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IT7928331A0 - Apparato e metodo per aumentare lapressione all'ingresso del compressore in turbomotori a gas. - Google Patents

Apparato e metodo per aumentare lapressione all'ingresso del compressore in turbomotori a gas.

Info

Publication number
IT7928331A0
IT7928331A0 IT7928331A IT2833179A IT7928331A0 IT 7928331 A0 IT7928331 A0 IT 7928331A0 IT 7928331 A IT7928331 A IT 7928331A IT 2833179 A IT2833179 A IT 2833179A IT 7928331 A0 IT7928331 A0 IT 7928331A0
Authority
IT
Italy
Prior art keywords
increasing
pressure
compressor inlet
gas turbo
turbo engines
Prior art date
Application number
IT7928331A
Other languages
English (en)
Other versions
IT1126668B (it
Inventor
Snow Barton Hunter
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of IT7928331A0 publication Critical patent/IT7928331A0/it
Application granted granted Critical
Publication of IT1126668B publication Critical patent/IT1126668B/it

Links

Classifications

    • 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
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
IT28331/79A 1978-12-27 1979-12-21 Apparato e metodo per aumentare la pressione all'ingresso del compressore in turbomotori a gas IT1126668B (it)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/973,766 US4292802A (en) 1978-12-27 1978-12-27 Method and apparatus for increasing compressor inlet pressure

Publications (2)

Publication Number Publication Date
IT7928331A0 true IT7928331A0 (it) 1979-12-21
IT1126668B IT1126668B (it) 1986-05-21

Family

ID=25521204

Family Applications (1)

Application Number Title Priority Date Filing Date
IT28331/79A IT1126668B (it) 1978-12-27 1979-12-21 Apparato e metodo per aumentare la pressione all'ingresso del compressore in turbomotori a gas

Country Status (6)

Country Link
US (1) US4292802A (it)
JP (1) JPS55104532A (it)
DE (1) DE2951962A1 (it)
FR (1) FR2445439B1 (it)
GB (1) GB2038947B (it)
IT (1) IT1126668B (it)

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US6174130B1 (en) * 1999-06-30 2001-01-16 General Electric Company Movable shaft assembly
JP4599652B2 (ja) * 2000-04-17 2010-12-15 株式会社Ｉｈｉ ジェットエンジンの制御方法及び制御装置
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US6742324B2 (en) * 2002-09-13 2004-06-01 General Electric Company Methods and apparatus for supporting variable bypass valve systems
US7188481B2 (en) * 2002-10-30 2007-03-13 Honeywell International Inc. Adjustable damper actuator
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EP2066872B1 (en) 2006-10-12 2014-06-18 United Technologies Corporation Method and device to avoid turbofan instability in a gas turbine engine.
WO2008045063A1 (en) 2006-10-12 2008-04-17 United Technologies Corporation Variable area nozzle assisted gas turbine engine restarting
US8459035B2 (en) 2007-07-27 2013-06-11 United Technologies Corporation Gas turbine engine with low fan pressure ratio
US8347633B2 (en) * 2007-07-27 2013-01-08 United Technologies Corporation Gas turbine engine with variable geometry fan exit guide vane system
US8511058B2 (en) * 2007-11-29 2013-08-20 United Technologies Corporation Convertible gas turbine propulsion system
FR2936558B1 (fr) * 2008-09-30 2016-11-11 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison a barillet.
FR2936561B1 (fr) 2008-09-30 2018-10-26 Safran Aircraft Engines Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par mecanisme a came
FR2936565B1 (fr) * 2008-09-30 2015-07-24 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine notamment, par guignols articules.
FR2936556B1 (fr) * 2008-09-30 2015-07-24 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine, notamment par guignols.
FR2936560B1 (fr) 2008-09-30 2014-06-27 Snecma Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par cremaillere
FR2936557B1 (fr) * 2008-09-30 2017-04-21 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison par pistes de guidage.
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.
US8084982B2 (en) 2008-11-18 2011-12-27 Honeywell International Inc. HVAC actuator with output torque compensation
US8961114B2 (en) 2010-11-22 2015-02-24 General Electric Company Integrated variable geometry flow restrictor and heat exchanger
US20130174534A1 (en) * 2012-01-05 2013-07-11 General Electric Company System and device for controlling fluid flow through a gas turbine exhaust
US20130192195A1 (en) 2012-01-31 2013-08-01 Eric J. Wehmeier Gas turbine engine with compressor inlet guide vane positioned for starting
US9062603B2 (en) * 2012-06-20 2015-06-23 United Technologies Corporation Four bar drive mechanism for bleed system
FR2994452B1 (fr) * 2012-08-09 2016-12-23 Snecma Turbomachine comportant une pluralite d'aubes radiales fixes montees en amont de la soufflante
US20140137538A1 (en) * 2012-11-16 2014-05-22 United Technologies Corporation Fast Response Bypass Engine
ZA201309530B (en) * 2012-12-21 2014-07-30 Elta Group Africa (Pty) Ltd Axial flow fan construction
US10030558B2 (en) 2015-06-29 2018-07-24 General Electric Company Power generation system exhaust cooling
US10215070B2 (en) * 2015-06-29 2019-02-26 General Electric Company Power generation system exhaust cooling
US10060316B2 (en) 2015-06-29 2018-08-28 General Electric Company Power generation system exhaust cooling
US20160376909A1 (en) * 2015-06-29 2016-12-29 General Electric Company Power generation system exhaust cooling
US20170058831A1 (en) * 2015-08-27 2017-03-02 William Barry Bryan Gas turbine engine having radially-split inlet guide vanes
US11391298B2 (en) * 2015-10-07 2022-07-19 General Electric Company Engine having variable pitch outlet guide vanes
US10316759B2 (en) 2016-05-31 2019-06-11 General Electric Company Power generation system exhaust cooling
US20180149114A1 (en) * 2016-11-30 2018-05-31 Sikorsky Aircraft Corporation Low infrared signature exhaust through active film cooling active mixing and acitve vane rotation
US10619649B2 (en) * 2017-04-04 2020-04-14 United Technologies Corporation Bellcrank assembly for gas turbine engine and method
US10174763B1 (en) * 2018-08-02 2019-01-08 Florida Turbine Technologies, Inc Variable pitch fan for gas turbine engine
US11286865B2 (en) * 2018-09-14 2022-03-29 Rolls-Royce North American Technologies Inc. Gas turbine engine with variable pitch fan and variable pitch compressor geometry
CN110685817A (zh) * 2019-10-11 2020-01-14 上海朝临动力科技有限公司 涡扇发动机及航空器

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FR1535872A (fr) * 1966-12-22 1968-08-09 Gen Electric Système de commande pour compresseurs à écoulement axial en particulier pour les moteurs à turbines à gaz
FR2094662A5 (it) * 1970-06-29 1972-02-04 Szydlowski Joseph
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DE2745131A1 (de) * 1977-10-07 1979-04-12 Motoren Turbinen Union Kombinationsgasturbinentriebwerk fuer fluggeraete mit v/stol eigenschaften

Also Published As

Publication number Publication date
GB2038947A (en) 1980-07-30
DE2951962C2 (it) 1992-07-09
US4292802A (en) 1981-10-06
GB2038947B (en) 1983-02-09
JPS55104532A (en) 1980-08-11
IT1126668B (it) 1986-05-21
FR2445439A1 (fr) 1980-07-25
FR2445439B1 (fr) 1986-03-21
DE2951962A1 (de) 1980-07-17

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Legal Events

Date Code Title Description
TA Fee payment date (situation as of event date), data collected since 19931001

Effective date: 19921216