the continuous increase that () requires along with combustor exit temperature, under the condition that oil-gas ratio is certain, combustion air amount is organized to increase gradually.In addition, in order to ensure that the Temperature Distribution of combustor exit meets the requirement of design, suitable dilution air amount is again not diminishbb, and in head air inflow one timing, this just causes the air capacity that can be used for cooling to reduce.As high temperature rise combustor still adopts traditional air film cooling technology, and cooling air volume remains unchanged or reduce, and Calculating Wall Temperature of Flame Tube will exceed the acceptability limit of the high temperature heat-resisting material adopted at present.(2) the total pressure ratio of aero-engine progressively improves, the total pressure ratio of high thrust-weight ratio aero-engine will reach 35 ~ 40, even higher, at this moment the air themperature of blower outlet will reach about 1000K, that is, the combustion chamber inlet air temperature of cooling flame tube wall surface will improve with aero-engine pressure ratio and progressively rise, and therefore, combustion chamber inlet air is declining gradually as the cooling capacity of cooling agent.
How under less cooling air volume and higher temperature, reliable cooling combustion room burner inner liner is effectively problem extremely important and in the urgent need to address, and this problem must solve by taking the technology of novelty.
At present, the advanced cooling technology that external advanced aero engine adopts mainly contains: Inclined multihole wass cooling technology, compared with the gaseous film control of routine, is carrying out the wall cooled being outputed a large amount of very intensive discrete air film hole, air film hole is much intensive, and aperture is also much smaller.Cold airflow is injected with certain incidence angle and is flow through in the hot main flow of wall from this some holes; main flow and wall are isolated; play the effect of protection wall; its cooling effectiveness is up to 90%; can make that cooling-air consumption reduces 40%, combustor exit temperature field is more even; its air film that can be formed in hot side evenly, more complete to the covering of wall, thus improve cooling effect significantly.
Impact and add the Compound cooling mode that effusion wall cooling is a kind of advanced person, its structure for add last layer impact opening wall outside Inclined multihole wass.Main feature is that cooling-air first carries out impinging cooling to porous wall cold side, then carries out heat convection in access aperture, forms protection air film, become and repeatedly cool, the potentiality of cooling-air are fully applied after flowing out aperture at hot side wall surface.Its most significant heat exchange characteristic there is strong impingement heat transfer at the cold side of Inclined multihole wass.Impact adds the effusion wall type of cooling and then further cooling tolerance is reduced to 25%.
Have employed effusion wall cooling respectively in the advanced engine of external many moneys and impact effusion wall cooling structure, GE90 and military F414 engine all have employed this burner inner liner processed by GTD222 alloy, shorten the length of combustion chamber, in the engine that thrust level is suitable, the length of GE90 engine chamber is the shortest.
The PW4000 that Pu Hui company produces, PW6000 engine then successfully applies and impacts effusion wall cooling structure, all achieve significant effect, this cooling structure generally adopts floating wall structure.Early 1990s, floating wall burner inner liner is applied on V2500 engine by PW company, has been applied to again afterwards on the civilian engine such as F119 ordnance engine and PW4000, PW6000, PW8000 series.Typical floating pad structure is as the floating pad structure of V2500 engine chamber, and its head adopts the splashing board effusion wall cooling structure that floats.Add thermal barrier coating Compound cooling mode can meet tile fragment cooling needs by impact, convection current, air film.The TALON series combustion chamber of PW also adopts the cooling scheme impacting effusion wall and add floating wall, and further enhancing cooling performance, obviously improved the working life of combustion chamber.
Impact adds the effusion wall type of cooling and has higher cooling effectiveness, and consumption cooling tolerance is less, but it adopts floating wall structure, make complex structure, difficulty of processing is improved further, in addition, floating wall structure is double-decker, and weight improves, and causes adverse effect for engine weight.How to be optimized design to impact effusion wall structure, to reach the weight reducing combustion chamber while strengthening cooling, be one of urgent problem in Combustion chamber design.
Utility model content
Technical problem to be solved in the utility model is for the deficiencies in the prior art, provides a kind of aeroengine combustor buring room adopting variable cross-section step type effusion wall cooling structure.
The technical solution of the utility model is as follows:
A kind of aeroengine combustor buring room adopting variable cross-section step type effusion wall cooling structure, comprise the first combustion box 1, second combustion box 2, first calotte 3, second calotte 4, burner inner liner external annulus 8, burner inner liner internal ring wall 9, burner inner liner 18, it is characterized in that:
1) burner inner liner 18 front end adopts axial location, and burner inner liner 18 rear end coordinates with the first combustion box 1 and the second combustion box 2;
2) burner inner liner 18 comprises burner inner liner external annulus 8 and burner inner liner internal ring wall 9, and linkage section 7 connects burner inner liner external annulus 8 and burner inner liner internal ring wall 9, and burner inner liner external annulus 8 and burner inner liner internal ring wall 9 are fixedly mounted on linkage section 7;
3) the first calotte 3 and the second calotte 4 are fixedly mounted on burner inner liner external annulus 8, burner inner liner internal ring wall 9 respectively;
4) linkage section 7 comprises cyclone 5 and splash pan 6, and cyclone 5 and splash pan 6 are fixed on linkage section 7, and cyclone 5 is fixed on the first calotte 3 and the second calotte 4 side, and splash pan 6 is arranged on burner inner liner internal ring wall 9 and burner inner liner external annulus 8 side;
5) on burner inner liner external annulus 8 and burner inner liner internal ring wall 9, offer the variable cross-section stepped ramp type inclined hole of a large amount of dense distribution, in its hole, sectional area is along flowing to as variable area distribution;
6) on burner inner liner external annulus 8, open the first primary holes 10, first blending hole 12, the 3rd blending hole 14 and the first effusion wall 16; And the diameter of the first primary holes 10 is greater than the first blending hole 12 and the 3rd blending hole 14; The pass of the first primary holes 10, first blending hole 12 and the 3rd blending hole 14 is straight hole; First effusion wall 16 is variable cross-section stepped hole, and the first effusion wall 16 arrangement mode is fork row;
7) on burner inner liner internal ring wall 9, open the second primary holes 11, second blending hole 13, the 4th blending hole 15 and the second effusion wall 17; And the diameter of the second primary holes 11 is greater than the second blending hole 13 and the 4th blending hole 15; The pass of the second primary holes 11, second blending hole 13 and the 4th blending hole 15 is straight hole; Second effusion wall 17 pass is variable cross-section stepped hole, and the second effusion wall 17 arrangement mode is fork row;
8) effusion wall is variable cross-section stepped ramp type, comprise upstream orifice 19 and downstream aperture 20, be uiform section hole, upstream orifice 19 is two concentration ellipses with the interface of downstream aperture 20, all parallel with wall, upstream orifice 19 overlaps with the center line of downstream aperture 20, all become α angle with burner inner liner 18 wall, upstream orifice aperture is D1, hole depth is H1, downstream aperture aperture is D2, hole depth is H2, same row is adjacent, and two inclined hole spacing are P, the adjacent two inclined hole array pitch of same row are S, first row inclined hole distance wall front end distance is L1, last row's inclined hole distance wall rear end distance is L2, inclined hole distance primary holes radial distance R1, distance blending hole radial distance R2.
Described upstream orifice aperture D1 is greater than 1.1 times of downstream aperture aperture D2, is less than 1.4 times of downstream aperture aperture D2.
The adjacent two inclined hole spacing P of described same row are not more than 5 times of downstream aperture aperture D2, and the adjacent two inclined hole array pitch S of same row are not more than 26 times of downstream aperture aperture D2.
Described upstream orifice hole depth H1 equals downstream aperture hole depth H2.
Described inclined hole distance primary holes radial distance R1 is not less than the upstream orifice aperture D1 of 2.6 times, is not more than the upstream orifice aperture D1 of 4 times; Inclined hole distance blending hole radial distance R2 is not less than the upstream orifice aperture D1 of 3 times, is not more than the upstream orifice aperture D1 of 5 times.
Described first row inclined hole distance wall front end distance L1 is not more than 3 times of upstream orifice aperture D1, and last row's inclined hole distance wall rear end distance L2 is not more than 5 times of upstream orifice aperture D1.
The utility model reaches purpose of design based on following thinking: combustion chamber is as one of engine core parts, its temperature rise size directly affects motor power size, when temperature increase requirement significantly improves, how reasonable distribution tissue burning gas consumption and cooling tolerance, ensure that wall controls in material require temperature range, cooling technology develop into one of key technology.Variable cross-section stepped ramp type effusion wall is a kind of NEW TYPE OF COMPOSITE cooling structure, its upstream and downstream hole depth, aperture, pitch of holes, and array pitch distribution in hole all has considerable influence to its cooling effect.Upstream and downstream aperture is than larger, and cooling effect is better, but flow losses also can become large simultaneously; Pitch of holes, hole array pitch are less, and cooling effect is better, but consume cooling air conditioning quantity also along with increase.In order to make combustion chamber have higher temperature rise, consume less cold gas, ensure that wall surface temperature is within the scope of material allowable temperature, rational cooling structure parameter designing is crucial simultaneously.
Design feature of the present utility model is, at the step inclined hole of the inner Formation cross-section sudden change of Inclined multihole wass, fluid is in inclined hole internal flow process, the platform at step place is formed and impacts, thus improve the impingement heat transfer amount of wall, the heat exchange of strengthening cooling fluid, fully excavates the cooling potential of refrigerating gas.
Impingement wall and Inclined multihole wass are merged by the utility model, impinging cooling are incorporated into effusion wall inside, form a kind of variable cross-section stepped ramp type effusion wall cooling structure, play effective cooling effect, additionally reduce cold gas consumption.Make tissue burning gas consumption increase further, improve combustion chamber temperature rise.
Accompanying drawing explanation
Fig. 1 is aeroengine combustor buring room schematic diagram.
Fig. 2 is aeroengine combustor buring room front view.
Fig. 3 is combustion chamber wall surface effusion wall arrangement schematic diagram.
Fig. 4 is the structural representation of variable cross-section stepped hole.
Fig. 5 is variable cross-section stepped hole schematic diagram.
In figure, 1 first combustion box, 2 second combustion boxes, 3 first calottes, 4 second calottes, 5 cyclones, 6 splash pans, 7 linkage sections, 8 burner inner liner external annulus, 9 burner inner liner internal ring walls, 10 first primary holes, 11 second primary holes, 12 first blending hole, 13 second blending hole, 14 the 3rd blending hole, 15 the 4th blending hole, 16 first effusion wall, 17 second effusion wall, 18 burner inner liners, 19 upstream orifice, 20 downstream apertures.
Detailed description of the invention
Below in conjunction with specific embodiment, the utility model is described in detail.
Embodiment
A kind of aeroengine combustor buring room adopting variable cross-section step type effusion wall cooling structure, as shown in Figure 1 and Figure 2, comprise the first combustion box 1, second combustion box 2, first calotte 3, second calotte 4, burner inner liner external annulus 8, burner inner liner internal ring wall 9, burner inner liner 18, its technical scheme is:
1) burner inner liner 18 front end adopts axial location, and burner inner liner 18 rear end coordinates with the first combustion box 1 and the second combustion box 2, adopts radial and circumference location, allows axial Free Thermal to expand;
2) burner inner liner 18 comprises burner inner liner external annulus 8 and burner inner liner internal ring wall 9, and linkage section 7 connects burner inner liner external annulus 8 and burner inner liner internal ring wall 9, and burner inner liner external annulus 8 and burner inner liner internal ring wall 9 are fixedly mounted on linkage section 7;
3) the first calotte 3 and the second calotte 4 are fixedly mounted on burner inner liner external annulus 8, burner inner liner internal ring wall 9 respectively;
4) linkage section 7 comprises cyclone 5 and splash pan 6, and cyclone 5 and splash pan 6 are fixed on linkage section 7, and cyclone 5 is fixed on the first calotte 3 and the second calotte 4 side, and splash pan 6 is arranged on burner inner liner internal ring wall 9 and burner inner liner external annulus 8 side;
5) on burner inner liner external annulus 8 and burner inner liner internal ring wall 9, offer the variable cross-section stepped ramp type inclined hole of a large amount of dense distribution, in its hole, sectional area is along flowing to as variable area distribution;
6) on burner inner liner external annulus 8, open the first primary holes 10, first blending hole 12, the 3rd blending hole 14 and the first effusion wall 16; And the diameter of the first primary holes 10 is greater than the first blending hole 12 and the 3rd blending hole 14; The pass of the first primary holes 10, first blending hole 12 and the 3rd blending hole 14 is straight hole; First effusion wall 16 is variable cross-section stepped hole, and the first effusion wall 16 arrangement mode is fork row;
7) on burner inner liner internal ring wall 9, open the second primary holes 11, second blending hole 13, the 4th blending hole 15 and the second effusion wall 17; And the diameter of the second primary holes 11 is greater than the second blending hole 13 and the 4th blending hole 15; The pass of the second primary holes 11, second blending hole 13 and the 4th blending hole 15 is straight hole; Second effusion wall 17 pass is variable cross-section stepped hole, and the second effusion wall 17 arrangement mode is fork row.
As Fig. 3, Fig. 4, shown in Fig. 5, effusion wall is variable cross-section stepped ramp type, comprise upstream orifice 19 and downstream aperture 20, be uiform section hole, upstream orifice 19 is two concentration ellipses with the interface of downstream aperture 20, all parallel with wall, upstream orifice 19 overlaps with the center line of downstream aperture 20, all become α angle with burner inner liner 18 wall, upstream orifice aperture is D1, hole depth is H1, downstream aperture aperture is D2, hole depth is H2, same row is adjacent, and two inclined hole spacing are P, the adjacent two inclined hole array pitch of same row are S, first row inclined hole distance wall front end distance is L1, last row's inclined hole distance wall rear end distance is L2, inclined hole distance primary holes radial distance R1, distance blending hole radial distance R2.
Wherein, downstream aperture aperture D2=0.3 ~ 0.7mm, pitch of holes P=1.025 ~ 1.685mm, hole array pitch S=1.8 ~ 8.06mm, (, than P/D2=2 ~ 5, hole array pitch is than S/D2=2 ~ 26 for pitch of holes), inclination alpha=20 ~ 120 °, hole.
Research shows, for variable cross-section step Inclined multihole wass, its heat transfer is made up of three parts, i.e. (1) cold side convection current cooling, (2) internal surface of hole convection current cools, (3) hot side gaseous film control.Although the span of P/D2 and S/D2 is suitable with conventional gaseous film control, but because the absolute value of D2, P and S is very little, under the condition of identical percent opening (ratio of perforated area and perforate antetheca area), the contact area of cold flow and Gu Bi increases, in the hole of upstream orifice, heat convection area is greater than downstream aperture especially, both are added and the ratio in hole shared by heat convection are significantly improved, reach about 45%, by regulating aperture, upstream and downstream hole ratio, the quantity of heat convection of wall inside can be improved further, reduce wall internal temperature gradient.In addition, the air film that this cooling structure is formed in hot side evenly, more complete to the covering of wall, thus improve cooling effect significantly, cooling effectiveness reaches more than 0.9.Its cooling gas consumption lower than conventional gaseous film control by 26%, combustion chamber external annulus hot side temperature controls at below 1150K, internal ring wall hot side temperature at below 1240K, all within the long-term allowable temperature scope of material.Under identical oil-gas ratio, compare conventional skill and add ring cooling combustion room, its outlet temperature can improve about 80K, for the wall cooling structure of high temperature rise combustor provides effective way.
Should be understood that, for those of ordinary skills, can be improved according to the above description or convert, and all these improve and convert the protection domain that all should belong to the utility model claims.
Claims (6)
1. one kind adopts the aeroengine combustor buring room of variable cross-section step type effusion wall cooling structure, comprise the first combustion box (1), the second combustion box (2), the first calotte (3), the second calotte (4), burner inner liner external annulus (8), burner inner liner internal ring wall (9), burner inner liner (18), it is characterized in that:
1) burner inner liner (18) front end adopts axial location, and burner inner liner (18) rear end coordinates with the first combustion box (1) and the second combustion box (2);
2) burner inner liner (18) comprises burner inner liner external annulus (8) and burner inner liner internal ring wall (9), linkage section (7) connects burner inner liner external annulus (8) and burner inner liner internal ring wall (9), and burner inner liner external annulus (8) and burner inner liner internal ring wall (9) are fixedly mounted on linkage section (7);
3) the first calotte (3) and the second calotte (4) are fixedly mounted on burner inner liner external annulus (8), burner inner liner internal ring wall (9) respectively;
4) linkage section (7) comprises cyclone (5) and splash pan (6), cyclone (5) and splash pan (6) are fixed on linkage section (7), and cyclone (5) is fixed on the first calotte (3) and the second calotte (4) side, splash pan (6) is arranged on burner inner liner internal ring wall (9) and burner inner liner external annulus (8) side;
5) on burner inner liner external annulus (8) and burner inner liner internal ring wall (9), offer the variable cross-section stepped ramp type inclined hole of a large amount of dense distribution, in its hole, sectional area is along flowing to as variable area distribution;
6) on burner inner liner external annulus (8), open the first primary holes (10), the first blending hole (12), the 3rd blending hole (14) and the first effusion wall (16); And the diameter of the first primary holes (10) is greater than the first blending hole (12) and the 3rd blending hole (14); The pass of the first primary holes (10), the first blending hole (12) and the 3rd blending hole (14) is straight hole; First effusion wall (16) is variable cross-section stepped hole, and the first effusion wall (16) arrangement mode is fork row;
7) on burner inner liner internal ring wall (9), open the second primary holes (11), the second blending hole (13), the 4th blending hole (15) and the second effusion wall (17); And the diameter of the second primary holes (11) is greater than the second blending hole (13) and the 4th blending hole (15); The pass of the second primary holes (11), the second blending hole (13) and the 4th blending hole (15) is straight hole; Second effusion wall (17) pass is variable cross-section stepped hole, and the second effusion wall (17) arrangement mode is fork row;
8) effusion wall is variable cross-section stepped ramp type, comprise upstream orifice (19) and downstream aperture (20), be uiform section hole, upstream orifice (19) is two concentration ellipses with the interface of downstream aperture (20), all parallel with wall, upstream orifice (19) overlaps with the center line of downstream aperture (20), all become α angle with burner inner liner (18) wall, upstream orifice aperture is D1, hole depth is H1, downstream aperture aperture is D2, hole depth is H2, same row is adjacent, and two inclined hole spacing are P, the adjacent two inclined hole array pitch of same row are S, first row inclined hole distance wall front end distance is L1, last row's inclined hole distance wall rear end distance is L2, inclined hole distance primary holes radial distance R1, distance blending hole radial distance R2.
2. aeroengine combustor buring room according to claim 1, is characterized in that, upstream orifice aperture D1 is greater than 1.1 times of downstream aperture aperture D2, is less than 1.4 times of downstream aperture aperture D2.
3. aeroengine combustor buring room according to claim 1, is characterized in that, the adjacent two inclined hole spacing P of same row are not more than 5 times of downstream aperture aperture D2, and the adjacent two inclined hole array pitch S of same row are not more than 26 times of downstream aperture aperture D2.
