GB1476414A - Combustion apparatus for a gas turbine engine - Google Patents

Combustion apparatus for a gas turbine engine

Info

Publication number
GB1476414A
GB1476414A GB1361075A GB1361075A GB1476414A GB 1476414 A GB1476414 A GB 1476414A GB 1361075 A GB1361075 A GB 1361075A GB 1361075 A GB1361075 A GB 1361075A GB 1476414 A GB1476414 A GB 1476414A
Authority
GB
United Kingdom
Prior art keywords
ring
flame tube
socket
abutment
cover
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
GB1361075A
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation 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 US458075A external-priority patent/US3910036A/en
Priority claimed from US458073A external-priority patent/US3911672A/en
Application filed by Motors Liquidation Co filed Critical Motors Liquidation Co
Publication of GB1476414A publication Critical patent/GB1476414A/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
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/264—Ignition
    • F02C7/266—Electric
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R2900/00012—Details of sealing devices

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1476414 Combustion apparatus for gas turbine engines GENERAL MOTORS CORP 3 April 1975 [5 April 1974(2)] 13610/75 Heading F1L Combustion apparatus for a gas turbine engine comprises a ceramic flame tube 2, Fig. 1, having a converging upstream wall 6 surrounding an opening 7, and an annular abutment 22 extending through opening 7 and bearing against the inner side of the flame tube wall, engagement being maintained by resilient means which may be a convoluted spring 32 seated on a rigid washer 34 interposed between an annular member 26, which may be connected to a cover 8, and the exterior of the flame tube to accommodate relative expansion between the flame tube and the supporting means. Fuel enters the combustion zone 12 via nozzle 14, air entering via ports 28, 30 and swirler 23, and also via ports 31, air for combustion and to cool spring 32 being guided by baffle 27 which also shields cover 8 from hot parts of the engine. Igniter 36 which is threaded into a socket 40 fixed to cover 8 extends into combustion zone 12 via port 47 sealed by a heat-resistant gasket 46 which may be of ceramic felt and is held in engagement with the flame tube by a spring-biased cylindrical guide 44 slidable within socket 40 to accommodate thermal expansion. The margin of socket 40 may be turned inward to engage a recess in guide 44 to prevent ejection of guide from socket. In a second embodiment, Fig. 3, the abutment consists of a cup-shaped ring 56 mounted between cover 8 and a ring 58, and the annular member is formed by a ring 59 lodged or welded in a recess 60 in baffle 27. An air swirler ring 62 is fixed to ring 58 extending outwardly to engage abutment ring 56. In a third embodiment, Fig. 4 (not shown), the abutment (68) and swirler 23 are integral with the nozzle 14, the resilient means being a coil spring (70).
GB1361075A 1974-04-05 1975-04-03 Combustion apparatus for a gas turbine engine Expired GB1476414A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US458075A US3910036A (en) 1974-04-05 1974-04-05 Igniter installation for combustor with ceramic liner
US458073A US3911672A (en) 1974-04-05 1974-04-05 Combustor with ceramic liner

Publications (1)

Publication Number Publication Date
GB1476414A true GB1476414A (en) 1977-06-16

Family

ID=27038849

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1361075A Expired GB1476414A (en) 1974-04-05 1975-04-03 Combustion apparatus for a gas turbine engine

Country Status (1)

Country Link
GB (1) GB1476414A (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4320428A1 (en) * 1993-06-21 1994-12-22 Abb Management Ag Probe lead-through for a combustion chamber
EP1096207A1 (en) 1999-10-27 2001-05-02 ABB Alstom Power UK Ltd. Combustor mounting for a gas turbine engine
EP1111219A2 (en) * 1999-12-21 2001-06-27 General Electric Company Mounting an igniter in an augmenter
WO2009056518A2 (en) * 2007-10-30 2009-05-07 Siemens Aktiengesellschaft Combustion chamber for gas turbines, including an igniter
EP1719949A3 (en) * 2005-04-27 2009-09-02 United Technologies Corporation Compliant metal support for ceramic combustor liner in a gas turbine engine
FR2956187A1 (en) * 2010-02-11 2011-08-12 Snecma Combustion chamber for turbine engine e.g. turbojet of airplane, has sealing unit whose ring is slidably mounted on spark plug and elastic unit biases ring over annular wall and ring sealably supported against end of chimney
CN102434893A (en) * 2010-08-24 2012-05-02 诺沃皮尼奥内有限公司 Combustor liner concentric support and method
WO2014137409A1 (en) * 2013-03-07 2014-09-12 Rolls-Royce Corporation Flexible bellows igniter seal for a gas turbine with a ceramic combustion liner
WO2015038274A1 (en) * 2013-09-11 2015-03-19 General Electric Company Spring loaded and sealed ceramic matrix composite combustor liner
WO2018009411A3 (en) * 2016-07-07 2018-02-01 General Electric Company Combustor damping assembly for a gas turbine engine
CN113494362A (en) * 2020-04-08 2021-10-12 中国航发商用航空发动机有限责任公司 Ignition electric nozzle mounting assembly, combustion chamber and aircraft engine

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4320428A1 (en) * 1993-06-21 1994-12-22 Abb Management Ag Probe lead-through for a combustion chamber
EP1096207A1 (en) 1999-10-27 2001-05-02 ABB Alstom Power UK Ltd. Combustor mounting for a gas turbine engine
US6453675B1 (en) 1999-10-27 2002-09-24 Abb Alstom Power Uk Ltd. Combustor mounting for gas turbine engine
EP1111219A2 (en) * 1999-12-21 2001-06-27 General Electric Company Mounting an igniter in an augmenter
EP1111219A3 (en) * 1999-12-21 2003-03-05 General Electric Company Mounting an igniter in an augmenter
EP2458282A1 (en) * 2005-04-27 2012-05-30 United Technologies Corporation Compliant metal support for ceramic combustor liner in a gas turbine engine
US7647779B2 (en) 2005-04-27 2010-01-19 United Technologies Corporation Compliant metal support for ceramic combustor liner in a gas turbine engine
US8122727B2 (en) 2005-04-27 2012-02-28 United Technologies Corporation Compliant metal support for ceramic combustor liner in a gas turbine engine
EP1719949A3 (en) * 2005-04-27 2009-09-02 United Technologies Corporation Compliant metal support for ceramic combustor liner in a gas turbine engine
WO2009056518A3 (en) * 2007-10-30 2010-05-14 Siemens Aktiengesellschaft Combustion chamber for gas turbines, including an igniter
WO2009056518A2 (en) * 2007-10-30 2009-05-07 Siemens Aktiengesellschaft Combustion chamber for gas turbines, including an igniter
FR2956187A1 (en) * 2010-02-11 2011-08-12 Snecma Combustion chamber for turbine engine e.g. turbojet of airplane, has sealing unit whose ring is slidably mounted on spark plug and elastic unit biases ring over annular wall and ring sealably supported against end of chimney
CN102434893A (en) * 2010-08-24 2012-05-02 诺沃皮尼奥内有限公司 Combustor liner concentric support and method
US9765698B2 (en) 2013-03-07 2017-09-19 Rolls-Royce Corporation Flexible bellows igniter seal
WO2014137409A1 (en) * 2013-03-07 2014-09-12 Rolls-Royce Corporation Flexible bellows igniter seal for a gas turbine with a ceramic combustion liner
WO2015038274A1 (en) * 2013-09-11 2015-03-19 General Electric Company Spring loaded and sealed ceramic matrix composite combustor liner
CN105518389A (en) * 2013-09-11 2016-04-20 通用电气公司 Spring loaded and sealed ceramic matrix composite combustor liner
CN105518389B (en) * 2013-09-11 2017-10-24 通用电气公司 Spring loads and sealed ceramic matrix composite combustion liner
US10436446B2 (en) 2013-09-11 2019-10-08 General Electric Company Spring loaded and sealed ceramic matrix composite combustor liner
WO2018009411A3 (en) * 2016-07-07 2018-02-01 General Electric Company Combustor damping assembly for a gas turbine engine
CN109477637A (en) * 2016-07-07 2019-03-15 通用电气公司 Burner assembly for turbogenerator
US10935242B2 (en) 2016-07-07 2021-03-02 General Electric Company Combustor assembly for a turbine engine
US11920789B2 (en) 2016-07-07 2024-03-05 General Electric Company Combustor assembly for a turbine engine
CN113494362A (en) * 2020-04-08 2021-10-12 中国航发商用航空发动机有限责任公司 Ignition electric nozzle mounting assembly, combustion chamber and aircraft engine
CN113494362B (en) * 2020-04-08 2022-12-16 中国航发商用航空发动机有限责任公司 Ignition electric nozzle mounting assembly, combustion chamber and aircraft engine

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee