DE60309272T2 - Diffusor mit Grenzschichteinblasung für einen Brennkammereinlass - Google Patents

Diffusor mit Grenzschichteinblasung für einen Brennkammereinlass Download PDF

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Publication number
DE60309272T2
DE60309272T2 DE60309272T DE60309272T DE60309272T2 DE 60309272 T2 DE60309272 T2 DE 60309272T2 DE 60309272 T DE60309272 T DE 60309272T DE 60309272 T DE60309272 T DE 60309272T DE 60309272 T2 DE60309272 T2 DE 60309272T2
Authority
DE
Germany
Prior art keywords
diffuser
flow path
radially
annular
arrangement
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.)
Expired - Lifetime
Application number
DE60309272T
Other languages
German (de)
English (en)
Other versions
DE60309272D1 (de
Inventor
David Louis Burrus
Jack Rogers Taylor
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Application granted granted Critical
Publication of DE60309272D1 publication Critical patent/DE60309272D1/de
Publication of DE60309272T2 publication Critical patent/DE60309272T2/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/545—Ducts
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
DE60309272T 2002-11-19 2003-11-19 Diffusor mit Grenzschichteinblasung für einen Brennkammereinlass Expired - Lifetime DE60309272T2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10/299,230 US6843059B2 (en) 2002-11-19 2002-11-19 Combustor inlet diffuser with boundary layer blowing
US299230 2002-11-19

Publications (2)

Publication Number Publication Date
DE60309272D1 DE60309272D1 (de) 2006-12-07
DE60309272T2 true DE60309272T2 (de) 2007-05-31

Family

ID=32297640

Family Applications (1)

Application Number Title Priority Date Filing Date
DE60309272T Expired - Lifetime DE60309272T2 (de) 2002-11-19 2003-11-19 Diffusor mit Grenzschichteinblasung für einen Brennkammereinlass

Country Status (5)

Country Link
US (1) US6843059B2 (enExample)
EP (1) EP1426688B1 (enExample)
JP (1) JP3977797B2 (enExample)
CN (1) CN100416062C (enExample)
DE (1) DE60309272T2 (enExample)

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GB2390890B (en) * 2002-07-17 2005-07-06 Rolls Royce Plc Diffuser for gas turbine engine
FR2860041B1 (fr) * 2003-09-22 2005-11-25 Snecma Moteurs Realisation de l'etancheite dans un turboreacteur pour le prelevement cabine par tube a double rotule
US7302802B2 (en) * 2003-10-14 2007-12-04 Pratt & Whitney Canada Corp. Aerodynamic trip for a combustion system
DE102005060704A1 (de) * 2005-12-19 2007-06-28 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer
FR2904035B1 (fr) * 2006-07-19 2008-08-29 Snecma Sa Systeme de refroidissement du rouet d'un compresseur centrifuge.
WO2009013665A2 (en) * 2007-07-23 2009-01-29 Nxp B.V. A leadframe structure for electronic packages
US8240974B2 (en) * 2008-03-21 2012-08-14 United Technologies Corporation Cold air buffer supply tube
US8438855B2 (en) * 2008-07-24 2013-05-14 General Electric Company Slotted compressor diffuser and related method
US8133017B2 (en) * 2009-03-19 2012-03-13 General Electric Company Compressor diffuser
FR2945589B1 (fr) * 2009-05-14 2015-08-07 Snecma Diffuseur.
US8919127B2 (en) 2011-05-24 2014-12-30 General Electric Company System and method for flow control in gas turbine engine
CN102913950B (zh) * 2012-08-07 2015-03-25 沈阳黎明航空发动机(集团)有限责任公司 一种降低燃气轮机污染物排放的分区预混燃烧方法
EP2961945B1 (en) 2013-02-28 2020-09-02 United Technologies Corporation Method and apparatus for collecting pre-diffuser airflow and routing it to combustor pre-swirlers
WO2014158243A1 (en) 2013-03-14 2014-10-02 Rolls-Royce Corporation Multi-passage diffuser with reactivated boundry layer
EP2781692A1 (de) * 2013-03-20 2014-09-24 Siemens Aktiengesellschaft Diffusor und Strömungsmaschine mit dem Diffusor
EP2803822B1 (fr) * 2013-05-13 2019-12-04 Safran Aero Boosters SA Système de prélèvement d'air de turbomachine axiale
US11732892B2 (en) 2013-08-14 2023-08-22 General Electric Company Gas turbomachine diffuser assembly with radial flow splitters
WO2015031796A1 (en) * 2013-08-29 2015-03-05 United Technologies Corporation Hybrid diffuser case for a gas turbine engine combustor
FR3019879A1 (fr) * 2014-04-09 2015-10-16 Turbomeca Moteur d'aeronef comprenant un calage azimutal du diffuseur, par rapport a la chambre de combustion
EP3026346A1 (en) * 2014-11-25 2016-06-01 Alstom Technology Ltd Combustor liner
CN105716114B (zh) * 2014-12-04 2018-05-08 中国航空工业集团公司沈阳发动机设计研究所 一种可拆换的矩形扩压器
US20170022834A1 (en) * 2015-07-22 2017-01-26 John A. Orosa High pressure compressor diffuser for an industrial gas turbine engine
CN106226056A (zh) * 2016-08-12 2016-12-14 中国航空工业集团公司沈阳发动机设计研究所 一种扩压器
JP6800006B2 (ja) * 2016-12-15 2020-12-16 三菱重工業株式会社 圧縮機ディフューザ及びガスタービン
US11384936B2 (en) * 2019-04-05 2022-07-12 Raytheon Technologies Corporation Pre-diffuser for a gas turbine engine
US11136995B2 (en) 2019-04-05 2021-10-05 Raytheon Technologies Corporation Pre-diffuser for a gas turbine engine
US11371704B2 (en) 2019-04-05 2022-06-28 Raytheon Technologies Corporation Pre-diffuser for a gas turbine engine
KR102122737B1 (ko) * 2020-03-11 2020-06-15 주식회사 성일터빈 가스 터빈의 출구 안내익 조립 구조체
JP7358280B2 (ja) * 2020-03-23 2023-10-10 三菱重工業株式会社 ダクテッドファン及び航空機
US11578869B2 (en) 2021-05-20 2023-02-14 General Electric Company Active boundary layer control in diffuser
CN114508768A (zh) * 2022-01-13 2022-05-17 南京航空航天大学 一种带涡控扩压器的航空燃气轮机燃烧室
US11859515B2 (en) 2022-03-04 2024-01-02 General Electric Company Gas turbine engines with improved guide vane configurations
CN115289499B (zh) * 2022-10-08 2023-01-10 成都中科翼能科技有限公司 一种燃气轮机燃烧室进气口的空心支板

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US2556161A (en) * 1944-03-21 1951-06-12 Power Jets Res & Dev Ltd Gas diffusers for air supplied to combustion chambers
US3216455A (en) * 1961-12-05 1965-11-09 Gen Electric High performance fluidynamic component
US3879939A (en) * 1973-04-18 1975-04-29 United Aircraft Corp Combustion inlet diffuser employing boundary layer flow straightening vanes
US3877221A (en) * 1973-08-27 1975-04-15 Gen Motors Corp Combustion apparatus air supply
US4029430A (en) 1975-09-02 1977-06-14 Fonda Bonardi Giusto Short subsonic diffuser for large pressure ratios
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US4796429A (en) * 1976-11-15 1989-01-10 General Motors Corporation Combustor diffuser
FI782193A7 (fi) * 1977-07-16 1979-01-17 Jastram Werke Foerfarande foer aostadkommande av skjutkraft vid styrdrivanordningar foer fartyg och en haerfoer avsedd styrdrivanordning
US4194359A (en) * 1977-12-12 1980-03-25 United Technologies Corporation Means for improving the performance of burner shroud diffusers
US4320304A (en) * 1978-01-30 1982-03-16 New Environment Energy Development Aktiebolag (Need) Apparatus for increasing the flow speed of a medium and for recovering its kinetic energy
US4279569A (en) * 1979-10-16 1981-07-21 Harloff Gary J Cross-flow turbine machine
US4482290A (en) * 1983-03-02 1984-11-13 The United States Of America As Represented By The United States Department Of Energy Diffuser for augmenting a wind turbine
US5152661A (en) * 1988-05-27 1992-10-06 Sheets Herman E Method and apparatus for producing fluid pressure and controlling boundary layer
US5115642A (en) * 1991-01-07 1992-05-26 United Technologies Corporation Gas turbine engine case with intergral shroud support ribs
US5211003A (en) * 1992-02-05 1993-05-18 General Electric Company Diffuser clean air bleed assembly
FR2694962B1 (fr) * 1992-08-19 1994-10-21 Snecma Turboréacteur dont la chambre de combustion est protégée contre les effets d'une ingestion massive d'eau.
US5316437A (en) 1993-02-19 1994-05-31 General Electric Company Gas turbine engine structural frame assembly having a thermally actuated valve for modulating a flow of hot gases through the frame hub
FR2706534B1 (fr) * 1993-06-10 1995-07-21 Snecma Diffuseur-séparateur multiflux avec redresseur intégré pour turboréacteur.
US6672072B1 (en) * 1998-08-17 2004-01-06 General Electric Company Pressure boosted compressor cooling system
US6390418B1 (en) 1999-02-25 2002-05-21 United Technologies Corporation Tangentially directed acoustic jet controlling boundary layer
GB9917957D0 (en) * 1999-07-31 1999-09-29 Rolls Royce Plc A combustor arrangement
DE10009655C1 (de) * 2000-02-29 2001-05-23 Mtu Aero Engines Gmbh Kühlluftsystem
US6360763B1 (en) 2001-04-20 2002-03-26 United Technologies Corporation Control of flow separation with harmonic forcing and induced separation

Also Published As

Publication number Publication date
EP1426688B1 (en) 2006-10-25
US6843059B2 (en) 2005-01-18
CN100416062C (zh) 2008-09-03
JP2004170064A (ja) 2004-06-17
US20040093871A1 (en) 2004-05-20
EP1426688A1 (en) 2004-06-09
DE60309272D1 (de) 2006-12-07
JP3977797B2 (ja) 2007-09-19
CN1510258A (zh) 2004-07-07

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