CN202209695U - Turboshaft engine backflow combustion chamber with novel flame tube cooling structure - Google Patents
Turboshaft engine backflow combustion chamber with novel flame tube cooling structure Download PDFInfo
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- CN202209695U CN202209695U CN2011202593997U CN201120259399U CN202209695U CN 202209695 U CN202209695 U CN 202209695U CN 2011202593997 U CN2011202593997 U CN 2011202593997U CN 201120259399 U CN201120259399 U CN 201120259399U CN 202209695 U CN202209695 U CN 202209695U
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- 238000001816 cooling Methods 0.000 title claims abstract description 78
- 238000002485 combustion reaction Methods 0.000 title abstract description 15
- 238000005452 bending Methods 0.000 claims description 56
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 13
- 150000001875 compounds Chemical class 0.000 abstract description 2
- 238000009792 diffusion process Methods 0.000 abstract 1
- 230000007704 transition Effects 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 8
- 239000000567 combustion gas Substances 0.000 description 6
- 239000007789 gas Substances 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- 230000005855 radiation Effects 0.000 description 3
- 230000007812 deficiency Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 238000005406 washing Methods 0.000 description 2
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
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Abstract
The utility model discloses a turboshaft engine backflow combustion chamber with a novel flame tube cooling structure, wherein the bent section of the turboshaft engine backflow combustion chamber is designed into a cooling structure of impact plus reverse convection plus an air film ; the impact cooling and enhanced heat exchange of a cooling air stream to the bent wall surface of the combustion chamber and the obstruction effect of the cooling air film to the high-temperature gas are taken full advantage so as to cool the wall surface; the straight pipe section of the combustion chamber is designed into a cooling structure of impact plus diffusion , and the wall surface of the combustion chamber is kept even by taking full advantage of low wall surface temperature gradient and high cooling efficiency of the cooling structure; and at the intersection of the straight pipe section and the bent section, the two cooling structures are in natural transition with each other so that the temperature change of this area is not high and the temperature distribution is even. Therefore, the turboshaft engine backflow combustion chamber is characterized in that different compound cooling structures are employed for different parts of the wall surface of the turboshaft engine backflow combustion chamber for the flow and heat exchange characteristics of different parts of the backflow combustion chamber, thereby obtaining optimal cooling effect of the wall surface of the backflow combustion chamber.
Description
Technical field
The utility model relates to a kind of turboshaft engine reverse flow type combustor, especially a kind of turboshaft engine reverse flow type combustor with novel flame tube cooling structure.
Background technology
The reverse flow type combustor is the important component part of turboshaft engine.Generally speaking, the reverse flow type combustor mainly is made up of diffuser, housing, burner inner liner, fuel nozzle and igniter etc.Its major function is exactly the abundant mixed combustion through fuel oil and air, and the combustion gas that produces HTHP promotes the turbine acting, thereby reaches the purpose that produces shaft work.In the reverse flow type combustor, burner inner liner is the place of tissue burning as most important member, and it partly is made up of flame cylindrical shell and swirler etc.Turboshaft engine reverse flow type combustor burner inner liner is because the primary zone volume is little, and heat radiation is big to the influence of burner inner liner wall, and inlet air flow speed and two strands of passage flow velocitys are low; The convection current cooling effect is poor, and the temperature difference of unit axial length is very big, is easy to generate distortion and crackle; Particularly, not only receive the radiation heating of high-temperature gas, make that combustion gas here is strong unusually to the heat convection of wall because air-flow washes away the bending section wall consumingly simultaneously at the bending section of burner inner liner; Therefore; For the reverse flow type combustor, how can the burner inner liner wall effectively be cooled off is a very stubborn problem, is a key technology of restriction turboshaft engine.
At present, the cooling structure of reverse flow type combustor's burner inner liner wall mainly is pure air film cooling structure.It has following deficiency: (1) is low owing to the cooling effect official post gets the burner inner liner efficiency of combustion, and the combustor exit temperature is low; (2) cooling air delivery is big, and the air capacity that causes participating in burning is few, makes that burning is insufficient, and ignition temperature is low, and is seriously polluted; (3) cooling effect is poor, causes the flame tube wall surface temperature too high, and the wall surface temperature gradient is big, causes the burner inner liner fracture easily, and reduce service life.In order further to improve the wall cooling effect of reverse flow type combustor's burner inner liner; External researcher has developed the multiple type of cooling; And applied for some patents, its core concept all is to carry out around the uniformity that improves reverse flow type combustor's inwall air film with the measure of taking.For example: technology (document 1) has proposed that burner inner liner wall straight length and bending section all adopt the pure cooling structure of dispersing in the reverse flow type combustor; Make that straight length and bending section wall all can form uniform air film in the reverse flow type combustor, thereby can effectively reduce the chamber wall surface temperature.But cooling effect that should technology is not high, especially makes and the not enough stable and uniform of air film causes the bending section wall surface temperature too high owing to internal face receives washing away of high temperature gas flow at bending section.Technology 2 (U.S. Pat 7451600B2) improve the cooling structure of reverse flow type combustor's burner inner liner head, have optimized the structure and the arrangement of burner inner liner head divergence hole, thereby have improved the cooling to the burner inner liner head.But should technology only be from improving the cooling effect of reverse flow type combustor's head, the whole cooling structure form of burner inner liner not being improved.Technology 3 (U.S. Pat 7624577B2) optimize to the divergence hole that adopts the burner inner liner blending hole place, reverse flow type combustor of dispersing cooling structure entirely; Improve near the flow of the divergence hole air-flow of blending hole, thereby effectively reduced the blending hole temperature of combustion chamber wall surface on every side.But this structure also is the part of only dispersing cooling structure for the reverse flow type combustor to be improved.Technology 4 (U.S. Pat 7509809B2) disperse cooling structure to primary zone, reverse flow type combustor burner inner liner and optimize, and have improved the primary zone and have dispersed cooling air volume, thereby effectively reduced the wall surface temperature in primary zone.But this structure also is only the part, reverse flow type combustor of dispersing cooling structure to be improved.
The utility model content
The utility model is to the deficiency of prior art; A kind of turboshaft engine reverse flow type combustor with novel flame tube cooling structure is provided; It adopts impact+reverse convection current+air film cooling structure at bending section; Make full use of the impact cooling reinforcing heat exchange effect of cooling blast, reach cooling wall to the combustion chamber curved wall; Impact+disperse cooling structure in the straight length employing, make full use of the little advantage of this cooling structure wall surface temperature gradient, make the chamber wall surface temperature keep evenly; And in the intersection of straight length and bending section, two kinds of cooling structures are excessive naturally, make that this regional variations in temperature is little, uniformity of temperature profile.Therefore, the utility model adopts different compound cooling structures to turboshaft engine reverse flow type combustor wall different parts, thereby obtains the best cooling effect of reverse flow type combustor's wall to reverse flow type combustor's different parts characteristics with heat transfer characteristic that flow.
For realizing above technical purpose, the utility model will be taked following technical scheme:
A kind of turboshaft engine reverse flow type combustor with novel flame tube cooling structure; Comprise burning chamber shell, burner inner liner and atomizer; Atomizer is supported on the burning chamber shell, and the jet of atomizer is connected with burner inner liner through swirler, between burning chamber shell and the burner inner liner cavity is set; This cavity is provided with the air inlet that is used to carry the cooling air, and said burner inner liner comprises burner inner liner outer wall and burner inner liner inwall; This burner inner liner outer wall comprises straight length impingement wall and the bending section impingement wall that is connected with the straight length impingement wall, and the burner inner liner inwall then comprises bending section burner inner liner inwall and the straight length divergence hole inwall that is connected with bending section burner inner liner inwall; Said straight length impingement wall is impacted the chamber with straight length divergence hole inwall through connecting being connected to form straight length of dividing plate, and the bending section impingement wall is then impacted the chamber with bending section burner inner liner inwall through being connected to form more than one bending section accordingly of plural connection dividing plate; Offer the straight length impact opening on the said straight length impingement wall, then offer divergence hole on the straight length divergence hole inwall; Each bending section impacts on the corresponding bending section impingement wall in chamber offers one group of bending section wall impact opening; And this bending section impact chamber corresponding bending section burner inner liner inwall is provided with the tongue mouth tongue piece of air inlet setting dorsad; Each sheet tongue piece all disposes an air film hole; Said tongue piece coating gas fenestra, and have the air film slit between tongue piece and the air film hole.
Said straight length divergence hole is positive rhombus and distributes; Said straight length impact opening just overlaps with the center of the positive rhombus of being made up of the straight length divergence hole at the center of straight length burner inner liner inwall projection.
Said air film hole is near connecting the dividing plate setting; Tongue piece is then extended to form with the end that is connected that connects dividing plate by the burner inner liner inwall.
Said straight length impact opening is three rows.
According to above technical scheme, can realize following beneficial effect:
Straight length burner inner liner wall bears the heating of strong luminous flame radiation and the high-temperature fuel gas heat convection to wall, and therefore, the suffered heat flow density distributed pole of this regional wall is inhomogeneous, and wall bears very big thermal stress.In order to solve this difficult problem, the utility model adopts at the straight length wall and impacts+disperse cooling structure, makes full use of the little advantage of this cooling structure wall surface temperature gradient, makes the chamber wall surface temperature keep evenly.At bending section, strong the washing away of high-temperature fuel gas born in burner inner liner inside, and the heat convection between combustion gas and wall is very strong.For this reason, the utility model adopts impact+reverse convection current+air film cooling structure at bending section, makes full use of the impact cooling reinforcing heat exchange effect of cooling blast to the combustion chamber curved wall, reaches the cooling to wall.In the intersection of straight length and bending section, two kinds of cooling structures are excessive naturally, make that this regional variations in temperature is little, uniformity of temperature profile.The concrete course of work of this reverse flow type combustor's cooling structure is: impact+disperse cooling structure for straight length; Cooling blast at first gets into the impact chamber by being positioned at the impact opening that impacts on the orifice plate; Cold side at the burner inner liner internal face forms impact jet flow; Cooling wall is carried out the enhanced heat exchange cooling wall, cool off the air entering then and be positioned at the aperture of dispersing on the burner inner liner internal face, and portion forms heat convection within it; Flow out by dispersing aperture subsequently, form stable air film layer in burner inner liner inside face combustion gas side.For bending section impact+reverse convection current+air film cooling structure; The cooling air is at first got into by impact opening and impacts the chamber; And form impact jet flow at burner inner liner internal face cold side wall strengthened heat convection, cooling blast flows in impacting the chamber against the flow direction of high-temperature fuel gas then, and with burner inner liner internal face cooling carrying out heat convection; Flow into the air film slit by the air film hole that is positioned on the burner inner liner internal face subsequently, under the effect of tongue piece, form the air film layer at burner inner liner combustion gas side wall surface.
In sum; The utility model is according to flowing and heat exchange characteristic between inner combustion gas of reverse flow type combustor's burner inner liner and wall; Made full use of flowing and the heat exchange advantage of cooling structure and impact+reverse convection current+air film cooling structure of impact+disperse; Thereby can effectively lower the Temperature Distribution and the thermograde of burner inner liner internal face, to improving burner inner liner obvious effects there is service life.The advantage of this utility model is: (1) burner inner liner thermograde is little, and wall surface temperature is low; (2) cooling effectiveness is high, and cooling air volume is few; (3) simple in structure, be easy to realize.
Description of drawings
Fig. 1 is an advanced cooling structure reverse flow type combustor structure chart.
Fig. 2 is that reverse flow type combustor's straight length impacts-disperse cooling structure expansion sketch map.
Fig. 3 is that reverse flow type combustor's bending section impact+reverse convection current+air film cooling structure launches sketch map.
In more than scheming, (1) atomizer; (2) swirler; (3) burning chamber shell; (4) straight length impingement wall; (5) burner inner liner straight length impact opening; (6) burner inner liner straight length divergence hole inwall; (7) divergence hole; (8) air film hole; (9) tongue piece; (10) bending section wall impact opening; (11) bending section burner inner liner inwall; (12) bending section impingement wall; (13) straight length impacts the chamber; (14) air film slit; (15) cavity between housing and burner inner liner; (16) bending section impacts the chamber.
The specific embodiment
Accompanying drawing discloses the structural representation of the related preferred embodiment of the utility model without limitation; Below will combine accompanying drawing that the technical scheme of the utility model at length is described.
Shown in Fig. 1 to 3; The described turboshaft engine reverse flow type combustor with novel flame tube cooling structure of the utility model comprises burning chamber shell, burner inner liner and atomizer, and atomizer is supported on the burning chamber shell; And the jet of atomizer is connected with burner inner liner through swirler; Between burning chamber shell and the burner inner liner cavity is set, this cavity is provided with the air inlet that is used to carry the cooling air, and said burner inner liner comprises burner inner liner outer wall and burner inner liner inwall; This burner inner liner outer wall comprises straight length impingement wall and the bending section impingement wall that is connected with the straight length impingement wall, and the burner inner liner inwall then comprises bending section burner inner liner inwall and the straight length divergence hole inwall that is connected with bending section burner inner liner inwall; Said straight length impingement wall is impacted the chamber with straight length divergence hole inwall through connecting being connected to form straight length of dividing plate, and the bending section impingement wall is then impacted the chamber with bending section burner inner liner inwall through being connected to form more than one bending section accordingly of plural connection dividing plate; Offer the straight length impact opening on the said straight length impingement wall, then offer divergence hole on the straight length divergence hole inwall; Each bending section impacts on the corresponding bending section impingement wall in chamber offers one group of bending section wall impact opening; And this bending section impact chamber corresponding bending section burner inner liner inwall is provided with the tongue mouth tongue piece of air inlet setting dorsad; Each sheet tongue piece all disposes an air film hole; Said tongue piece coating gas fenestra, and have the air film slit between tongue piece and the air film hole.
As shown in Figure 2, it discloses the said reverse flow type combustor of the utility model straight length and has impacted-dispersed cooling structure expansion sketch map, and wherein: said straight length divergence hole is positive rhombus and distributes; Said straight length impact opening just overlaps with the center of the positive rhombus of being made up of the straight length divergence hole at the center of straight length burner inner liner inwall projection.Promptly be positioned at divergence hole on the burner inner liner inwall and be positive rhombus and arrange, and be positioned at the centre that impact opening on the impingement wall occupy six divergence holes.
Said air film hole is near connecting the dividing plate setting; Tongue piece is then extended to form with the end that is connected that connects dividing plate by the burner inner liner inwall.Shown in the accompanying drawing 1, air film hole is opened in the afterbody of bending section burner inner liner inwall and bending section impingement wall respectively, offers the site all with to connect dividing plate adjacent for two kinds.Tongue piece comprises following two kinds of forms: the link extension of straight length burner inner liner inwall and connection dividing plate forms, bending section burner inner liner inwall forms with the link extension that connects dividing plate.
As shown in Figure 3; It discloses the said reverse flow type combustor of the utility model bending section impact+reverse convection current+air film cooling structure and has launched sketch map; Wherein: said straight length impact opening is three rows; Promptly on the bending section impingement wall, be furnished with 3 row's impact openings, the air film hole that is positioned on the bending section inwall adopts the static pressure intake method.Adopt the pure air film type of cooling in the burner inner liner outlet.
Claims (4)
1. turboshaft engine reverse flow type combustor with novel flame tube cooling structure; Comprise burning chamber shell, burner inner liner and atomizer; Atomizer is supported on the burning chamber shell, and the jet of atomizer is connected with burner inner liner through swirler, between burning chamber shell and the burner inner liner cavity is set; This cavity is provided with the air inlet that is used to carry the cooling air, and it is characterized in that: said burner inner liner comprises burner inner liner outer wall and burner inner liner inwall; This burner inner liner outer wall comprises straight length impingement wall and the bending section impingement wall that is connected with the straight length impingement wall, and the burner inner liner inwall then comprises bending section burner inner liner inwall and the straight length divergence hole inwall that is connected with bending section burner inner liner inwall; Said straight length impingement wall is impacted the chamber with straight length divergence hole inwall through connecting being connected to form straight length of dividing plate, and the bending section impingement wall is then impacted the chamber with bending section burner inner liner inwall through being connected to form more than one bending section accordingly of plural connection dividing plate; Offer the straight length impact opening on the said straight length impingement wall, then offer divergence hole on the straight length divergence hole inwall; Each bending section impacts on the corresponding bending section impingement wall in chamber offers one group of bending section wall impact opening; And this bending section impact chamber corresponding bending section burner inner liner inwall is provided with the tongue mouth tongue piece of air inlet setting dorsad; Each sheet tongue piece all disposes an air film hole; Said tongue piece coating gas fenestra, and have the air film slit between tongue piece and the air film hole.