4. aeroengine combustor buring room according to claim 1, is characterized in that, upstream orifice hole depth H1 equals downstream aperture hole depth H2.
5. aeroengine combustor buring room according to claim 1, is characterized in that, inclined hole distance primary holes radial distance R1 is not less than the upstream orifice aperture D1 of 2.6 times, is not more than the upstream orifice aperture D1 of 4 times; Inclined hole distance blending hole radial distance R2 is not less than the upstream orifice aperture D1 of 3 times, is not more than the upstream orifice aperture D1 of 5 times.
6. aeroengine combustor buring room according to claim 1, is characterized in that, first row inclined hole distance wall front end distance L1 is not more than 3 times of upstream orifice aperture D1, and last row's inclined hole distance wall rear end distance L2 is not more than 5 times of upstream orifice aperture D1.
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| CN201420486337.3U CN204100296U (en) | 2014-08-26 | 2014-08-26 | A kind of aeroengine combustor buring room adopting variable cross-section step type effusion wall cooling structure |
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| CN201420486337.3U CN204100296U (en) | 2014-08-26 | 2014-08-26 | A kind of aeroengine combustor buring room adopting variable cross-section step type effusion wall cooling structure |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104197373A (en) * | 2014-08-26 | 2014-12-10 | 南京航空航天大学 | Aero-engine combustor with variable-cross-section step-shaped multiple-inclined-hole cooling structure used |
| CN108036633A (en) * | 2017-12-09 | 2018-05-15 | 北京中飞华正检测技术服务有限公司 | A kind of swirling eddy generating means of electric drying oven with forced convection |
| CN109340826A (en) * | 2018-09-25 | 2019-02-15 | 西北工业大学 | A kind of flame combustion chamber tube wall surface two-layer compound cooling structure |
| CN111486477A (en) * | 2020-04-07 | 2020-08-04 | 南京航空航天大学 | Mixing hole adjusting system and method for adjusting outlet temperature distribution of combustion chamber |
| CN114526497A (en) * | 2022-01-07 | 2022-05-24 | 清华大学 | Double-necking combined spiral-flow type center-grading high-temperature-rise combustion chamber |
| CN115727354A (en) * | 2022-11-11 | 2023-03-03 | 中国航发哈尔滨东安发动机有限公司 | Turbofan engine flame tube structure for aircraft |
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2014
- 2014-08-26 CN CN201420486337.3U patent/CN204100296U/en not_active Withdrawn - After Issue
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104197373A (en) * | 2014-08-26 | 2014-12-10 | 南京航空航天大学 | Aero-engine combustor with variable-cross-section step-shaped multiple-inclined-hole cooling structure used |
| CN104197373B (en) * | 2014-08-26 | 2016-04-06 | 南京航空航天大学 | A kind of aeroengine combustor buring room adopting variable cross-section step type effusion wall cooling structure |
| CN108036633A (en) * | 2017-12-09 | 2018-05-15 | 北京中飞华正检测技术服务有限公司 | A kind of swirling eddy generating means of electric drying oven with forced convection |
| CN109340826A (en) * | 2018-09-25 | 2019-02-15 | 西北工业大学 | A kind of flame combustion chamber tube wall surface two-layer compound cooling structure |
| CN111486477A (en) * | 2020-04-07 | 2020-08-04 | 南京航空航天大学 | Mixing hole adjusting system and method for adjusting outlet temperature distribution of combustion chamber |
| CN111486477B (en) * | 2020-04-07 | 2021-04-20 | 南京航空航天大学 | Mixing hole adjusting system and method for adjusting outlet temperature distribution of combustion chamber |
| CN114526497A (en) * | 2022-01-07 | 2022-05-24 | 清华大学 | Double-necking combined spiral-flow type center-grading high-temperature-rise combustion chamber |
| CN115727354A (en) * | 2022-11-11 | 2023-03-03 | 中国航发哈尔滨东安发动机有限公司 | Turbofan engine flame tube structure for aircraft |
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