IT1200886B - Potenziatore per turbomotore a gas - Google Patents

Potenziatore per turbomotore a gas

Info

Publication number
IT1200886B
IT1200886B IT23205/85A IT2320585A IT1200886B IT 1200886 B IT1200886 B IT 1200886B IT 23205/85 A IT23205/85 A IT 23205/85A IT 2320585 A IT2320585 A IT 2320585A IT 1200886 B IT1200886 B IT 1200886B
Authority
IT
Italy
Prior art keywords
potentiator
turbo engine
gas turbo
engine
gas
Prior art date
Application number
IT23205/85A
Other languages
English (en)
Other versions
IT8523205A0 (it
Inventor
John William Vdoviak
Jr Chester Joseph Lamando
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 IT8523205A0 publication Critical patent/IT8523205A0/it
Application granted granted Critical
Publication of IT1200886B publication Critical patent/IT1200886B/it

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
    • F23R3/002—Wall structures
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Exhaust Silencers (AREA)
  • Exhaust Gas After Treatment (AREA)
IT23205/85A 1984-12-17 1985-12-13 Potenziatore per turbomotore a gas IT1200886B (it)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/682,526 US4833881A (en) 1984-12-17 1984-12-17 Gas turbine engine augmentor

Publications (2)

Publication Number Publication Date
IT8523205A0 IT8523205A0 (it) 1985-12-13
IT1200886B true IT1200886B (it) 1989-01-27

Family

ID=24740092

Family Applications (1)

Application Number Title Priority Date Filing Date
IT23205/85A IT1200886B (it) 1984-12-17 1985-12-13 Potenziatore per turbomotore a gas

Country Status (8)

Country Link
US (1) US4833881A (it)
JP (1) JPS61155652A (it)
CA (1) CA1256708A (it)
DE (1) DE3543356A1 (it)
FR (1) FR2574859B1 (it)
GB (2) GB2169696B (it)
IT (1) IT1200886B (it)
SE (2) SE458549B (it)

Families Citing this family (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4848081A (en) * 1988-05-31 1989-07-18 United Technologies Corporation Cooling means for augmentor liner
US5070690A (en) * 1989-04-26 1991-12-10 General Electric Company Means and method for reducing differential pressure loading in an augmented gas turbine engine
FR2646880A1 (fr) * 1989-05-11 1990-11-16 Snecma Chemise de protection thermique pour canal de post-combustion ou de transition d'un turboreacteur
US5233828A (en) * 1990-11-15 1993-08-10 General Electric Company Combustor liner with circumferentially angled film cooling holes
US5181379A (en) * 1990-11-15 1993-01-26 General Electric Company Gas turbine engine multi-hole film cooled combustor liner and method of manufacture
CA2048726A1 (en) * 1990-11-15 1992-05-16 Phillip D. Napoli Combustor liner with circumferentially angled film cooling holes
CA2056592A1 (en) * 1990-12-21 1992-06-22 Phillip D. Napoli Multi-hole film cooled combustor liner with slotted film starter
GB9127505D0 (en) * 1991-03-11 2013-12-25 Gen Electric Multi-hole film cooled afterburner combustor liner
US5241827A (en) * 1991-05-03 1993-09-07 General Electric Company Multi-hole film cooled combuster linear with differential cooling
US5144795A (en) * 1991-05-14 1992-09-08 The United States Of America As Represented By The Secretary Of The Air Force Fluid cooled hot duct liner structure
US5184455A (en) * 1991-07-09 1993-02-09 The United States Of America As Represented By The Secretary Of The Air Force Ceramic blanket augmentor liner
US5720434A (en) * 1991-11-05 1998-02-24 General Electric Company Cooling apparatus for aircraft gas turbine engine exhaust nozzles
US5201887A (en) * 1991-11-26 1993-04-13 United Technologies Corporation Damper for augmentor liners
US5287697A (en) * 1992-01-02 1994-02-22 General Electric Company Variable area bypass injector seal
GB2289504B (en) * 1994-05-11 1998-01-14 British Aerospace Gas turbine propulsion unit
US5685140A (en) * 1995-06-21 1997-11-11 United Technologies Corporation Method for distributing fuel within an augmentor
GB2309296B (en) * 1995-10-11 2000-02-09 Europ Gas Turbines Ltd Gas turbine engine combuster
US5927067A (en) * 1997-11-13 1999-07-27 United Technologies Corporation Self-cleaning augmentor fuel manifold
US6351947B1 (en) * 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
ES2309029T3 (es) * 2001-01-09 2008-12-16 Mitsubishi Heavy Industries, Ltd. Camara de combustion de turbina de gas.
ITMI20012785A1 (it) 2001-12-21 2003-06-21 Nuovo Pignone Spa Tubo di fianna o "liner" migliorato per una camera di combustione di una turbina a gas a basse emissioni inquinanti
US6655147B2 (en) * 2002-04-10 2003-12-02 General Electric Company Annular one-piece corrugated liner for combustor of a gas turbine engine
US6857600B1 (en) 2002-04-26 2005-02-22 General Electric Company Infrared suppressing two dimensional vectorable single expansion ramp nozzle
US7086232B2 (en) 2002-04-29 2006-08-08 General Electric Company Multihole patch for combustor liner of a gas turbine engine
US6711900B1 (en) * 2003-02-04 2004-03-30 Pratt & Whitney Canada Corp. Combustor liner V-band design
US7013635B2 (en) * 2003-12-30 2006-03-21 United Technologies Corporation Augmentor with axially displaced vane system
FR2867507B1 (fr) * 2004-03-15 2006-06-23 Snecma Moteurs Pontet de positionnement et son utilisation au canal support de tuyere d'un turbopropulseur
US7966823B2 (en) * 2006-01-06 2011-06-28 General Electric Company Exhaust dust flow splitter system
DE102006040760A1 (de) * 2006-08-31 2008-03-06 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand für eine mager-brennende Gasturbinenbrennkammer
GB2443830B (en) * 2006-11-15 2010-01-20 Rolls Royce Plc Cowling arrangement
US20090065295A1 (en) * 2007-09-11 2009-03-12 Sherikar Sanjay V Desuperheater muffler
US8069648B2 (en) 2008-07-03 2011-12-06 United Technologies Corporation Impingement cooling for turbofan exhaust assembly
SE534873C2 (sv) 2010-06-22 2012-01-31 Scania Cv Ab Bränslesystem för insprutning av en bränsleblandning i en förbränningsmotor
US20130074507A1 (en) * 2011-09-28 2013-03-28 Karthick Kaleeswaran Combustion liner for a turbine engine
US8984888B2 (en) 2011-10-26 2015-03-24 General Electric Company Fuel injection assembly for use in turbine engines and method of assembling same
US10077741B2 (en) 2012-05-29 2018-09-18 United Technologies Corporation Spraybar face seal retention arrangement
US10253651B2 (en) 2012-06-14 2019-04-09 United Technologies Corporation Turbomachine flow control device
US9194251B2 (en) 2012-08-10 2015-11-24 United Technologies Corporation Duct damper
EP3037725B1 (en) * 2014-12-22 2018-10-31 Ansaldo Energia Switzerland AG Mixer for admixing a dilution air to the hot gas flow
US11339966B2 (en) 2018-08-21 2022-05-24 General Electric Company Flow control wall for heat engine
US11519289B2 (en) 2019-12-06 2022-12-06 Raytheon Technologies Corporation Systems and methods for hybrid electric turbine engines
US11073107B1 (en) * 2020-01-24 2021-07-27 Raytheon Technologies Corporation Systems and methods for hybrid electric turbine engines

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE466639A (it) * 1944-12-13
BE535906A (it) * 1954-02-23
US3437173A (en) * 1966-11-25 1969-04-08 Gen Electric Gas turbine engine with screech attenuating means
US3712062A (en) * 1968-04-17 1973-01-23 Gen Electric Cooled augmentor liner
FR2191025B1 (it) * 1972-07-04 1975-03-07 Aerospatiale
US3826088A (en) * 1973-02-01 1974-07-30 Gen Electric Gas turbine engine augmenter cooling liner stabilizers and supports
US3866417A (en) * 1973-02-09 1975-02-18 Gen Electric Gas turbine engine augmenter liner coolant flow control system
US3826082A (en) * 1973-03-30 1974-07-30 Gen Electric Combustion liner cooling slot stabilizing dimple
US3974647A (en) * 1974-08-26 1976-08-17 United Technologies Corporation Combustion instability reduction device having swirling flow
US4122674A (en) * 1976-12-27 1978-10-31 The Boeing Company Apparatus for suppressing combustion noise within gas turbine engines
US4222233A (en) * 1977-08-02 1980-09-16 General Electric Company Auxiliary lift propulsion system with oversized front fan

Also Published As

Publication number Publication date
DE3543356A1 (de) 1986-06-19
SE8803527D0 (sv) 1988-10-05
GB8530280D0 (en) 1986-01-22
GB2206686B (en) 1989-11-22
CA1256708A (en) 1989-07-04
FR2574859B1 (fr) 1992-11-06
US4833881A (en) 1989-05-30
IT8523205A0 (it) 1985-12-13
SE8505707L (sv) 1986-06-18
GB8813184D0 (en) 1988-07-06
GB2169696B (en) 1989-06-14
JPS61155652A (ja) 1986-07-15
FR2574859A1 (fr) 1986-06-20
SE8505707D0 (sv) 1985-12-03
SE8803527L (sv) 1988-10-05
GB2169696A (en) 1986-07-16
SE458549B (sv) 1989-04-10
GB2206686A (en) 1989-01-11

Similar Documents

Publication Publication Date Title
IT1200886B (it) Potenziatore per turbomotore a gas
IT1184116B (it) Tenuta tra componenti di turbomotore a gas
IT1168267B (it) Carburatore per turbomotore a gas
GB2211596B (en) Gas turbine engine carburetor
GB8509675D0 (en) Gas turbine engine
DE3663847D1 (en) Combustor for gas turbine engine
GB8602990D0 (en) Gas turbine engine
EP0213055A3 (en) Gas turbine engine assembly
IT8422791A0 (it) Combustore schermato specialmente per turbomotori a gas.
IT1240296B (it) Assieme rotorico per turbomotore a gas
GB8527286D0 (en) Gas turbine engines
NO850046L (no) Gassturbin
IT1183316B (it) Perfezionata rientranza di carcassa di compressore per turbomotore a gas
IT1190576B (it) Turbocompressore a gas di scarico
IT1163366B (it) Prediffusore per motori a turbina a gas
IT1185058B (it) Dispositivo di modulazione di spinta per turbomotore a gas
DK240986A (da) Udstoedsroer til en forbraendingsmotor
IL76670A0 (en) Gas turbine engine
IT1190334B (it) Struttura trasmettitrice di potenza per turbomotori a gas
IL80634A0 (en) Gas turbine engine augmentor
GB2176274B (en) Combustor for gas turbine engine
DK159937C (da) Regulator til en forbraendingsmotor
GB2169695B (en) Gas turbine engine
DK170184A (da) Udstoedningssystem til en turboladet forbraendingsmotor
BR8506080A (pt) Motor turbina a gas

Legal Events

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

Effective date: 19921216