CN101092978A - Synergic action device of preventing breath heavily and expanding stability of airbleed inside stator of multistage axial flow air compresdsor - Google Patents
Synergic action device of preventing breath heavily and expanding stability of airbleed inside stator of multistage axial flow air compresdsor Download PDFInfo
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- CN101092978A CN101092978A CN 200710119702 CN200710119702A CN101092978A CN 101092978 A CN101092978 A CN 101092978A CN 200710119702 CN200710119702 CN 200710119702 CN 200710119702 A CN200710119702 A CN 200710119702A CN 101092978 A CN101092978 A CN 101092978A
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Abstract
This invention discloses a stator internal gas-inducing efficient anti-surge steady expansion device of a multi-stage axial compressor composed of a stator, a gas-suction groove, a gas-inducing pipe and a gas-collecting chamber, in which the stator is stator blade in the multi-stage axial compressor, the groove, one or many, is placed in a region adjacent to flow separation existing on the surface of the stator suction face, the gas inducing pipe is in the stator blade and a ventilation pipe connecting suction pipes, the collecting chamber is set outside of the runner box and collects gas flows induced by the gas-inducing pipe after the suction groove absorbs small low energy gas flows, and the suction groove absorbs fluids of low energy on the surface of the stator suction side and transports them to the chamber and discharges them out of the system after mixed press.
Description
(1) technical field:
The invention provides a kind of anti-asthma of taking into account control of axial flow compressor stator blade boundary layer flow and inter-stage venting and expand stabilization device, belong to the aerospace vehicle technical field of engines.
(2) background technique:
Axial fan/gas compressor develops towards high-performance, high load and high stability direction at present, studies show that, time-dependent commentaries on classics stator is interfered the working life that can influence motor, and produce a large amount of noises, non-stationarity and heterogeneity that the pressure loss in the stator exit flow field of upstream can be aggravated the downstream rotor import, but also might cause the high cycle fatigue of motor, and therefore study a kind of air-flow control measure and effectively weaken flow separation in the stator passage, have great importance.
Prandtl has just proposed to use as far back as 1904 to blow/adsorb the way that surface layer delays airflow breakaway, and is applied in supersonic inlet.In general, FLOW CONTROL is defined as with tiny mobile variation and changes than its much bigger flow characteristic, as delay to separate, strengthen or weaken mixing, foundation " virtual " shape, and reduce resistance etc., be widely used in aerospace vehicle, naval vessel and other field of fluid machinery.Studies show that, air-breathing at blade surface, can delay airflow breakaway, improve diffusance, thereby improve the level pressure ratio.In the fluting/perforate of blade suction surface surface, absorb the low energy fluid of blade surface, prevent or postpone boundary layer and separate, make blade profile can reach very big camber, fan or the raising greatly of gas compressor load.Figure 3 shows that a heavy camber leaf grating, Fig. 4 adds the grid schematic representation of air-breathing groove for its trailing edge.Distribute and can clearly find out from Fig. 5 and Fig. 6 Mach number isopleth, after the process trailing edge was air-breathing, the flow separation situation of heavy camber leaf grating trailing edge was significantly improved, the obvious attenuate of tail.
Axial flow compressor must have enough surge margins, could guarantee that motor normally reliablely and stablely works in whole flight envelope scope He under all maneuvering flight states.Surge is to do one's utmost to avoid the state that occurs in the engine operation, therefore on the gas compressor measure that prevents gas compressor surge under off design point must arranged.Generally be provided with air vent, or adopt the adjustable stator blade of many rows, or gas compressor is made the negotiability of two rotating speed different measures such as rotor change runners at gas compressor intergrade place.Shown in Fig. 7 A, Fig. 7 B, certain the one-level place after air bleed valve places the gas compressor centre partially, during proper functioning, air bleed valve is in closed condition under the effect of high-pressure air; After engine speed drops to a certain setting value, after the tach signal that open air bleed valve is experienced in pressurized strut, the valve of the control high-pressure air in the pressurized strut is closed, air bleed valve is opened under the effect of spring force, the compressed air of a part spills out (flow into atmosphere turbojet engine, in turbofan engine in the runner by-pass air duct) from intergrade.
(3) summary of the invention:
The objective of the invention is to: provide a kind of axial flow compressor stator surface local bleed anti-asthma to expand stabilization device, to solve the problem that axial flow compressor inter-stage venting anti-asthma expands steady and stator blade surface boundary layer FLOW CONTROL.
Bleed synergy anti-asthma expands stabilization device in a kind of multi stage axial flow compressor stator of the present invention, and its technological scheme is: this device is by the air-breathing groove (or suction port) on stator, stator blade surface, in the air entraining pipe of stator blade inside and casing is provided with stator outside collection chamber formation.Stator is certain stator blade in the multi stage axial flow compressor; There is the phase near field of flow separation in the suction surface surface that air-breathing groove (or suction port) is positioned at stator, can be for one or more; Air entraining pipe is positioned at the blade interior of stator, is a breather line that is communicated with each sucking pipe; Collection chamber is positioned at runner casing outside, is the chamber that the stator air-breathing groove in surface (or suction port) suction shallow bid low energy air-flow compiles by the air entraining pipe air-flow afterwards.Air-breathing groove (or suction port) sucks air entraining pipe with the low energy fluid on stator suction surface surface, and it is transported to collection chamber, through discharge system after the mixed pressure.The core of this invention is that the anti-asthma with the venting of blade surface boundary layer FLOW CONTROL and multi stage axial flow compressor inter-stage expands steady measure and combines together, and comprehensively realizes absorbing the synergy of low energy stream group, and middle venting anti-asthma expands steady effect.
Wherein, axial flow compressor bleed and venting are to offer suction port or the realization of air-breathing groove by stator surface local zone.
Wherein, the stator surface local is offered air-breathing groove (or suction port) and is realized bleed and venting, meanwhile, suppresses the stator boundary layer flow and separates, and improves stator total pressure recovery coefficient and gas compressor stability margin.
Bleed synergy anti-asthma expands stabilization device in a kind of multi stage axial flow compressor stator of the present invention, and its advantage and effect are:
1, be easy to processing, not high to Structural Design Requirement.Slot on the stator blade surface, and for current processing technology level, all be not difficult to realize at the inner logical air entraining pipe of stator blade.
2, air-breathing by the stator blade surface, realize boundary layer flow control, aeroperformance improves in absorption low energy stream group, and it is steady that the middle venting of multistage compressor simultaneously realizes that anti-asthma expands.
(4) description of drawings:
Bleed synergy anti-asthma expands the stabilization device schematic representation in Fig. 1 stator
Bleed synergy anti-asthma expands stabilization device 3D solid schematic representation in Fig. 2 stator
Fig. 3 heavy camber leaf grating
The air-breathing grid schematic representation of Fig. 4 heavy camber leaf grating trailing edge
The Mach number isopleth distributes in Fig. 5 prototype leaf grating
The Mach number isopleth distributes in the air-breathing leaf grating of Fig. 6
Fig. 7 A axial flow compressor typical case bleed device air bleed valve is opened schematic representation
Fig. 7 B axial flow compressor typical case bleed device air bleed valve cuts out schematic representation
Sequence number is described as follows among the figure:
1, stator 2, air-breathing groove (or suction port) 3, air entraining pipe 4, collection chamber
5, rotor 6, casing 7, air bleed valve
(5) embodiment:
Bleed synergy anti-asthma expands stabilization device in a kind of multi stage axial flow compressor stator blade of the present invention, as shown in Figure 1, is made up of stator 1, air-breathing groove (or suction port) 2, air entraining pipe 3, collection chamber 4.Stator 1 is certain stator blade in the multi stage axial flow compressor; There is the phase near field of flow separation in the suction surface surface that air-breathing groove (or suction port) 2 is positioned at stator 1, can be for one or more; Air entraining pipe 3 is positioned at stator 1 blade interior, is a breather line that is communicated with each sucking pipe; Collection chamber 4 is positioned at runner casing 6 outsides, is the chamber that stator 1 surperficial air-breathing groove (or suction port) 2 suction shallow bid low energy air-flows compile by air entraining pipe 3 air-flows afterwards.Air-breathing groove (or suction port) 2 sucks air entraining pipe 3 with the low energy fluid on stator 1 suction surface surface, and it is transported to collection chamber 4, through discharge system after the mixed pressure.Its 3D solid signal as shown in Figure 2.
The present invention can realize simultaneously between compressor stage that venting and stator blade are air-breathing.Absorb stator blade surface low energy fluid, can effectively prevent or postpone flow separation, and the improvement of flow separation situation can improve the negotiability of compressor passage, and the shallow bid fluid is discharged the negotiability that runner can further improve earlier stages again simultaneously, reaches anti-asthma and expands steady purpose.The present invention just can significantly improve the aeroperformance of axial flow compressor under the situation of absorbing seldom a part of air-flow like this.
Claims (3)
1, bleed synergy anti-asthma expands stabilization device in a kind of multi stage axial flow compressor stator, and it is characterized in that: this device is to be made of stator, air-breathing groove, air entraining pipe and collection chamber; Stator is the stator blade in the multi stage axial flow compressor; There is the phase near field of flow separation in the suction surface surface that air-breathing groove is positioned at stator, can be for one or more; Air entraining pipe is positioned at stator blade inside, is a breather line that is communicated with each sucking pipe; Collection chamber is positioned at runner casing outside, is the chamber that the air-breathing groove suction in stator surface shallow bid low energy air-flow compiles by the air entraining pipe air-flow afterwards; Air-breathing groove sucks air entraining pipe with the low energy fluid on stator suction surface surface, and it is transported to collection chamber, through discharge system after the mixed pressure.
2, bleed synergy anti-asthma expands stabilization device in the multi stage axial flow compressor stator according to claim 1, it is characterized in that: axial flow compressor bleed and venting are to offer air-breathing groove or suction port realization by stator surface local zone.
3, bleed synergy anti-asthma expands stabilization device in the multi stage axial flow compressor stator according to claim 1, it is characterized in that: the stator surface local offers air-breathing groove or suction port is realized bleed and venting, meanwhile, suppress the stator boundary layer flow and separate, improve stator total pressure recovery coefficient and gas compressor stability margin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200710119702 CN101092978A (en) | 2007-07-30 | 2007-07-30 | Synergic action device of preventing breath heavily and expanding stability of airbleed inside stator of multistage axial flow air compresdsor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200710119702 CN101092978A (en) | 2007-07-30 | 2007-07-30 | Synergic action device of preventing breath heavily and expanding stability of airbleed inside stator of multistage axial flow air compresdsor |
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| CN101092978A true CN101092978A (en) | 2007-12-26 |
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| CN 200710119702 Pending CN101092978A (en) | 2007-07-30 | 2007-07-30 | Synergic action device of preventing breath heavily and expanding stability of airbleed inside stator of multistage axial flow air compresdsor |
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Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102094850A (en) * | 2010-12-24 | 2011-06-15 | 北京航空航天大学 | Design method of circumferential discontinuously distributed entraining grooves of engine air system |
| CN103047193A (en) * | 2012-12-27 | 2013-04-17 | 哈尔滨东安发动机（集团）有限公司 | Surge-preventing structure for aero-engine compressor |
| CN103133057A (en) * | 2011-11-25 | 2013-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | T-shaped groove structure adsorption type hollow stator blade |
| CN103321960A (en) * | 2013-07-12 | 2013-09-25 | 西北工业大学 | Compressor stator blade with suction surface provided with suction grooves |
| CN105156361A (en) * | 2015-09-14 | 2015-12-16 | 北京航空航天大学 | Compressor stator cascade with blade root provided with equal-width circular arc shaped channels |
| CN105156356A (en) * | 2015-09-14 | 2015-12-16 | 北京航空航天大学 | Compressor stator cascade with blade root provided with equal-width broken line shaped channels |
| CN105179322A (en) * | 2015-09-14 | 2015-12-23 | 北京航空航天大学 | Gas compressor stationary blade cascade with equal-width linear groove formed in blade root |
| CN105240322A (en) * | 2015-11-04 | 2016-01-13 | 北京航空航天大学 | Method for forming S-shaped channels on blade root to control corner separation of compressor stator |
| CN105378294A (en) * | 2013-10-17 | 2016-03-02 | 三菱重工业株式会社 | Compressor and gas turbine |
| CN105443443A (en) * | 2015-12-10 | 2016-03-30 | 哈尔滨工程大学 | Stability enhancement structure of turbocharger compressor |
| CN106368973A (en) * | 2016-11-09 | 2017-02-01 | 哈尔滨工业大学 | Gap flow control method used between fixed blade and end wall of gas compressor and gas compressor |
| CN107120315A (en) * | 2017-05-16 | 2017-09-01 | 珠海格力电器股份有限公司 | Stator blade, compressor structure and compressor |
| CN107165864A (en) * | 2017-07-24 | 2017-09-15 | 北京航空航天大学 | A kind of multi stage axial flow compressor for turning stator blade joint automatic adjusument |
| CN107191412A (en) * | 2017-07-24 | 2017-09-22 | 北京航空航天大学 | A kind of multi stage axial flow compressor of the adaptive blowing suction of front stage stator |
| CN107202036A (en) * | 2017-07-24 | 2017-09-26 | 北京航空航天大学 | It is a kind of at the same improve stator corner region flow self-loopa processor box |
| CN110300839A (en) * | 2017-02-27 | 2019-10-01 | 三菱重工业株式会社 | The exhaust component of rotating machinery, rotating machinery |
| CN111396196A (en) * | 2019-01-02 | 2020-07-10 | 中国航发商用航空发动机有限责任公司 | S-shaped switching section of gas compressor and turbofan engine |
| CN111472998A (en) * | 2020-04-21 | 2020-07-31 | 中国航发沈阳发动机研究所 | Compressor inner flow passage surface static pressure test stator blade structure |
| CN112955661A (en) * | 2019-07-22 | 2021-06-11 | 开利公司 | Centrifugal or mixed flow compressor comprising a suction diffuser |
| CN113123997A (en) * | 2021-06-17 | 2021-07-16 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor transition section synergistic structure |
| CN113153815A (en) * | 2020-11-22 | 2021-07-23 | 西北工业大学 | Supersonic adsorption type compressor blade based on multiple holes |
| CN114017387A (en) * | 2021-11-10 | 2022-02-08 | 中国航发沈阳发动机研究所 | Aeroengine compressor bleed structure |
| CN114838939A (en) * | 2021-02-01 | 2022-08-02 | 中国航发商用航空发动机有限责任公司 | Method and device for calculating flow of bleed valve of turbofan engine with large bypass ratio |
-
2007
- 2007-07-30 CN CN 200710119702 patent/CN101092978A/en active Pending
Cited By (32)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102094850A (en) * | 2010-12-24 | 2011-06-15 | 北京航空航天大学 | Design method of circumferential discontinuously distributed entraining grooves of engine air system |
| CN103133057A (en) * | 2011-11-25 | 2013-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | T-shaped groove structure adsorption type hollow stator blade |
| CN103047193A (en) * | 2012-12-27 | 2013-04-17 | 哈尔滨东安发动机（集团）有限公司 | Surge-preventing structure for aero-engine compressor |
| CN103047193B (en) * | 2012-12-27 | 2017-06-20 | 哈尔滨东安发动机（集团）有限公司 | Surge-preventing structure for aero-engine compressor |
| CN103321960A (en) * | 2013-07-12 | 2013-09-25 | 西北工业大学 | Compressor stator blade with suction surface provided with suction grooves |
| CN103321960B (en) * | 2013-07-12 | 2015-07-15 | 西北工业大学 | Compressor stator blade with suction surface provided with suction grooves |
