GB1303962A - - Google Patents

Info

Publication number
GB1303962A
GB1303962A GB1970171*[A GB1970171A GB1303962A GB 1303962 A GB1303962 A GB 1303962A GB 1970171 A GB1970171 A GB 1970171A GB 1303962 A GB1303962 A GB 1303962A
Authority
GB
United Kingdom
Prior art keywords
openings
end wall
array
smaller
diameter
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
GB1970171*[A
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 GB1303962A publication Critical patent/GB1303962A/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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Abstract

1303962 Gas turbine combustion apparatus WESTINGHOUSE ELECTRIC CORP 9 June 1971 [17 July 1970] 19701/71 Heading F1L Combustion apparatus for a gas turbine plant comprises, Figs.1, 3, a cylindrical casing 19 divided into upper and lower halves 20, 21 surrounding an annular array of flame tubes 30 and having an upstream annular end wall 22 provided with an array of circular openings 35 through each of which fuel is supplied to an associated flame tube 30, the diameter of at least alternate openings 35 being smaller than the maximum outer diameter of the corresponding flame tubes. In Figs.1, 3 all the openings 35 are smaller and thus a flame tube 30 can only be removed after first removing the upper casing half 20. In a modification, Fig. 8, the array of openings in annular end wall 90 consists of openings 98 of larger diameter than the associated flame tubes 92 and alternating with smaller diameter openings. Openings 98 are normally closed by plates 97 having holes 94 for fuel supply means. Thus flame tubes 92 can be removed through openings 98 without removing the upper casing half. Further minor modifications concerning the disposition of the end wall openings in relation to the horizontal casing joining flanges are described.
GB1970171*[A 1970-07-17 1971-06-09 Expired GB1303962A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US5582170A 1970-07-17 1970-07-17

Publications (1)

Publication Number Publication Date
GB1303962A true GB1303962A (en) 1973-01-24

Family

ID=22000363

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1970171*[A Expired GB1303962A (en) 1970-07-17 1971-06-09

Country Status (8)

Country Link
US (1) US3657883A (en)
JP (1) JPS5023450B1 (en)
CA (1) CA918937A (en)
CH (1) CH541716A (en)
DE (1) DE2133256A1 (en)
FR (1) FR2099438B1 (en)
GB (1) GB1303962A (en)
NL (1) NL7109893A (en)

Families Citing this family (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3742704A (en) * 1971-07-13 1973-07-03 Westinghouse Electric Corp Combustion chamber support structure
US4720970A (en) * 1982-11-05 1988-01-26 The United States Of America As Represented By The Secretary Of The Air Force Sector airflow variable geometry combustor
JPS61195214A (en) * 1985-02-22 1986-08-29 Hitachi Ltd Air flow part adjusting device for gas turbine combustor
US5233822A (en) * 1991-01-31 1993-08-10 General Electric Company Method and system for the disassembly of an annular combustor
US5983641A (en) * 1997-04-30 1999-11-16 Mitsubishi Heavy Industries, Ltd. Tail pipe of gas turbine combustor and gas turbine combustor having the same tail pipe
US6691519B2 (en) * 2000-02-18 2004-02-17 Siemens Westinghouse Power Corporation Adaptable modular gas turbine power plant
US6672073B2 (en) 2002-05-22 2004-01-06 Siemens Westinghouse Power Corporation System and method for supporting fuel nozzles in a gas turbine combustor utilizing a support plate
US7200987B2 (en) * 2004-06-18 2007-04-10 General Electric Company Off-axis pulse detonation configuration for gas turbine engine
US7509807B2 (en) * 2004-08-13 2009-03-31 Siemens Energy, Inc. Concentric catalytic combustor
US8109098B2 (en) * 2006-05-04 2012-02-07 Siemens Energy, Inc. Combustor liner for gas turbine engine
EP2119966A1 (en) * 2008-05-15 2009-11-18 ALSTOM Technology Ltd Combustor with reduced carbon monoxide emissions
US7874138B2 (en) * 2008-09-11 2011-01-25 Siemens Energy, Inc. Segmented annular combustor
US8938976B2 (en) * 2011-05-20 2015-01-27 Siemens Energy, Inc. Structural frame for gas turbine combustion cap assembly
US20140083111A1 (en) * 2012-09-25 2014-03-27 United Technologies Corporation Gas turbine asymmetric fuel nozzle combustor
US9546601B2 (en) * 2012-11-20 2017-01-17 General Electric Company Clocked combustor can array
EP3015770B1 (en) * 2014-11-03 2020-07-01 Ansaldo Energia Switzerland AG Can combustion chamber
JP6625427B2 (en) * 2015-12-25 2019-12-25 川崎重工業株式会社 Gas turbine engine
US10641491B2 (en) 2016-03-25 2020-05-05 General Electric Company Cooling of integrated combustor nozzle of segmented annular combustion system
US10584876B2 (en) 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system
US10584880B2 (en) 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in a segmented annular combustion system
US10830442B2 (en) 2016-03-25 2020-11-10 General Electric Company Segmented annular combustion system with dual fuel capability
US10724441B2 (en) 2016-03-25 2020-07-28 General Electric Company Segmented annular combustion system
US11428413B2 (en) 2016-03-25 2022-08-30 General Electric Company Fuel injection module for segmented annular combustion system
US10605459B2 (en) 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10563869B2 (en) 2016-03-25 2020-02-18 General Electric Company Operation and turndown of a segmented annular combustion system
US10520194B2 (en) 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for a segmented annular combustion system
US10690350B2 (en) 2016-11-28 2020-06-23 General Electric Company Combustor with axially staged fuel injection
US11156362B2 (en) 2016-11-28 2021-10-26 General Electric Company Combustor with axially staged fuel injection
US11015812B2 (en) * 2018-05-07 2021-05-25 Rolls-Royce North American Technologies Inc. Combustor bolted segmented architecture
RU2710642C1 (en) * 2018-11-15 2019-12-30 Публичное Акционерное Общество "Одк-Сатурн" Tubular combustion chamber of gas turbine engine
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE806613C (en) * 1947-02-24 1951-06-14 Cem Comp Electro Mec Arrangement of the combustion chambers of gas turbines
US2674090A (en) * 1950-03-21 1954-04-06 United Aircraft Corp Combustion chamber for gas turbines
DE1117348B (en) * 1954-02-27 1961-11-16 United Aircraft Corp Gas turbine engine
US3044263A (en) * 1959-05-21 1962-07-17 Dresser Ind Combustor with unitary liner
US3169367A (en) * 1963-07-18 1965-02-16 Westinghouse Electric Corp Combustion apparatus

Also Published As

Publication number Publication date
US3657883A (en) 1972-04-25
DE2133256A1 (en) 1972-01-20
FR2099438A1 (en) 1972-03-17
CA918937A (en) 1973-01-16
FR2099438B1 (en) 1975-07-11
JPS5023450B1 (en) 1975-08-07
NL7109893A (en) 1972-01-19
CH541716A (en) 1973-09-15

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees