JPS5429644B1 - - Google Patents

Info

Publication number
JPS5429644B1
JPS5429644B1 JP2859971A JP2859971A JPS5429644B1 JP S5429644 B1 JPS5429644 B1 JP S5429644B1 JP 2859971 A JP2859971 A JP 2859971A JP 2859971 A JP2859971 A JP 2859971A JP S5429644 B1 JPS5429644 B1 JP S5429644B1
Authority
JP
Japan
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.)
Pending
Application number
JP2859971A
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 filed Critical
Publication of JPS5429644B1 publication Critical patent/JPS5429644B1/ja
Pending legal-status Critical Current

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
    • 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
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • 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
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between 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
    • 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
JP2859971A 1970-05-04 1971-05-01 Pending JPS5429644B1 (ja)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US3407170A 1970-05-04 1970-05-04

Publications (1)

Publication Number Publication Date
JPS5429644B1 true JPS5429644B1 (ja) 1979-09-25

Family

ID=21874121

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2859971A Pending JPS5429644B1 (ja) 1970-05-04 1971-05-01

Country Status (7)

Country Link
US (1) US3638428A (ja)
JP (1) JPS5429644B1 (ja)
BE (1) BE766616A (ja)
CA (1) CA940312A (ja)
DE (1) DE2121043C2 (ja)
FR (1) FR2088303B1 (ja)
GB (1) GB1345892A (ja)

