DE3881640T2 - Rahmenkonstruktion für ein Strahltriebwerk. - Google Patents

Rahmenkonstruktion für ein Strahltriebwerk.

Info

Publication number
DE3881640T2
DE3881640T2 DE88310426T DE3881640T DE3881640T2 DE 3881640 T2 DE3881640 T2 DE 3881640T2 DE 88310426 T DE88310426 T DE 88310426T DE 3881640 T DE3881640 T DE 3881640T DE 3881640 T2 DE3881640 T2 DE 3881640T2
Authority
DE
Germany
Prior art keywords
jet engine
frame construction
jet
engine
construction
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 - Fee Related
Application number
DE88310426T
Other languages
English (en)
Other versions
DE3881640D1 (de
Inventor
John William Vdoviak
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 DE3881640D1 publication Critical patent/DE3881640D1/de
Publication of DE3881640T2 publication Critical patent/DE3881640T2/de
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/04—Mounting of an exhaust cone in the jet pipe
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • F02K1/825—Infrared radiation suppressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
DE88310426T 1987-11-05 1988-11-04 Rahmenkonstruktion für ein Strahltriebwerk. Expired - Fee Related DE3881640T2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/117,187 US5020318A (en) 1987-11-05 1987-11-05 Aircraft engine frame construction

Publications (2)

Publication Number Publication Date
DE3881640D1 DE3881640D1 (de) 1993-07-15
DE3881640T2 true DE3881640T2 (de) 1994-02-03

Family

ID=22371393

Family Applications (1)

Application Number Title Priority Date Filing Date
DE88310426T Expired - Fee Related DE3881640T2 (de) 1987-11-05 1988-11-04 Rahmenkonstruktion für ein Strahltriebwerk.

Country Status (5)

Country Link
US (1) US5020318A (de)
EP (1) EP0315486B1 (de)
JP (1) JP2675361B2 (de)
CA (1) CA1306872C (de)
DE (1) DE3881640T2 (de)

