GB802370A - Improvements relating to exhaust reheaters for gas turbine jet engines - Google Patents

Improvements relating to exhaust reheaters for gas turbine jet engines

Info

Publication number
GB802370A
GB802370A GB5477/55A GB547755A GB802370A GB 802370 A GB802370 A GB 802370A GB 5477/55 A GB5477/55 A GB 5477/55A GB 547755 A GB547755 A GB 547755A GB 802370 A GB802370 A GB 802370A
Authority
GB
United Kingdom
Prior art keywords
plates
exhaust
outer shell
flame tube
gas turbine
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
Application number
GB5477/55A
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
Priority claimed from US417192A external-priority patent/US2874536A/en
Application filed by General Electric Co filed Critical General Electric Co
Publication of GB802370A publication Critical patent/GB802370A/en
Expired 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
    • F23R3/002—Wall structures
    • 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
    • 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; Infra-red radiation suppressors
    • 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

Abstract

802,370. Jet propulsion plant. GENERAL ELECTRIC CO. Feb. 23, 1955 [March 18, 1954], No. 5477/55. Class 110 (3). [Also in Group XII] In a gas turbine jet propulsion engine, exhaust reheat combustion equipment comprises an outer shell 24 and a liner or flame tube disposed therein, the liner being formed of a number of plates 30 disposed in axial and circumferential rows, the plates being supported on axially-directed I-section beams 26 spaced circumferentially within the outer shell. The plates 30 are bowed inwardly to permit relative circumferential expansion, and the plates are formed with louvres 32 by means of which air or gas may be directed inwardly from the annular space between the outer shell and the flame tube to flow adjacent the inner surface of the flame tube so as to cool it. The plates 30 may overlap in the axial direction to permit relative axial expansion. Reheat fuel is supplied through injectors 20 and a flame holder 22 is supported at the downstream end of the exhaust cone 15. The cooling gas may be exhaust gases discharged from the turbine. It is stated that the reheater construction prevents "screech."
GB5477/55A 1954-02-23 1955-02-23 Improvements relating to exhaust reheaters for gas turbine jet engines Expired GB802370A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US803813XA 1954-02-23 1954-02-23
US417192A US2874536A (en) 1954-03-18 1954-03-18 Cooling means for tailpipe

Publications (1)

Publication Number Publication Date
GB802370A true GB802370A (en) 1958-10-01

Family

ID=26763440

Family Applications (2)

Application Number Title Priority Date Filing Date
GB5477/55A Expired GB802370A (en) 1954-02-23 1955-02-23 Improvements relating to exhaust reheaters for gas turbine jet engines
GB5476/55A Expired GB803813A (en) 1954-02-23 1955-02-23 Improvements relating to exhaust reheaters for gas turbine jet engines

Family Applications After (1)

Application Number Title Priority Date Filing Date
GB5476/55A Expired GB803813A (en) 1954-02-23 1955-02-23 Improvements relating to exhaust reheaters for gas turbine jet engines

Country Status (4)

Country Link
BE (1) BE535906A (en)
CH (2) CH335303A (en)
DE (2) DE1045180B (en)
GB (2) GB802370A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4833881A (en) * 1984-12-17 1989-05-30 General Electric Company Gas turbine engine augmentor
EP1677050A2 (en) * 2004-12-29 2006-07-05 United Technologies Corporation Augmentor liner

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3085401A (en) * 1959-01-22 1963-04-16 Rolls Royce Reheat combustion equipment of gas-turbine engines
DE1221053B (en) * 1960-06-11 1966-07-14 Rolls Royce Turbine jet engine
DE1210628B (en) * 1962-02-08 1966-02-10 Rolls Royce Jet pipe for recoil engines, for example for the gas turbine jet engine of an aircraft
GB1102572A (en) * 1964-06-06 1968-02-07 Bristol Siddeley Engines Ltd Jet propulsion engines
US3307354A (en) * 1965-10-01 1967-03-07 Gen Electric Cooling structure for overlapped panels
GB1157930A (en) * 1966-12-28 1969-07-09 Rolls Royce Gas Turbine Jet Propulsion Engine

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH214477A (en) * 1939-01-30 1941-04-30 Bbc Brown Boveri & Cie Cooling device on pipes, containers, housings or the like through which hot gases flow or which include them.
US2458497A (en) * 1945-05-05 1949-01-11 Babcock & Wilcox Co Combustion chamber
FR962862A (en) * 1946-10-26 1950-06-22
CH255541A (en) * 1947-05-12 1948-06-30 Bbc Brown Boveri & Cie Cooled metal combustion chamber for generating heating and propellant gases.
NL72931C (en) * 1948-02-21
US2508420A (en) * 1948-09-21 1950-05-23 Westinghouse Electric Corp Combustion apparatus
US2547619A (en) * 1948-11-27 1951-04-03 Gen Electric Combustor with sectional housing and liner
US2632299A (en) * 1949-06-17 1953-03-24 United Aircraft Corp Precombustion chamber
DE825777C (en) * 1949-08-19 1951-12-20 Canadian Patents Dev Flame tube of combustion chambers, especially for gas turbines
GB700004A (en) * 1949-12-12 1953-11-25 Babcock & Wilcox Ltd Improvements in or relating to combustion apparatus
DE889240C (en) * 1950-10-17 1953-09-10 Canadian Patents Dev Flame tube of combustion chambers, especially for gas turbine engines
US2651912A (en) * 1950-10-31 1953-09-15 Gen Electric Combustor and cooling means therefor
FR1002312A (en) * 1951-04-01 1952-03-05 Combustion chamber for thermo-propellants, turbo-engines or the like

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4833881A (en) * 1984-12-17 1989-05-30 General Electric Company Gas turbine engine augmentor
EP1677050A2 (en) * 2004-12-29 2006-07-05 United Technologies Corporation Augmentor liner
EP1677050A3 (en) * 2004-12-29 2009-09-23 United Technologies Corporation Augmentor liner

Also Published As

Publication number Publication date
DE1021208B (en) 1957-12-19
GB803813A (en) 1958-11-05
BE535906A (en)
CH335303A (en) 1958-12-31
CH331332A (en) 1958-07-15
DE1045180B (en) 1958-11-27

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