EP2473741B1 - Compresseur de turbomachine ayant des injecteurs d'air - Google Patents

Compresseur de turbomachine ayant des injecteurs d'air Download PDF

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Publication number
EP2473741B1
EP2473741B1 EP10762738.2A EP10762738A EP2473741B1 EP 2473741 B1 EP2473741 B1 EP 2473741B1 EP 10762738 A EP10762738 A EP 10762738A EP 2473741 B1 EP2473741 B1 EP 2473741B1
Authority
EP
European Patent Office
Prior art keywords
housing
compressor
air
upstream
rim
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP10762738.2A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2473741A1 (fr
Inventor
Michel André BOURU
Laurent Jablonski
Armel Touyeras
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP2473741A1 publication Critical patent/EP2473741A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0238—Details or means for fluid reinjection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection

Definitions

  • the present invention relates to the general field of turbomachine compressors. It relates more particularly to a high-pressure compressor turbomachine in which is provided an air recirculation to limit the phenomenon of pumping.
  • a turbomachine compressor comprises several successive stages of compression, each compression stage consisting of a row (or grid) of fixed vanes followed by a row of moving blades.
  • An annular casing surrounds the rows of blades and delimits on the outside the vein of flow of the air flow passing through the compressor.
  • Such a compressor is subject to pumping.
  • Pumping is a phenomenon that is sought to minimize within a turbomachine since it results in sudden oscillations of air pressure and air flow, which subject the compressor blades to mechanical stresses. considerable risks that may lead to their weakening or even their rupture. This phenomenon occurs especially at the blade head, at the level of the air boundary layer present between the blade heads and the compressor housing and is translated locally by lower pressure pockets.
  • the reinjection of the air taken from the flow passage is generally done by means of air injectors which are mounted in housings provided for this purpose on the casing surrounding the blades.
  • these air injectors are parts regularly angularly spaced from each other and each provided with an internal channel air injection opening, on one side in the flow path of the compressor, and on the other side to an air supply duct connected to the recirculation circuit.
  • the known solutions consist either of mounting the air injectors in their housing by a tight fit type H7p6, or to real estate air injectors in their housing by means of screws.
  • the mounting of the air injectors by a tight fit has the main drawback disassembly of these injectors which is made impossible without causing damage to the housing.
  • the maintenance of the injectors by means of screws it poses problems of application with regard to the size and the number of screws necessary (one to two screws by injector of air), not to mention the congestion which one would have to be able to have to insert a self-braking means on the housing.
  • a turbomachine compressor comprising a first casing delimiting externally a flow vein of a gaseous flow passing through the compressor, a second casing centered on the longitudinal axis of the compressor and arranged around the first casing, making allowance with that an annular space, at least one internal air injection channel opening radially, on one side into the flow passage of the gas flow passing through the compressor and, on the other, into the annular space formed between the housings, and a plurality of air injectors formed at an upstream longitudinal end of the first housing and regularly spaced from each other.
  • the main purpose of the present invention is to overcome such disadvantages by providing a compressor in which the position of the air injectors is reliable while maintaining the possibility of being able to disassemble them.
  • the invention has the advantage of providing a positional maintenance of all the air injectors in their respective housing by a simple mechanical pinch of the injectors between the two housings. In the absence of tight adjustments in the assembly, it is thus possible to replace the air injectors without causing damage to the crankcase. This results in simplified maintenance.
  • the first casing comprises bosses formed between the housings and whose outer face is on the one hand projecting with respect to the outer face of the first casing, and on the other hand recessed with respect to the outer face of the flanges.
  • the clamping means upstream of the air injectors, comprising at least one fixing screw which passes radially through the second housing and which is screwed onto one of the bosses of the first housing.
  • Each air injector may further comprise at a downstream longitudinal end, a downstream flange having an inner face bearing radially against a downstream flange of the corresponding housing of the first housing.
  • each air injector also comprises lateral flanges connecting the upstream flange to the downstream flange, these lateral flanges each having an inner face bearing radially against a lateral flange of the corresponding housing of the first housing. The presence of these lateral flanges avoids any form of parasitic introduction of the air for injection by a path other than that defined by the internal channels of air injection.
  • the invention also relates to a turbomachine comprising a compressor as defined above, the latter being able to constitute a high-pressure compressor of the turbomachine.
