CN104847498B - The inter-stage firing chamber of water conservancy diversion integration in whirlpool - Google Patents
The inter-stage firing chamber of water conservancy diversion integration in whirlpool Download PDFInfo
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- CN104847498B CN104847498B CN201510278234.7A CN201510278234A CN104847498B CN 104847498 B CN104847498 B CN 104847498B CN 201510278234 A CN201510278234 A CN 201510278234A CN 104847498 B CN104847498 B CN 104847498B
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Abstract
The inter-stage firing chamber of water conservancy diversion integration in whirlpool, relates to gas turbine.Be provided with shell, front guide vane, rear guide vane and tail bone; Shell and front guide vane, rear guide vane and tail bone arrange with medial axis and are integrated; Shell is provided with annular cavity, and the same of housing front shell wall circumferentially arranges cooling air inlet hole uniformly at intervals; The each front vane of front guide vane is equipped with cooling air runner hole, leadingly form main duct between hollow body and described jacket wall, form by-pass air duct between jacket wall and described shell, formed in described cavity and stay whirlpool, for fuel oil in cavity and air blending and tissue stabilization burns ready.After burning, the low-pressure turbine acting at gas shock rear, increases thermal cycle merit, increases gas engine thrust.The technical problem of high-pressure turbine exit flow flow velocity is large, turbulence pulsation is high difficulty and flameholding and device cooling protection can be solved.
Description
Technical field
The present invention relates to gas turbine, especially relate to a kind of inter-stage firing chamber be applied between gas turbine high-pressure turbine and low-pressure turbine.
Background technique
In order to promote the power performance of aeroengine, usually having and increasing compressor pressure ratio, improve the method such as turbine inlet temperature, but due to correlative study comparatively concentrated, development potentiality is very little.
Inter-stage firing chamber promotes circulating-heating amount by adding a firing chamber between the high pressure and low-pressure turbine of aeroengine, thus promote engine power.From open source literature, this method not only can promote gas turbine thrust, can also improve oil inflame efficiency.But after this firing chamber is disposed in high-pressure turbine, its inlet air flow temperature, speed and turbulence scale are all very high, this is to realizing reliable and stable burning and device cooling protection is proposed very high requirement.Standing vortex burning chamber is made up of cavity and main flow, and air and fuel is rapid mixing also burning formation recirculating zone in cavity, and strong eddy flow can strengthen the blending of air and fuel, tissue stabilization efficient burning.Open source literature (Conradetal.AIAA2013-3711) proposes ultra-compact firing chamber and turbojet engine integrated design and main flow/inter-stage and to burn the concept of point flow integrated air inlet, but not with regard to how between tissue class firing chamber active combustion scheme carry out design and researchp.Up-to-date trapped vortex combustion is used for annular firing chamber by the present invention, by air inlet water conservancy diversion, in whirlpool and core engine/inter-stage firing chamber integration.
Patent No. publication number is that the patent of invention of CN103266922B is by transforming the guide vane between high and low pressure turbine, fuel oil merges in blade cavity to be formed with main flow after ejection atomization stays whirlpool, smooth combustion is realized after igniting, this invention is expected to promote engine thrust-weight ratio, improves fuel oil utilization efficiency.
Summary of the invention
The object of this invention is to provide one is applicable between aeroengine or ground gas turbine high and low pressure turbine, the inter-stage firing chamber of the water conservancy diversion integration in whirlpool worked under high speed, high temperature gas flow condition.This inter-stage firing chamber can solve the difficulty that high-pressure turbine exit flow flow velocity is large, turbulence pulsation is high, can solve the technical problem of flameholding and device cooling protection.
For achieving the above object, the present invention adopts following technological scheme:
The inter-stage firing chamber of water conservancy diversion integration in whirlpool, is provided with shell, front guide vane, rear guide vane and tail bone; Shell and front guide vane, rear guide vane and tail bone arrange with medial axis and are integrated;
Shell is provided with axial central through hole, housing front profile is pre-small post-large tubaeform, in the middle part of shell, profile is oblate cylindricality, in the middle part of shell, inner chamber is provided with the interlayer wall of bending structure, the interlayer wall of bending structure forms annular cavity, shell rear appearance is closing waist cylindricality, and the same of housing front shell wall circumferentially arranges cooling air inlet hole uniformly at intervals;
Front guide vane is provided with leading to hollow body, jacket wall and plural front vane, leadingly be located at housing center through hole leading portion to hollow body, leadingly expose case nose to hollow body front end, leadingly be provided with baffle plate to hollow body endoporus front portion, jacket wall is located at leading peripheral to hollow body, each front vane interval is located at leading on hollow body periphery wall, and in uniform setting, each front vane is stretched out to hollow body outer wall by leading, through jacket wall, be connected with housing front inwall, each front vane is equipped with cooling air runner hole, one end, cooling air runner hole is communicated with described cooling air inlet hole, the cooling air runner hole the other end to be leadingly communicated with to hollow body endoporus rear portion with described, leadingly form main duct between hollow body and described jacket wall, by-pass air duct is formed between jacket wall and described shell, by-pass air duct communicates with described annular cavity inside,
Rear guide vane is provided with rear guiding hollow body and plural rear blade; Rear guiding hollow body front end is connected to hollow body with leading, and each rear blade is located at rear guiding hollow body outer wall uniformly at intervals;
Tail bone is the hollow taper structure of tail end sealing, and tail bone front end is connected with described rear guiding hollow body rear end, and tail bone wall shell rear portion is provided with uniform fumarole of same circle spacing;
The blade quantity of described front guide vane can be 9 ~ 18.
The quantity of described fumarole can be 9 ~ 36.
The present invention can be applicable to the inter-stage firing chamber between gas turbine high and low pressure turbine.After gas turbine main combustion chamber, air-flow is after the acting of impulse high voltage turbine, and enter front portion of the present invention, premenstrual guide vane carries out diffusion water conservancy diversion, and high speed and high pressure air-flow slows down at this, and under the effect of guide vane, turbulence scale also reduces greatly.By-pass air duct air-flow can enter cavity from inlet hole inside and outside cavity, with main duct air-flow one same-action, is formed and stay whirlpool in described cavity, for fuel oil in cavity and air blending and tissue stabilization burns ready.After cavity burning air-flow through after after guide vane, impact the low-pressure turbine acting at rear, increase thermal cycle merit, increase gas engine thrust.Meanwhile, constantly introduce cooling air from gas compressor by cooling pore, protection associated components, after cooling, gas sprays from tail cone hole and converges with main flow.The present invention forms trapped vortex combustion, by air inlet water conservancy diversion, in whirlpool and core engine/inter-stage firing chamber integration, be applicable between aeroengine or ground gas turbine high and low pressure turbine, the inter-stage firing chamber of the water conservancy diversion integration in whirlpool worked under high speed, high temperature gas flow condition.This inter-stage firing chamber can solve the difficulty that high-pressure turbine exit flow flow velocity is large, turbulence pulsation is high, can solve the technical problem of flameholding and device cooling protection.
The present invention mainly contains following advantage:
(1) as inter-stage firing chamber, the acting loss of high-temperature fuel gas after high-pressure turbine expands can be supplemented, increased the temperature rise of combustion gas by tissue burning, improve combustion gas acting ability, thus improve motor complete machine power;
(2) taken into full account the feature of high-pressure turbine exit flow high speed, high temperature, high turbulence scale, and devised from structure the low speed flow condition that diffusion diversion section and cavity obtain being applicable to tissue burning;
(3) take into account inter-stage combustion chamber operational environment, devise cooling pore, adequately protect parts.
Accompanying drawing explanation
Fig. 1 is embodiment of the present invention overall structure schematic diagram.
Fig. 2 is the axial sectional structure schematic diagram of the embodiment of the present invention.
Fig. 3 is the embodiment of the present invention axially 120 ° of sectional structure schematic diagram.
Fig. 4 is guide blade structures schematic diagram before the embodiment of the present invention.
Fig. 5 is guide vane forward sight structural representation before the embodiment of the present invention.
Fig. 6 is the left TV structure schematic diagram of guide vane before the embodiment of the present invention.
Fig. 7 is that embodiment of the present invention enclosure axis is to sectional structure schematic diagram.
Fig. 8 is embodiment of the present invention shell mechanism schematic diagram.
Fig. 9 is guide blade structures schematic diagram after the embodiment of the present invention.
Figure 10 is the left TV structure schematic diagram of guide vane after the embodiment of the present invention.
Figure 11 is embodiment of the present invention tail cone structural representation.
Embodiment
See Fig. 1 ~ 11, the inter-stage firing chamber of water conservancy diversion integration in whirlpool described in the present embodiment, is provided with shell 2, front guide vane 4, rear guide vane 9 and tail bone 10; Shell 2 and front guide vane 4, rear guide vane 9 and tail bone 10 arrange with medial axis and are integrated.
Shell 2 is provided with axial central through hole, shell 2 front appearance is pre-small post-large tubaeform, in the middle part of shell 2, profile is oblate cylindricality, in the middle part of shell 2, inner chamber is provided with the interlayer wall 21 of bending structure, the interlayer wall 21 of bending structure forms annular cavity 8, shell 2 rear appearance is closing waist cylindricality, and the same of the anterior shell wall of shell 2 circumferentially arranges cooling air inlet hole 5 uniformly at intervals.