2. the turboshaft engine reverse flow type combustor with novel flame tube cooling structure according to claim 1 is characterized in that: said straight length divergence hole is positive rhombus and distributes; Said straight length impact opening just overlaps with the center of the positive rhombus of being made up of the straight length divergence hole at the center of straight length burner inner liner inwall projection.
3. the turboshaft engine reverse flow type combustor with novel flame tube cooling structure according to claim 1 is characterized in that: said air film hole is near connecting the dividing plate setting; Tongue piece is then extended to form with the end that is connected that connects dividing plate by the burner inner liner inwall.
4. according to the said turboshaft engine reverse flow type combustor with novel flame tube cooling structure of claim 1, it is characterized in that: said straight length impact opening is three rows.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011202593997U CN202209695U (en) | 2011-07-21 | 2011-07-21 | Turboshaft engine backflow combustion chamber with novel flame tube cooling structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011202593997U CN202209695U (en) | 2011-07-21 | 2011-07-21 | Turboshaft engine backflow combustion chamber with novel flame tube cooling structure |
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| CN202209695U true CN202209695U (en) | 2012-05-02 |
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| CN2011202593997U Expired - Fee Related CN202209695U (en) | 2011-07-21 | 2011-07-21 | Turboshaft engine backflow combustion chamber with novel flame tube cooling structure |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108775601A (en) * | 2018-07-04 | 2018-11-09 | 大连派思透平动力科技有限公司 | A kind of inner tube structure suitable for gas turbine reflux tube-type 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 |
| CN113266849A (en) * | 2021-05-18 | 2021-08-17 | 中国航发湖南动力机械研究所 | Air film cooling structure and flame tube of combustion chamber of turbine engine |
| CN113483355A (en) * | 2017-07-25 | 2021-10-08 | 通用电气阿维奥有限责任公司 | Recirculation combustion liner, recirculation combustor and method of mixing cooling air therein |
| CN113739208A (en) * | 2021-09-09 | 2021-12-03 | 成都中科翼能科技有限公司 | Mixed cooling flame tube for low-pollution gas turbine |
-
2011
- 2011-07-21 CN CN2011202593997U patent/CN202209695U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113483355A (en) * | 2017-07-25 | 2021-10-08 | 通用电气阿维奥有限责任公司 | Recirculation combustion liner, recirculation combustor and method of mixing cooling air therein |
| CN113483355B (en) * | 2017-07-25 | 2023-08-11 | 通用电气阿维奥有限责任公司 | Reflow-combustion liner, reflow-combustor, and method of mixing cooling air therein |
| CN108775601A (en) * | 2018-07-04 | 2018-11-09 | 大连派思透平动力科技有限公司 | A kind of inner tube structure suitable for gas turbine reflux tube-type combustion chamber |
| CN108775601B (en) * | 2018-07-04 | 2024-05-10 | 大连欧谱纳透平动力科技有限公司 | Inner cylinder structure suitable for gas turbine backflow cylinder type 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 |
| CN113266849A (en) * | 2021-05-18 | 2021-08-17 | 中国航发湖南动力机械研究所 | Air film cooling structure and flame tube of combustion chamber of turbine engine |
| CN113266849B (en) * | 2021-05-18 | 2022-08-05 | 中国航发湖南动力机械研究所 | Air film cooling structure and flame tube of turbine engine combustion chamber |
| CN113739208A (en) * | 2021-09-09 | 2021-12-03 | 成都中科翼能科技有限公司 | Mixed cooling flame tube for low-pollution gas turbine |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120502 Termination date: 20130721 |