  • the figure 1 partially represents a turbomachine 10 of longitudinal axis 12. From upstream to downstream (in the direction of flow of the gas flows therethrough), the turbomachine comprises a fan 14, a low-pressure compressor 16, a high-pressure compressor 18 , a combustion chamber 20 and a turbine (not shown).
  • Each compressor and in particular the high-pressure compressor 18, comprises several compression stages, each stage being composed of a row (or grid) of fixed vanes 22 followed by a row of moving vanes 24. blades 22, 24 are arranged in a flow channel 26 for the flow of air passing through the compressor, this flow being defined radially on the outside by an annular envelope 28.
  • the envelope 28 surrounding the rows of blades 22, 24 of the compressor comprises one or more openings 30 opening in the vein 26 (by the right or just downstream of the blade head of a compressor. compressor stage) and opening into an annular diffusion duct 32 centered on the longitudinal axis 12 and surrounding the casing.
  • This diffusion duct 32 is connected via one or more tubes 34 to an annular sampling duct 36 also centered on the longitudinal axis 12.
  • the diffusion duct 32 opens upstream into the duct 26, for example into direction of the moving blade head of another stage of the compressor, via a plurality of air injectors 38 described hereinafter in connection with the Figures 2 to 5 .
  • the casing 28 surrounding the rows of blades of the compressor consists of a first casing 28a forming an injector support and a second casing 28b disposed around the first casing.
  • the first housing 28a is sectored, that is to say it consists of a plurality of annular housing segments put end-to-end.
  • These two housings 28a, 28b are centered on the longitudinal axis 12 of the turbomachine and are spaced radially from one another to form between them an annular space 40 which opens into the diffusion duct 32.
  • the first housing 28a At its upstream end (with respect to the direction of flow of the gas flow through the compressor), the first housing 28a has a plurality of housings 42 regularly spaced from each other, each housing 42 having an upstream flange 44 and a flange downstream 46. In these housings are mounted the air injectors 38.
  • Each air injector 38 comprises at least one internal air injection channel 48 which opens radially, on one side into the flow line 26 of the gas flow passing through the compressor and on the other side into the space ring 40 formed between the casings 28a, 28b. This air injection channel is thus supplied with air by the diffusion duct 32.
  • each air injector 38 comprises at its longitudinal end downstream a flange (or spoiler) 50 whose inner face 50a bears against the downstream flange 46 of the corresponding housing of the first housing.
  • Each air injector 38 also comprises at its upstream longitudinal end an upstream rim (or spoiler) 52 having an inner face 52a bearing radially against the upstream edge 44 of the corresponding housing of the first housing and an outer face 52b bearing radially against an inner face of the second housing 28b.
  • an upstream rim (or spoiler) 52 having an inner face 52a bearing radially against the upstream edge 44 of the corresponding housing of the first housing and an outer face 52b bearing radially against an inner face of the second housing 28b.
  • These flanges 50, 52 make it possible in particular to participate in the radial positioning of the injectors 38 on the first casing 28a and constitute obstacles to the parasitic passage of air via a path other than that provided by the internal air injection channels 48.
  • the air injectors 38 are held in position in their respective housings 42 of the first housing 28a by means of clamping their upstream flange 52.
  • the first housing 28a comprises bosses 54 which are formed at the upstream end between the housings 42 of the air injectors. These bosses have an outer face which is, on the one hand protruding radially from the outer face of the first housing, and secondly radially recessed with respect to the outer face 52b of the upstream flanges 52 of the air injectors. .
  • the outer face 52b of the upstream flanges 52 of the air injectors project radially relative to the bosses 54 of the first casing when the air injectors are mounted in their housings (this difference in level is shown schematically by the h rating on the figure 3 ).
  • at least one of these bosses has a threaded hole 56.
  • a fixing screw 58 which passes radially through the second casing 28b from one side to the other is screwed into this bore 56.
  • This screw makes it possible to fix the second casing 28b on the first casing 28a. It also allows the housings 28a, 28b to exert a radial clamping force of the upstream flange 52 of each air injector 38 mounted in the housing 42 of the first housing.
  • fixing screws 58 may vary. Preferably, these are regularly distributed over the entire circumference of the compressor.
  • the air injectors 38 'of the compressor 10' partially shown on the figure 5 have the particularity of having lateral flanges (or spoilers) 60 which connect the downstream flange 50 to the upstream flange 52 of the injectors.
  • These lateral flanges each have an inner face which bears radially against a lateral rim 62 of the corresponding housing 42 'of the first casing 28a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)
EP10762738.2A 2009-08-31 2010-08-20 Compresseur de turbomachine ayant des injecteurs d'air Active EP2473741B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0955922A FR2949518B1 (fr) 2009-08-31 2009-08-31 Compresseur de turbomachine ayant des injecteurs d'air
PCT/FR2010/051744 WO2011023891A1 (fr) 2009-08-31 2010-08-20 Compresseur de turbomachine ayant des injecteurs d'air