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US4791783A (en) * 1981-11-27 1988-12-20 General Electric Company Convertible aircraft engine
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US4569199A (en) * 1982-09-29 1986-02-11 The Boeing Company Turboprop engine and method of operating the same
FR2569783B1 (fr) * 1984-09-06 1986-09-12 Snecma Structure d'anneau et dispositif de decharge de compresseur comportant cet anneau
FR2569785B1 (fr) * 1984-09-06 1986-09-12 Snecma Disposit
US4715779A (en) * 1984-12-13 1987-12-29 United Technologies Corporation Bleed valve for axial flow compressor
US4662817A (en) * 1985-08-20 1987-05-05 The Garrett Corporation Apparatus and methods for preventing compressor surge
US4698964A (en) * 1985-09-06 1987-10-13 The Boeing Company Automatic deflector for a jet engine bleed air exhaust system
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US4827713A (en) * 1987-06-29 1989-05-09 United Technologies Corporation Stator valve assembly for a rotary machine
FR2640685B1 (fr) * 1988-12-15 1991-02-08 Snecma Vanne de decharge de compresseur de turboreacteur
FR2649445B1 (fr) * 1989-07-05 1991-10-04 Snecma Dispositif de decharge pour moteur de turbine a gaz a double flux
US5113649A (en) * 1990-05-11 1992-05-19 General Electric Company Passive bypass valve assembly
US5048286A (en) * 1990-06-29 1991-09-17 General Electric Company Bypass valve door
FR2664018B1 (fr) * 1990-06-29 1993-08-13 Gen Electric Systeme de vanne de derivation.
US5134843A (en) * 1990-10-10 1992-08-04 General Electric Company Telemetry carrier ring and support
US5236393A (en) * 1991-08-28 1993-08-17 Metal Industries, Inc. Bypass damper in series-type ventilation fan
GB2259328B (en) * 1991-09-03 1995-07-19 Gen Electric Gas turbine engine variable bleed pivotal flow splitter
US5269135A (en) * 1991-10-28 1993-12-14 General Electric Company Gas turbine engine fan cooled heat exchanger
US5380151A (en) * 1993-10-13 1995-01-10 Pratt & Whitney Canada, Inc. Axially opening cylindrical bleed valve
US5477673A (en) * 1994-08-10 1995-12-26 Pratt & Whitney Canada Inc. Handling bleed valve
US6048171A (en) 1997-09-09 2000-04-11 United Technologies Corporation Bleed valve system
DE19907907A1 (de) * 1999-02-24 2000-08-31 Abb Alstom Power Ch Ag Mehrstufiger Turboverdichter
DE19959596A1 (de) * 1999-12-10 2001-06-13 Rolls Royce Deutschland Abblaseventil eines Verdichters, insbesondere für ein Zweistrahl-Flugtriebwerk
DE10042933A1 (de) * 2000-08-31 2002-03-14 Rolls Royce Deutschland Vorrichtung zum Kühlen des Gehäuses einer Fluggasturbine
US6742324B2 (en) * 2002-09-13 2004-06-01 General Electric Company Methods and apparatus for supporting variable bypass valve systems
US6802691B2 (en) * 2002-11-19 2004-10-12 United Technologies Corporation Maintainable compressor stability bleed system
EP1799989A4 (en) * 2004-10-07 2014-07-09 Gkn Aerospace Sweden Ab GAS TURBINE INTERMEDIATE STRUCTURE AND THE INTERMEDIATE STRUCTURE COMPRISING GAS TURBINE MOTOR
US7434405B2 (en) * 2005-05-31 2008-10-14 United Technologies Corporation Bleed diffuser for gas turbine engine
GB2473578B (en) * 2006-01-20 2011-08-03 Rolls Royce Power Eng Gas turbine engine system
EP2019914A4 (en) * 2006-05-04 2013-08-14 Volvo Aero Corp DEVICE FOR SWIVING AT LEAST ONE SWIVELING ELEMENT IN A TURBO ENGINE
DE102006040757A1 (de) * 2006-08-31 2008-04-30 Rolls-Royce Deutschland Ltd & Co Kg Fluidrückführung im Trennkörper von Strömungsarbeitsmaschinen mit Nebenstromkonfiguration
US8480350B2 (en) 2006-10-12 2013-07-09 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
FR2912466A1 (fr) 2007-02-12 2008-08-15 Snecma Sa Dispositif de decharge pour un turboreacteur,et turboreacteur le comportant
US7870741B2 (en) * 2007-05-25 2011-01-18 General Electric Company Turbine engine valve assembly and method of assembling the same
FR2920134B1 (fr) * 2007-08-20 2010-02-26 Aircelle Sa Nacelle equipee d'au moins une trappe de surpression
US8371806B2 (en) * 2007-10-03 2013-02-12 United Technologies Corporation Gas turbine engine having core auxiliary duct passage
FR2936559B1 (fr) * 2008-09-30 2013-11-22 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine faisant partie de corps differents.
FR2960611B1 (fr) * 2010-05-27 2013-04-12 Snecma Bielle angulee et turbomachine a double flux comportant une telle bielle angulee
US20120070271A1 (en) 2010-09-21 2012-03-22 Urban Justin R Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events
US8602717B2 (en) 2010-10-28 2013-12-10 United Technologies Corporation Compression system for turbomachine heat exchanger
US8935926B2 (en) 2010-10-28 2015-01-20 United Technologies Corporation Centrifugal compressor with bleed flow splitter for a gas turbine engine
US8777793B2 (en) 2011-04-27 2014-07-15 United Technologies Corporation Fan drive planetary gear system integrated carrier and torque frame
FR2976022B1 (fr) * 2011-05-31 2015-05-22 Snecma Turbomachine a vannes de decharge localisees au niveau du carter intermediaire
US8919784B2 (en) * 2011-06-29 2014-12-30 United Technologies Corporation Fan duct blocker actuation tab seal
US9038366B2 (en) 2012-01-31 2015-05-26 United Technologies Corporation LPC flowpath shape with gas turbine engine shaft bearing configuration
US8402741B1 (en) 2012-01-31 2013-03-26 United Technologies Corporation Gas turbine engine shaft bearing configuration
US8863491B2 (en) 2012-01-31 2014-10-21 United Technologies Corporation Gas turbine engine shaft bearing configuration
US10400629B2 (en) 2012-01-31 2019-09-03 United Technologies Corporation Gas turbine engine shaft bearing configuration
US9091209B2 (en) 2012-06-20 2015-07-28 United Technologies Corporation Four bar bracket
US9062603B2 (en) 2012-06-20 2015-06-23 United Technologies Corporation Four bar drive mechanism for bleed system
US9518513B2 (en) * 2012-10-12 2016-12-13 General Electric Company Gas turbine engine two degree of freedom variable bleed valve for ice extraction
US9982598B2 (en) 2012-10-22 2018-05-29 General Electric Company Gas turbine engine variable bleed valve for ice extraction
WO2014160486A1 (en) * 2013-03-13 2014-10-02 Rolls-Royce North American Technologies, Inc. Compact actuation system for a gas turbine engine exhaust nozzle
US9623354B2 (en) 2013-11-21 2017-04-18 General Electric Company System for extracting matter through variable bleed valves in turbines
US10287992B2 (en) 2015-08-26 2019-05-14 General Electric Company Gas turbine engine hybrid variable bleed valve
US11391298B2 (en) 2015-10-07 2022-07-19 General Electric Company Engine having variable pitch outlet guide vanes
US10208676B2 (en) 2016-03-29 2019-02-19 General Electric Company Gas turbine engine dual sealing cylindrical variable bleed valve
US10233845B2 (en) * 2016-10-07 2019-03-19 General Electric Company Bleed valve assembly for a gas turbine engine
US10830179B2 (en) * 2017-03-01 2020-11-10 General Electric Company Variable bleed valve door assembly and system for gas turbine engines
US10830438B2 (en) * 2017-10-12 2020-11-10 Raytheon Technologies Corporation Modulated combustor bypass
US10794272B2 (en) * 2018-02-19 2020-10-06 General Electric Company Axial and centrifugal compressor
FR3083577B1 (fr) * 2018-07-06 2021-05-07 Safran Aircraft Engines Turbomachine pour aeronef comportant une pluralite de vannes de decharge variable et procede de commande
FR3095005B1 (fr) * 2019-04-09 2021-03-19 Safran Aircraft Engines Turbomachine pour un aeronef
FR3096083B1 (fr) * 2019-05-16 2021-04-16 Safran Aircraft Engines Procédé et dispositif d’estimation et d’utilisation d’une zone morte d’une vanne de turbomachine
US20230228219A1 (en) * 2022-01-18 2023-07-20 General Electric Company Bleed valve assemblies

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB867849A (en) * 1957-04-04 1961-05-10 Szydlowski Joseph Improvements in or relating to axial flow compressors, and their applications

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GB864519A (en) * 1958-08-05 1961-04-06 Rolls Royce Improved annular fluid control valve device
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FR1232667A (fr) * 1958-08-05 1960-10-11 Rolls Royce Soupape annulaire
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Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB867849A (en) * 1957-04-04 1961-05-10 Szydlowski Joseph Improvements in or relating to axial flow compressors, and their applications

Also Published As

Publication number Publication date
DE2121043C2 (de) 1981-10-08
GB1345892A (en) 1974-02-06
US3638428A (en) 1972-02-01
DE2121043A1 (de) 1972-01-13
FR2088303A1 (ja) 1972-01-07
BE766616A (fr) 1971-10-01
FR2088303B1 (ja) 1975-02-21
CA940312A (en) 1974-01-22

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