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US5212940A (en) * 1991-04-16 1993-05-25 General Electric Company Tip clearance control apparatus and method
US5157917A (en) * 1991-05-20 1992-10-27 United Technologies Corporation Gas turbine engine cooling air flow
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US5396763A (en) * 1994-04-25 1995-03-14 General Electric Company Cooled spraybar and flameholder assembly including a perforated hollow inner air baffle for impingement cooling an outer heat shield
US5396761A (en) * 1994-04-25 1995-03-14 General Electric Company Gas turbine engine ignition flameholder with internal impingement cooling
EP0906494B1 (de) * 1996-06-21 2002-12-18 Siemens Aktiengesellschaft Turbinenwelle sowie verfahren zur kühlung einer turbinenwelle
FR2763648B1 (fr) * 1997-05-22 1999-07-02 Snecma Systeme de rechauffe dichotomique reduisant les pertes en sec
FR2764644B1 (fr) * 1997-06-12 1999-07-16 Hispano Suiza Sa Turboreacteur a double flux associe a un inverseur de poussee avec un carenage rapporte dans la veine fluide
US6612807B2 (en) 2001-11-15 2003-09-02 General Electric Company Frame hub heating system
US6868665B2 (en) * 2001-12-21 2005-03-22 General Electric Company Methods and apparatus for operating gas turbine engines
US6813878B2 (en) * 2002-12-11 2004-11-09 General Electric Company Methods and apparatus for operating gas turbine engines
US6971239B2 (en) * 2003-05-13 2005-12-06 United Technologies Corporation Augmentor pilot nozzle
US7251941B2 (en) * 2004-03-10 2007-08-07 General Electric Company Ablative afterburner
US7334409B2 (en) * 2004-05-19 2008-02-26 Alltech, Inc. Retractable afterburner for jet engine
US7007488B2 (en) * 2004-07-06 2006-03-07 General Electric Company Modulated flow turbine nozzle
US7455498B2 (en) * 2006-06-19 2008-11-25 United Technologies Corporation Slotted bleed deflector for a gas turbine engine
FR2902831B1 (fr) * 2006-06-27 2010-10-22 Airbus France Turboreacteur pour aeronef
US7565804B1 (en) 2006-06-29 2009-07-28 General Electric Company Flameholder fuel shield
US7581398B2 (en) 2006-06-29 2009-09-01 General Electric Company Purged flameholder fuel shield
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FR2917458B1 (fr) * 2007-06-13 2009-09-25 Snecma Sa Moyeu de carter d'echappement comportant des nervures de repartition de contraintes
US8029234B2 (en) * 2007-07-24 2011-10-04 United Technologies Corp. Systems and methods involving aerodynamic struts
JP5118496B2 (ja) 2008-01-10 2013-01-16 三菱重工業株式会社 ガスタービンの排気部の構造およびガスタービン
US8257030B2 (en) * 2008-03-18 2012-09-04 United Technologies Corporation Gas turbine engine systems involving fairings with locating data
US8393062B2 (en) * 2008-03-31 2013-03-12 United Technologies Corp. Systems and methods for positioning fairing sheaths of gas turbine engines
US8371812B2 (en) * 2008-11-29 2013-02-12 General Electric Company Turbine frame assembly and method for a gas turbine engine
US8177488B2 (en) * 2008-11-29 2012-05-15 General Electric Company Integrated service tube and impingement baffle for a gas turbine engine
US8713909B2 (en) * 2009-03-04 2014-05-06 United Technologies Corporation Elimination of unfavorable outflow margin
DE102009034530A1 (de) * 2009-07-23 2011-01-27 Rolls-Royce Deutschland Ltd & Co Kg Querschnittsprofil für die Stützen oder die Verkleidung von Stützen und Versorgungsleitungen eines Turbofantriebwerks
GB2486488A (en) 2010-12-17 2012-06-20 Ge Aviat Systems Ltd Testing a transient voltage protection device
US20120186261A1 (en) * 2011-01-20 2012-07-26 General Electric Company System and method for a gas turbine exhaust diffuser
JP5951187B2 (ja) * 2011-03-29 2016-07-13 三菱重工業株式会社 タービン排気構造及びガスタービン
JP5222384B2 (ja) * 2011-09-09 2013-06-26 三菱重工業株式会社 ガスタービン
US9279341B2 (en) 2011-09-22 2016-03-08 Pratt & Whitney Canada Corp. Air system architecture for a mid-turbine frame module
US9896968B2 (en) 2012-07-30 2018-02-20 United Technologies Corporation Forward compartment baffle arrangement for a geared turbofan engine
US9194330B2 (en) * 2012-07-31 2015-11-24 United Technologies Corporation Retrofitable auxiliary inlet scoop
US9097134B2 (en) * 2012-09-14 2015-08-04 Pratt & Whitney Canada Corp. Air cooling design for tail-cone generator installation
EP2938859B1 (de) 2012-12-29 2019-05-22 United Technologies Corporation Kühlarchitektur für turbinenabgasgehäuse
US10330011B2 (en) * 2013-03-11 2019-06-25 United Technologies Corporation Bench aft sub-assembly for turbine exhaust case fairing
WO2014189579A2 (en) * 2013-03-15 2014-11-27 United Technologies Corporation Rotatable full ring fairing for a turbine engine
WO2015038374A1 (en) * 2013-09-10 2015-03-19 United Technologies Corporation Flow splitting first vane support for gas turbine engine
JP5876894B2 (ja) * 2014-04-07 2016-03-02 川崎重工業株式会社 タービンの換気構造
WO2015169555A1 (en) * 2014-05-08 2015-11-12 Siemens Aktiengesellschaft Turbine assembly and corresponding method of operation
US20160102566A1 (en) * 2014-10-13 2016-04-14 Pw Power Systems, Inc. Power turbine air strut
US10087884B2 (en) 2014-12-15 2018-10-02 United Technologies Corporation Stepped fairing modulated exhaust cooling
US9784133B2 (en) * 2015-04-01 2017-10-10 General Electric Company Turbine frame and airfoil for turbine frame
US9771828B2 (en) 2015-04-01 2017-09-26 General Electric Company Turbine exhaust frame and method of vane assembly
US10711702B2 (en) 2015-08-18 2020-07-14 General Electric Company Mixed flow turbocore
US10578028B2 (en) 2015-08-18 2020-03-03 General Electric Company Compressor bleed auxiliary turbine
US20170051680A1 (en) * 2015-08-18 2017-02-23 General Electric Company Airflow injection nozzle for a gas turbine engine
US10273812B2 (en) * 2015-12-18 2019-04-30 Pratt & Whitney Canada Corp. Turbine rotor coolant supply system
US20180080476A1 (en) * 2016-09-19 2018-03-22 United Technologies Corporation Geared turbofan front center body thermal management
CN108253456B (zh) * 2017-12-29 2020-04-07 南京航空航天大学 一种基于外凹腔的旋流加力燃烧室
US10808572B2 (en) * 2018-04-02 2020-10-20 General Electric Company Cooling structure for a turbomachinery component
CN109339875B (zh) * 2018-09-21 2019-10-11 南京航空航天大学 一种带旁路引气的混合扩压器
GB2615335B (en) * 2022-02-04 2024-05-08 Rolls Royce Plc A reheat assembly
CN115200042B (zh) * 2022-07-21 2023-08-22 中国航发沈阳发动机研究所 一种采用气冷串列和分流支板整流的加力燃烧室
US20240060459A1 (en) * 2022-08-19 2024-02-22 Pratt & Whitney Canada Corp. Exhaust assembly for purging a nacelle cavity of a propulsion system
WO2024080334A1 (ja) * 2022-10-14 2024-04-18 三菱パワー株式会社 翼環アッセンブリ、およびこれを備えているガスタービン
CN116182197B (zh) * 2022-12-26 2024-05-03 中国科学院工程热物理研究所 一种加力燃烧室壁面防烧蚀结构

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Also Published As

Publication number Publication date
US5020318A (en) 1991-06-04
JP2675361B2 (ja) 1997-11-12
DE3881640D1 (de) 1993-07-15
EP0315486A3 (en) 1990-01-17
CA1306872C (en) 1992-09-01
JPH01187323A (ja) 1989-07-26
EP0315486A2 (de) 1989-05-10
EP0315486B1 (de) 1993-06-09

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Legal Events

Date Code Title Description
8320 Willingness to grant licences declared (paragraph 23)
8364 No opposition during term of opposition
8339 Ceased/non-payment of the annual fee