Publications (2)

Publication Number Publication Date
EP2473741A1 EP2473741A1 (fr) 2012-07-11
EP2473741B1 true EP2473741B1 (fr) 2018-10-03

Family

ID=42062503

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10762738.2A Active EP2473741B1 (fr) 2009-08-31 2010-08-20 Compresseur de turbomachine ayant des injecteurs d'air

Country Status (9)

Country Link
US (1) US9074605B2 (enExample)
EP (1) EP2473741B1 (enExample)
JP (1) JP5686809B2 (enExample)
CN (1) CN102483070B (enExample)
BR (1) BR112012004470B1 (enExample)
CA (1) CA2772054C (enExample)
FR (1) FR2949518B1 (enExample)
RU (1) RU2561838C2 (enExample)
WO (1) WO2011023891A1 (enExample)

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CN102852668B (zh) * 2011-06-29 2015-08-12 中国科学院工程热物理研究所 一种轴流风扇/压气机自引气喷气机构
EP2639411B1 (de) * 2012-03-12 2014-12-10 MTU Aero Engines GmbH Gehäuse einer Stömungsmaschine mit einem Fluidleitsystem
CN103994101B (zh) * 2013-02-19 2016-04-20 中国科学院工程热物理研究所 基于多级轴流压气机轮毂端壁自循环抽吸喷气装置及方法
DE102013210168A1 (de) * 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für eine Strömungsmaschine
DE102013210171A1 (de) * 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für eine Strömungsmaschine
DE102013210167A1 (de) * 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für eine Strömungsmaschine
FR3034145B1 (fr) 2015-03-26 2017-04-07 Snecma Etage de compresseur
CN106015098B (zh) * 2016-05-18 2017-12-12 中国北方发动机研究所(天津) 一种有效拓宽压气机流量范围的预旋消音装置
CN105927560B (zh) * 2016-06-28 2018-09-04 中国科学院工程热物理研究所 一种具有扩稳增效装置的压气机
US10746098B2 (en) 2018-03-09 2020-08-18 General Electric Company Compressor rotor cooling apparatus
FR3101670B1 (fr) * 2019-10-08 2021-10-08 Safran Aircraft Engines Injecteur pour une turbine haute pression
US11674396B2 (en) 2021-07-30 2023-06-13 General Electric Company Cooling air delivery assembly
US11732612B2 (en) * 2021-12-22 2023-08-22 Rolls-Royce North American Technologies Inc. Turbine engine fan track liner with tip injection air recirculation passage
US11946379B2 (en) 2021-12-22 2024-04-02 Rolls-Royce North American Technologies Inc. Turbine engine fan case with manifolded tip injection air recirculation passages
US11702945B2 (en) 2021-12-22 2023-07-18 Rolls-Royce North American Technologies Inc. Turbine engine fan case with tip injection air recirculation passage
CN116717373A (zh) * 2023-05-16 2023-09-08 中国航发沈阳发动机研究所 一种燃气轮机及航空发动机中压气机扩稳设计方法
CN120062163B (zh) * 2025-04-28 2025-07-25 东方电气集团东方电机有限公司 一种消除水泵水轮机顶盖下腔簇状压力脉动的装置

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Also Published As

Publication number Publication date
CA2772054C (fr) 2017-01-17
CN102483070A (zh) 2012-05-30
BR112012004470A2 (pt) 2020-08-11
FR2949518A1 (fr) 2011-03-04
RU2561838C2 (ru) 2015-09-10
US9074605B2 (en) 2015-07-07
WO2011023891A1 (fr) 2011-03-03
FR2949518B1 (fr) 2011-10-21
BR112012004470B1 (pt) 2021-01-26
JP2013503292A (ja) 2013-01-31
CN102483070B (zh) 2015-05-06
JP5686809B2 (ja) 2015-03-18
CA2772054A1 (fr) 2011-03-03
RU2012112476A (ru) 2013-10-10
US20120201654A1 (en) 2012-08-09
EP2473741A1 (fr) 2012-07-11

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