Front guide vane 4 is provided with leading to hollow body 41, jacket wall 42 and plural front vane 43, leadingly be located at shell 2 central through bore leading portion to hollow body 41, leadingly expose shell 2 front end to hollow body 41 front end, leadingly be provided with baffle plate 12 to hollow body 41 endoporus front portion, jacket wall 42 is located at leading peripheral to hollow body 41, each front vane 43 interval is located at leading on hollow body 41 periphery wall, and in uniform setting, each front vane 43 is stretched out to hollow body 41 outer wall by leading, through jacket wall 42, be connected with shell 2 front inner wall, each front vane 43 is equipped with cooling air runner hole 431, one end, cooling air runner hole 431 is communicated with described cooling air inlet hole 5, cooling air runner hole 431 the other end to be leadingly communicated with to hollow body 41 endoporus rear portion with described, leadingly form main duct 1 between hollow body 41 and described jacket wall 42, by-pass air duct 3 is formed between jacket wall 42 and described shell 2, by-pass air duct 3 is by being located at inlet hole 6 on described interlayer wall 21 and intake duct 7 communicates with described annular cavity 8 inside,
Rear guide vane 9 is provided with rear guiding hollow body 91 and plural rear blade 92; Rear guiding hollow body 91 front end is connected to hollow body 41 with leading, and each rear blade 92 is located at rear guiding hollow body 91 outer wall uniformly at intervals.
The hollow taper structure that tail bone 10 seals for tail end, tail bone 10 front end is connected with described rear guiding hollow body 91 rear end, and tail bone 10 wall shell rear portion is provided with uniform fumarole 11 of same circle spacing.
Blade 43 quantity of described front guide vane 4 is 12.
The quantity of described fumarole 11 is 9.
Working principle is as follows:
The embodiment of the present invention is entered from main duct 1, by-pass air duct 3 respectively from high-pressure turbine gas out.Wherein in by-pass air duct 3, air-flow slows down through expanding channel, before flowing through after guide vane 4, stream turbulence also reduces greatly, and in main duct 1, gas is then respectively through front guide vane 4 and rear guide vane 9, impacts low-pressure turbine afterwards together with cavity 8 Exhaust Gas and cooled gas.
Described cavity 8, its outside formation intake duct 7, inside has inlet hole 6, and under the acting in conjunction of main duct 1 air-flow, in by-pass air duct 3, gas will form upper and lower vortex pair after inlet hole 6,7 enters cavity, and fuel oil forms stability and high efficiency trapped vortex combustion after spraying into igniting.Combustion gas exports from cavity 8 and discharges, through after guide vane 9 rectification, then to converge with main flow, impact gas turbine low-pressure turbine in the lump and do work.
Meanwhile, in gas turbine blower, the lower gas of temperature enters tail cone 10 of the present invention by the cooling pore 5 in front guide vane 4.Thus, front guide vane 4 all can be cooled with tail cone 10, prevents from melting under very high temperature, ensure that reliably working of the present invention.Spray tail cone through tail cone fumarole 11 after cooling air, converge with main flow.The temperature being greatly conducive to exit flow is tending towards even by rear guide vane 9, and this is to the prolongation working life of low-pressure turbine and the reliably working important in inhibiting of assurance device.
Claims (3)
1. the inter-stage firing chamber of water conservancy diversion integration in whirlpool, is characterized in that, is provided with shell, front guide vane, rear guide vane and tail bone; Shell and front guide vane, rear guide vane and tail bone arrange with medial axis and are integrated;
Shell is provided with axial central through hole, housing front profile is pre-small post-large tubaeform, in the middle part of shell, profile is oblate cylindricality, in the middle part of shell, inner chamber is provided with the interlayer wall of bending structure, the interlayer wall of bending structure forms annular cavity, shell rear appearance is closing waist cylindricality, and the same of housing front shell wall circumferentially arranges cooling air inlet hole uniformly at intervals;
Front guide vane is provided with leading to hollow body, jacket wall and plural front vane, leadingly be located at housing center through hole leading portion to hollow body, leadingly expose case nose to hollow body front end, leadingly be provided with baffle plate to hollow body endoporus front portion, jacket wall is located at leading peripheral to hollow body, each front vane interval is located at leading on hollow body periphery wall, and in uniform setting, each front vane is stretched out to hollow body outer wall by leading, through jacket wall, be connected with housing front inwall, each front vane is equipped with cooling air runner hole, one end, cooling air runner hole is communicated with described cooling air inlet hole, the cooling air runner hole the other end to be leadingly communicated with to hollow body endoporus rear portion with described, leadingly form main duct between hollow body and described jacket wall, by-pass air duct is formed between jacket wall and described shell, by-pass air duct communicates with described annular cavity inside,
Rear guide vane is provided with rear guiding hollow body and plural rear blade; Rear guiding hollow body front end is connected to hollow body with leading, and each rear blade is located at rear guiding hollow body outer wall uniformly at intervals;
Tail bone is the hollow taper structure of tail end sealing, and tail bone front end is connected with described rear guiding hollow body rear end, and tail bone wall shell rear portion is provided with uniform fumarole of same circle spacing.
2. the inter-stage firing chamber of water conservancy diversion integration in whirlpool as claimed in claim 1, is characterized in that, the blade quantity of described front guide vane is 9 ~ 18.
3. the inter-stage firing chamber of water conservancy diversion integration in whirlpool as claimed in claim 1, is characterized in that, the quantity of described fumarole is 9 ~ 36.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510278234.7A CN104847498B (en) | 2015-05-27 | 2015-05-27 | The inter-stage firing chamber of water conservancy diversion integration in whirlpool |
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| CN201510278234.7A CN104847498B (en) | 2015-05-27 | 2015-05-27 | The inter-stage firing chamber of water conservancy diversion integration in whirlpool |
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| CN104847498A CN104847498A (en) | 2015-08-19 |
| CN104847498B true CN104847498B (en) | 2016-04-06 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110686275B (en) * | 2019-09-23 | 2020-09-25 | 中国科学院工程热物理研究所 | Combustion chamber flame stabilizing structure for reinforcing mixing and flame propagation |
| CN111706879B (en) * | 2020-06-10 | 2023-06-27 | 中国空气动力研究与发展中心 | Flame-stabilizing concave cavity and oil-gas matching device for duty stage of vortex-holding combustion chamber |
| CN112524641A (en) * | 2020-12-02 | 2021-03-19 | 西北工业大学 | Novel turbine interstage combustion chamber |
| CN115451427B (en) * | 2022-09-01 | 2023-10-27 | 中国航发湖南动力机械研究所 | Interstage combustion chamber and turbofan engine with same |
Citations (5)
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|---|---|---|---|---|
| CN1187232A (en) * | 1995-06-07 | 1998-07-08 | 肖恩·P·劳勒 | Improved method and apparatus for power generation |
| CN101566353A (en) * | 2009-05-11 | 2009-10-28 | 北京航空航天大学 | Double-vortex combustion chamber |
| CN102713202A (en) * | 2009-09-13 | 2012-10-03 | 贫焰公司 | Combustion cavity layouts for fuel staging in trapped vortex combustors |
| CN103266922A (en) * | 2013-06-15 | 2013-08-28 | 厦门大学 | Turbine stator blade with interstage combustor |
| EP2721273A1 (en) * | 2011-06-16 | 2014-04-23 | Socpra-Sciences Et Génie S.E.C. | Combustion systems and combustion system components for rotary ramjet engines |
-
2015
- 2015-05-27 CN CN201510278234.7A patent/CN104847498B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1187232A (en) * | 1995-06-07 | 1998-07-08 | 肖恩·P·劳勒 | Improved method and apparatus for power generation |
| CN101566353A (en) * | 2009-05-11 | 2009-10-28 | 北京航空航天大学 | Double-vortex combustion chamber |
| CN102713202A (en) * | 2009-09-13 | 2012-10-03 | 贫焰公司 | Combustion cavity layouts for fuel staging in trapped vortex combustors |
| EP2721273A1 (en) * | 2011-06-16 | 2014-04-23 | Socpra-Sciences Et Génie S.E.C. | Combustion systems and combustion system components for rotary ramjet engines |
| CN103266922A (en) * | 2013-06-15 | 2013-08-28 | 厦门大学 | Turbine stator blade with interstage combustor |
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Inventor after: Huang Yue Inventor after: Xing Fei Inventor after: Ruan Can Inventor after: Liu Chen Inventor after: Lin Zhiwei Inventor after: Zhang Tongyi Inventor after: Dong Yiwei Inventor before: Huang Yue Inventor before: Xing Fei Inventor before: Ruan Can Inventor before: Liu Chen Inventor before: Lin Zhiwei Inventor before: Zhang Tongyi |
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Effective date of registration: 20170714 Address after: Xiamen City, Fujian Province, 361005 South Siming Road No. 422 Co-patentee after: Shenzhen Research Institute of Xiamen University Patentee after: Xiamen University Address before: Xiamen City, Fujian Province, 361005 South Siming Road No. 422 Patentee before: Xiamen University |