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GB1089660A - Gas turbine engine combustion equipment - Google Patents

Gas turbine engine combustion equipment

Info

Publication number
GB1089660A
GB1089660A GB1808166A GB1808166A GB1089660A GB 1089660 A GB1089660 A GB 1089660A GB 1808166 A GB1808166 A GB 1808166A GB 1808166 A GB1808166 A GB 1808166A GB 1089660 A GB1089660 A GB 1089660A
Authority
GB
United Kingdom
Prior art keywords
dogs
gas turbine
platform
turbine engine
flame tube
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
GB1808166A
Inventor
George Pask
Roy Thornhill
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB1808166A priority Critical patent/GB1089660A/en
Publication of GB1089660A publication Critical patent/GB1089660A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,089,660. Gas turbine blade mounting. ROLLS-ROYCE Ltd. April 25, 1966, No.18081/66. Heading F1T. Each nozzle guide blade 17 in a gas turbine engine is supported from the annular flame tube 25 by engagement of flanges 32 and 35 on the respective outer and inner platforms 30, 31 with annular recesses 33, 36 at the downstream end of the flame tube so that the blades move radially with the flame tube but with axial freedom at their upstream ends. The downstream end of each platform 30 is located circumferentially and axially by engagement of dogs 40 on the platform between annular members 41, 42 bolted to the outer casing 14, member 41 also being provided with dogs. The dogs 40 have a limited degree of radial freedom in the recess 43 between members 41, 42. Each platform 31 is similarly located by dogs 45 engaged between dogs on a flange 46 carried by the inner casing 26.
GB1808166A 1966-04-25 1966-04-25 Gas turbine engine combustion equipment Expired GB1089660A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1808166A GB1089660A (en) 1966-04-25 1966-04-25 Gas turbine engine combustion equipment

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1808166A GB1089660A (en) 1966-04-25 1966-04-25 Gas turbine engine combustion equipment

Publications (1)

Publication Number Publication Date
GB1089660A true GB1089660A (en) 1967-11-01

Family

ID=10106341

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1808166A Expired GB1089660A (en) 1966-04-25 1966-04-25 Gas turbine engine combustion equipment

Country Status (1)

Country Link
GB (1) GB1089660A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5249921A (en) * 1991-12-23 1993-10-05 General Electric Company Compressor outlet guide vane support
WO2005054632A1 (en) * 2003-12-03 2005-06-16 Pratt & Whitney Canada Corp. Sliding joint between combustor wall and nozzle platform
EP1607582A1 (en) * 2004-06-17 2005-12-21 Snecma Moteurs Mounting of a gas turbine combustor with integrated turbine inlet guide conduit
WO2010023172A1 (en) * 2008-08-26 2010-03-04 Snecma Turbomachine improved high-pressure turbine, associated guide vanes sector and associated aircraft engine
US7836702B2 (en) 2006-09-15 2010-11-23 Pratt & Whitney Canada Corp. Gas turbine combustor exit duct and HP vane interface

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5249921A (en) * 1991-12-23 1993-10-05 General Electric Company Compressor outlet guide vane support
US7000406B2 (en) 2003-12-03 2006-02-21 Pratt & Whitney Canada Corp. Gas turbine combustor sliding joint
WO2005054632A1 (en) * 2003-12-03 2005-06-16 Pratt & Whitney Canada Corp. Sliding joint between combustor wall and nozzle platform
RU2368790C2 (en) * 2004-06-17 2009-09-27 Снекма Gas turbine with combustion chamber fixed to nozzle block
FR2871845A1 (en) * 2004-06-17 2005-12-23 Snecma Moteurs Sa GAS TURBINE COMBUSTION CHAMBER ASSEMBLY WITH INTEGRATED HIGH PRESSURE TURBINE DISPENSER
US7237388B2 (en) 2004-06-17 2007-07-03 Snecma Assembly comprising a gas turbine combustion chamber integrated with a high pressure turbine nozzle
EP1607582A1 (en) * 2004-06-17 2005-12-21 Snecma Moteurs Mounting of a gas turbine combustor with integrated turbine inlet guide conduit
US7836702B2 (en) 2006-09-15 2010-11-23 Pratt & Whitney Canada Corp. Gas turbine combustor exit duct and HP vane interface
US8166767B2 (en) 2006-09-15 2012-05-01 Pratt & Whitney Canada Corp. Gas turbine combustor exit duct and hp vane interface
WO2010023172A1 (en) * 2008-08-26 2010-03-04 Snecma Turbomachine improved high-pressure turbine, associated guide vanes sector and associated aircraft engine
FR2935430A1 (en) * 2008-08-26 2010-03-05 Snecma IMPROVED TURBOMACHINE HIGH-PRESSURE TURBINE, DISPENSER SECTOR AND AIRCRAFT ENGINE
CN102132009A (en) * 2008-08-26 2011-07-20 斯奈克玛公司 Turbomachine improved high-pressure turbine, associated guide vanes sector and associated aircraft engine
US8858169B2 (en) 2008-08-26 2014-10-14 Snecma High-pressure turbine for turbomachine, associated guide vane sector and aircraft engine
CN102132009B (en) * 2008-08-26 2015-04-01 斯奈克玛公司 Turbomachine high-pressure turbine, associated guide vanes sector,flange and associated aircraft engine

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