IL37773A0 - Wall structure for a gas turbine engine - Google Patents

Wall structure for a gas turbine engine

Info

Publication number
IL37773A0
IL37773A0 IL37773A IL3777371A IL37773A0 IL 37773 A0 IL37773 A0 IL 37773A0 IL 37773 A IL37773 A IL 37773A IL 3777371 A IL3777371 A IL 3777371A IL 37773 A0 IL37773 A0 IL 37773A0
Authority
IL
Israel
Prior art keywords
gas turbine
turbine engine
wall structure
wall
engine
Prior art date
Application number
IL37773A
Other versions
IL37773A (en
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of IL37773A0 publication Critical patent/IL37773A0/en
Publication of IL37773A publication Critical patent/IL37773A/en

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
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
    • 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)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
IL37773A 1970-10-30 1971-09-23 Wall structure for a gas turbine engine IL37773A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US8562970A 1970-10-30 1970-10-30

Publications (2)

Publication Number Publication Date
IL37773A0 true IL37773A0 (en) 1971-12-29
IL37773A IL37773A (en) 1974-01-14

Family

ID=22192885

Family Applications (1)

Application Number Title Priority Date Filing Date
IL37773A IL37773A (en) 1970-10-30 1971-09-23 Wall structure for a gas turbine engine

Country Status (10)

Country Link
US (1) US3706203A (en)
AU (1) AU3490971A (en)
BE (1) BE774560A (en)
CA (1) CA938797A (en)
CH (1) CH534847A (en)
DE (1) DE2147135A1 (en)
FR (1) FR2111931B1 (en)
GB (1) GB1314666A (en)
IL (1) IL37773A (en)
NL (1) NL7113326A (en)

Families Citing this family (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3955361A (en) * 1971-12-15 1976-05-11 Phillips Petroleum Company Gas turbine combustor with controlled fuel mixing
US3938323A (en) * 1971-12-15 1976-02-17 Phillips Petroleum Company Gas turbine combustor with controlled fuel mixing
US4012902A (en) * 1974-03-29 1977-03-22 Phillips Petroleum Company Method of operating a gas turbine combustor having an independent airstream to remove heat from the primary combustion zone
US4184326A (en) * 1975-12-05 1980-01-22 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
US4361010A (en) * 1980-04-02 1982-11-30 United Technologies Corporation Combustor liner construction
US4414816A (en) * 1980-04-02 1983-11-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Combustor liner construction
US4302941A (en) * 1980-04-02 1981-12-01 United Technologies Corporation Combuster liner construction for gas turbine engine
US4333216A (en) * 1981-03-23 1982-06-08 United Technologies Corporation Method for manufacturing a sandwich panel structure
US4407205A (en) * 1982-04-30 1983-10-04 Beaufrere Albert H Regeneratively cooled coal combustor/gasifier with integral dry ash removal
US4619604A (en) * 1983-06-30 1986-10-28 Carrier Corporation Flame radiator structure
JPH0648095B2 (en) * 1985-04-18 1994-06-22 石川島播磨重工業株式会社 Liner cooling structure for gas turbine combustors, etc.
US4642993A (en) * 1985-04-29 1987-02-17 Avco Corporation Combustor liner wall
US5329773A (en) * 1989-08-31 1994-07-19 Alliedsignal Inc. Turbine combustor cooling system
US5323601A (en) * 1992-12-21 1994-06-28 United Technologies Corporation Individually removable combustor liner panel for a gas turbine engine
US5327727A (en) * 1993-04-05 1994-07-12 General Electric Company Micro-grooved heat transfer combustor wall
GB9926257D0 (en) * 1999-11-06 2000-01-12 Rolls Royce Plc Wall elements for gas turbine engine combustors
US6868675B1 (en) * 2004-01-09 2005-03-22 Honeywell International Inc. Apparatus and method for controlling combustor liner carbon formation
US20060010874A1 (en) * 2004-07-15 2006-01-19 Intile John C Cooling aft end of a combustion liner
US7278256B2 (en) * 2004-11-08 2007-10-09 United Technologies Corporation Pulsed combustion engine
US7509809B2 (en) * 2005-06-10 2009-03-31 Pratt & Whitney Canada Corp. Gas turbine engine combustor with improved cooling
DE102005059502A1 (en) * 2005-12-06 2007-06-14 Deutsches Zentrum für Luft- und Raumfahrt e.V. hot chamber
EP2116770B1 (en) * 2008-05-07 2013-12-04 Siemens Aktiengesellschaft Combustor dynamic attenuation and cooling arrangement
US8549861B2 (en) * 2009-01-07 2013-10-08 General Electric Company Method and apparatus to enhance transition duct cooling in a gas turbine engine
WO2010132439A1 (en) 2009-05-12 2010-11-18 Icr Turbine Engine Corporation Gas turbine energy storage and conversion system
US8402764B1 (en) * 2009-09-21 2013-03-26 Florida Turbine Technologies, Inc. Transition duct with spiral cooling channels
US8307654B1 (en) * 2009-09-21 2012-11-13 Florida Turbine Technologies, Inc. Transition duct with spiral finned cooling passage
US20120003595A1 (en) * 2009-09-29 2012-01-05 Honeywell International Inc. High turn down low nox burner
US8866334B2 (en) 2010-03-02 2014-10-21 Icr Turbine Engine Corporation Dispatchable power from a renewable energy facility
RU2530685C2 (en) * 2010-03-25 2014-10-10 Дженерал Электрик Компани Impact action structures for cooling systems
US8984895B2 (en) 2010-07-09 2015-03-24 Icr Turbine Engine Corporation Metallic ceramic spool for a gas turbine engine
EP2612009B1 (en) 2010-09-03 2020-04-22 ICR Turbine Engine Corporatin Gas turbine engine
US20120260662A1 (en) * 2011-02-14 2012-10-18 Icr Turbine Engine Corporation Radiation shield for a gas turbine combustor
US8955330B2 (en) * 2011-03-29 2015-02-17 Siemens Energy, Inc. Turbine combustion system liner
US9051873B2 (en) 2011-05-20 2015-06-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine shaft attachment
CN103717971B (en) * 2011-08-11 2015-09-02 通用电气公司 For the system of burner oil in gas-turbine unit
US10094288B2 (en) 2012-07-24 2018-10-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine volute attachment for a gas turbine engine
CN105318356A (en) * 2014-07-21 2016-02-10 北京航天动力研究所 High aspect ratio variable section heat exchange channel
US10478920B2 (en) 2014-09-29 2019-11-19 Rolls-Royce Corporation Dual wall components for gas turbine engines
EP3061556B1 (en) 2015-02-26 2018-08-15 Rolls-Royce Corporation Method for repairing a dual walled metallic component using braze material and such component obtained
EP3061557B1 (en) 2015-02-26 2018-04-18 Rolls-Royce Corporation Repair of dual walled metallic components using directed energy deposition material addition
GB2545459B (en) * 2015-12-17 2020-05-06 Rolls Royce Plc A combustion chamber
US20180073390A1 (en) 2016-09-13 2018-03-15 Rolls-Royce Corporation Additively deposited gas turbine engine cooling component
US11480337B2 (en) 2019-11-26 2022-10-25 Collins Engine Nozzles, Inc. Fuel injection for integral combustor and turbine vane
RU201848U1 (en) * 2020-08-12 2021-01-15 федеральное государственное бюджетное образовательное учреждение высшего образования "Ульяновский государственный технический университет" COMBUSTION CHAMBER OF A GAS TURBINE ENGINE WITH AN ACTIVE COOLING ZONE

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2458066A (en) * 1944-07-20 1949-01-04 American Locomotive Co Combustion chamber
CH255541A (en) * 1947-05-12 1948-06-30 Bbc Brown Boveri & Cie Cooled metal combustion chamber for generating heating and propellant gases.
US2775094A (en) * 1953-12-03 1956-12-25 Gen Electric End cap for fluid fuel combustor
US3154914A (en) * 1959-12-12 1964-11-03 Bolkow Entwicklungen Kg Rocket engine construction
US3545202A (en) * 1969-04-02 1970-12-08 United Aircraft Corp Wall structure and combustion holes for a gas turbine engine
US3572031A (en) * 1969-07-11 1971-03-23 United Aircraft Corp Variable area cooling passages for gas turbine burners

Also Published As

Publication number Publication date
IL37773A (en) 1974-01-14
BE774560A (en) 1972-02-14
CH534847A (en) 1973-03-15
FR2111931B1 (en) 1976-02-13
FR2111931A1 (en) 1972-06-09
DE2147135A1 (en) 1972-05-04
GB1314666A (en) 1973-04-26
US3706203A (en) 1972-12-19
AU3490971A (en) 1973-05-03
NL7113326A (en) 1972-05-03
CA938797A (en) 1973-12-25

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