| CN105378294A (en) * | 2013-10-17 | 2016-03-02 | 三菱重工业株式会社 | Compressor and gas turbine |
| CN105378294B (en) * | 2013-10-17 | 2017-07-25 | 三菱重工业株式会社 | Compressor and gas turbine |
| CN105179322A (en) * | 2015-09-14 | 2015-12-23 | 北京航空航天大学 | Gas compressor stationary blade cascade with equal-width linear groove formed in blade root |
| CN105179322B (en) * | 2015-09-14 | 2017-08-25 | 北京航空航天大学 | Blade root opens up the Profile For Compressor Stator leaf grating of wide straight-line groove |
| CN105156356B (en) * | 2015-09-14 | 2017-12-22 | 北京航空航天大学 | Blade root opens up the Profile For Compressor Stator leaf grating of wide broken line groove |
| CN105156356A (en) * | 2015-09-14 | 2015-12-16 | 北京航空航天大学 | Compressor stator cascade with blade root provided with equal-width broken line shaped channels |
| CN105156361A (en) * | 2015-09-14 | 2015-12-16 | 北京航空航天大学 | Compressor stator cascade with blade root provided with equal-width circular arc shaped channels |
| CN105240322A (en) * | 2015-11-04 | 2016-01-13 | 北京航空航天大学 | Method for forming S-shaped channels on blade root to control corner separation of compressor stator |
| CN105443443A (en) * | 2015-12-10 | 2016-03-30 | 哈尔滨工程大学 | Stability enhancement structure of turbocharger compressor |
| CN106368973A (en) * | 2016-11-09 | 2017-02-01 | 哈尔滨工业大学 | Gap flow control method used between fixed blade and end wall of gas compressor and gas compressor |
| CN106368973B (en) * | 2016-11-09 | 2018-04-06 | 哈尔滨工业大学 | Gap flow control method and compressor between the stator blade and end wall of compressor |
| CN110300839A (en) * | 2017-02-27 | 2019-10-01 | 三菱重工业株式会社 | The exhaust component of rotating machinery, rotating machinery |
| CN107120315A (en) * | 2017-05-16 | 2017-09-01 | 珠海格力电器股份有限公司 | Stator blade, compressor structure and compressor |
| US11408440B2 (en) | 2017-05-16 | 2022-08-09 | Gree Electric Appliances (Wuhan) Co., Ltd. | Stator blade, compressor structure and compressor |
| WO2018209955A1 (en) * | 2017-05-16 | 2018-11-22 | 格力电器（武汉）有限公司 | Stator vane, compressor structure, and compressor |
| CN107165864A (en) * | 2017-07-24 | 2017-09-15 | 北京航空航天大学 | A kind of multi stage axial flow compressor for turning stator blade joint automatic adjusument |
| CN107202036A (en) * | 2017-07-24 | 2017-09-26 | 北京航空航天大学 | It is a kind of at the same improve stator corner region flow self-loopa processor box |
| CN107191412B (en) * | 2017-07-24 | 2020-10-23 | 北京航空航天大学 | Multistage axial compressor with front-stage stator and rear-stage stator self-adaptive air blowing and sucking |
| CN107191412A (en) * | 2017-07-24 | 2017-09-22 | 北京航空航天大学 | A kind of multi stage axial flow compressor of the adaptive blowing suction of front stage stator |
| CN111396196A (en) * | 2019-01-02 | 2020-07-10 | 中国航发商用航空发动机有限责任公司 | S-shaped switching section of gas compressor and turbofan engine |
| CN112955661A (en) * | 2019-07-22 | 2021-06-11 | 开利公司 | Centrifugal or mixed flow compressor comprising a suction diffuser |
| CN111472998A (en) * | 2020-04-21 | 2020-07-31 | 中国航发沈阳发动机研究所 | Compressor inner flow passage surface static pressure test stator blade structure |
| CN113153815A (en) * | 2020-11-22 | 2021-07-23 | 西北工业大学 | Supersonic adsorption type compressor blade based on multiple holes |
| CN114838939A (en) * | 2021-02-01 | 2022-08-02 | 中国航发商用航空发动机有限责任公司 | Method and device for calculating flow of bleed valve of turbofan engine with large bypass ratio |
| CN113123997A (en) * | 2021-06-17 | 2021-07-16 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor transition section synergistic structure |
| CN114017387A (en) * | 2021-11-10 | 2022-02-08 | 中国航发沈阳发动机研究所 | Aeroengine compressor bleed structure |
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