EP1693572A3 - Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine - Google Patents

Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine Download PDF

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Publication number
EP1693572A3
EP1693572A3 EP20060100669 EP06100669A EP1693572A3 EP 1693572 A3 EP1693572 A3 EP 1693572A3 EP 20060100669 EP20060100669 EP 20060100669 EP 06100669 A EP06100669 A EP 06100669A EP 1693572 A3 EP1693572 A3 EP 1693572A3
Authority
EP
European Patent Office
Prior art keywords
axis
tip
high pressure
turbine engine
pressure compressor
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.)
Granted
Application number
EP20060100669
Other languages
German (de)
French (fr)
Other versions
EP1693572B1 (en
EP1693572A2 (en
Inventor
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
Original Assignee
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1693572A2 publication Critical patent/EP1693572A2/en
Publication of EP1693572A3 publication Critical patent/EP1693572A3/en
Application granted granted Critical
Publication of EP1693572B1 publication Critical patent/EP1693572B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • 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
    • F04D27/023—Details or means for fluid extraction
    • 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
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Abstract

Compresseur de turbomachine comportant au moins une pluralité d'aubes mobiles (16) et, espacée dans une direction axiale par rapport à un axe central longitudinal de la turbomachine (12), une pluralité d'aubes fixes (18), un carter fixe (14) enveloppant cette pluralité d'aubes mobiles et comportant une pluralité de trous de prélèvement (24) centrés entre 5 et 50% de la longueur de corde de l'aube et d'un diamètre inférieur ou égal à 30% de la longueur de corde de l'aube, chacun des trous de prélèvement présentant une double inclinaison par rapport à l'axe central longitudinal. Avantageusement, les trous de prélèvement comportent chacun un premier axe d'inclinaison présentant un angle ϕ par rapport à l'axe central longitudinal compris entre 30 et 90° et un second axe d'inclinaison perpendiculaire au premier et présentant un angle θ par rapport à l'axe central longitudinal compris entre 30 et 90°.

Figure imgaf001
A turbomachine compressor comprising at least a plurality of moving blades (16) and, spaced in an axial direction relative to a longitudinal central axis of the turbomachine (12), a plurality of stationary vanes (18), a stationary housing ( 14) enclosing said plurality of blades and having a plurality of sampling holes (24) centered between 5 and 50% of the length of rope of the blade and of a diameter less than or equal to 30% of the length of the blade. dawn rope, each of the sampling holes having a double inclination with respect to the longitudinal central axis. Advantageously, the sampling holes each comprise a first axis of inclination having an angle φ with respect to the longitudinal central axis of between 30 and 90 ° and a second axis of inclination perpendicular to the first and having an angle θ with respect to the central longitudinal axis between 30 and 90 °.
Figure imgaf001
EP06100669.8A 2005-02-16 2006-01-20 Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine Active EP1693572B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0501567A FR2882112B1 (en) 2005-02-16 2005-02-16 HEAD SAMPLING OF HIGH PRESSURE COMPRESSOR MOBILE WHEELS FROM TURBOREACTOR

Publications (3)

Publication Number Publication Date
EP1693572A2 EP1693572A2 (en) 2006-08-23
EP1693572A3 true EP1693572A3 (en) 2011-05-18
EP1693572B1 EP1693572B1 (en) 2015-11-04

Family

ID=35229705

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06100669.8A Active EP1693572B1 (en) 2005-02-16 2006-01-20 Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine

Country Status (7)

Country Link
US (1) US7549838B2 (en)
EP (1) EP1693572B1 (en)
JP (1) JP5004476B2 (en)
CN (1) CN1840864B (en)
CA (1) CA2536132C (en)
FR (1) FR2882112B1 (en)
RU (1) RU2395010C2 (en)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0616847D0 (en) * 2006-08-25 2006-10-04 Rolls Royce Plc Aeroengine bleed valve
EP2058524A1 (en) * 2007-11-12 2009-05-13 Siemens Aktiengesellschaft Air bleed compressor with variable guide vanes
FR2958694B1 (en) * 2010-04-07 2014-04-18 Snecma ENGINE COMPRESSOR, IN PARTICULAR AIRCRAFT TURBOJET ENGINE, EQUIPPED WITH AN AIR-TESTING SYSTEM
FR2970302B1 (en) * 2011-01-11 2015-07-17 Snecma DOUBLE FLOW TURBOREACTOR
JP5591142B2 (en) * 2011-02-16 2014-09-17 三菱重工業株式会社 Extraction structure of rotating machine
EP2532898A1 (en) * 2011-06-08 2012-12-12 Siemens Aktiengesellschaft Axial turbo compressor
CN102312860B (en) * 2011-09-01 2013-04-24 西北工业大学 Suction surface sucking stator blade of air 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
US9399951B2 (en) * 2012-04-17 2016-07-26 General Electric Company Modular louver system
RU2623323C2 (en) * 2012-09-06 2017-06-23 Сименс Акциенгезелльшафт Turbomachine and method of its operation
CN103994101B (en) * 2013-02-19 2016-04-20 中国科学院工程热物理研究所 Based on multi stage axial flow compressor wheel hub end wall self-loopa suction air jet system and method
US9810157B2 (en) 2013-03-04 2017-11-07 Pratt & Whitney Canada Corp. Compressor shroud reverse bleed holes
US9726084B2 (en) 2013-03-14 2017-08-08 Pratt & Whitney Canada Corp. Compressor bleed self-recirculating system
JP6037996B2 (en) 2013-10-17 2016-12-07 三菱重工業株式会社 Compressor and gas turbine
EP2868898A1 (en) 2013-10-30 2015-05-06 Siemens Aktiengesellschaft Improved partial load operation of a gas turbine with an adjustable bypass flow channel
GB201702383D0 (en) * 2017-02-14 2017-03-29 Rolls Royce Plc Gas turbine engine fan blade with axial lean
CN108119406B (en) * 2018-01-11 2020-11-27 南京航空航天大学 Axial compressor circumferential large-interval small-through-hole casing
JP7041033B2 (en) * 2018-09-26 2022-03-23 本田技研工業株式会社 Axial flow compressor
JP7228402B2 (en) * 2019-02-18 2023-02-24 株式会社オティックス Compressor housing for turbocharger and manufacturing method thereof
CN110083869B (en) * 2019-03-27 2021-02-26 南京航空航天大学 Calculation method for evaluating influence of mode conversion on stability margin of turbojet/turbofan variable cycle engine
CN111734679A (en) * 2020-07-02 2020-10-02 中国航发常州兰翔机械有限责任公司 Aeroengine compressor inner casing with air vent and machining method thereof
CN114183403B (en) * 2022-02-14 2022-05-06 成都中科翼能科技有限公司 Inclined hole type processing casing and air compressor

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3993414A (en) * 1973-10-23 1976-11-23 Office National D'etudes Et De Recherches Aerospatiales (O.N.E.R.A.) Supersonic compressors
US4479755A (en) * 1982-04-22 1984-10-30 A/S Kongsberg Vapenfabrikk Compressor boundary layer bleeding system
GB2158879A (en) * 1984-05-19 1985-11-20 Rolls Royce Preventing surge in an axial flow compressor
FR2669687A1 (en) * 1984-06-19 1992-05-29 Rolls Royce Plc Axial-flow compressor
EP0751280A1 (en) * 1995-05-31 1997-01-02 United Technologies Corporation Flow aligned plenum endwall treatment for compressor blades
EP1103725A2 (en) * 1999-11-25 2001-05-30 Rolls Royce Plc Processing tip treatment bars in a gas turbine engine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59168296A (en) * 1983-03-16 1984-09-21 Hitachi Ltd Surging preventive device of multistage axial-flow compressor
JP3816150B2 (en) * 1995-07-18 2006-08-30 株式会社荏原製作所 Centrifugal fluid machinery
JP3884880B2 (en) * 1999-04-26 2007-02-21 淳一 黒川 Turbomachine with reduced blade inlet recirculation flow and blade rotation stall
US6226974B1 (en) * 1999-06-25 2001-05-08 General Electric Co. Method of operation of industrial gas turbine for optimal performance
JP3841391B2 (en) * 2000-03-17 2006-11-01 株式会社 日立インダストリイズ Turbo machine
US7147426B2 (en) * 2004-05-07 2006-12-12 Pratt & Whitney Canada Corp. Shockwave-induced boundary layer bleed

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3993414A (en) * 1973-10-23 1976-11-23 Office National D'etudes Et De Recherches Aerospatiales (O.N.E.R.A.) Supersonic compressors
US4479755A (en) * 1982-04-22 1984-10-30 A/S Kongsberg Vapenfabrikk Compressor boundary layer bleeding system
GB2158879A (en) * 1984-05-19 1985-11-20 Rolls Royce Preventing surge in an axial flow compressor
FR2669687A1 (en) * 1984-06-19 1992-05-29 Rolls Royce Plc Axial-flow compressor
EP0751280A1 (en) * 1995-05-31 1997-01-02 United Technologies Corporation Flow aligned plenum endwall treatment for compressor blades
EP1103725A2 (en) * 1999-11-25 2001-05-30 Rolls Royce Plc Processing tip treatment bars in a gas turbine engine

Also Published As

Publication number Publication date
RU2395010C2 (en) 2010-07-20
CN1840864A (en) 2006-10-04
CA2536132A1 (en) 2006-08-16
US7549838B2 (en) 2009-06-23
FR2882112A1 (en) 2006-08-18
EP1693572B1 (en) 2015-11-04
FR2882112B1 (en) 2007-05-11
EP1693572A2 (en) 2006-08-23
JP2006226285A (en) 2006-08-31
CA2536132C (en) 2013-06-18
CN1840864B (en) 2010-05-26
JP5004476B2 (en) 2012-08-22
US20060182623A1 (en) 2006-08-17
RU2006104789A (en) 2007-09-27

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