GB1335145A - Turbine casing for a gas turbine engine - Google Patents

Turbine casing for a gas turbine engine

Info

Publication number
GB1335145A
GB1335145A GB136572A GB1335145DA GB1335145A GB 1335145 A GB1335145 A GB 1335145A GB 136572 A GB136572 A GB 136572A GB 1335145D A GB1335145D A GB 1335145DA GB 1335145 A GB1335145 A GB 1335145A
Authority
GB
United Kingdom
Prior art keywords
supported
flange
struts
guide vanes
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
GB136572A
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
Publication of GB1335145A publication Critical patent/GB1335145A/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator

Landscapes

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

Abstract

1335145 Gas turbine blade shrouding ROLLSROYCE (1971) Ltd 12 Jan 1972 1365/72 Heading FIT Gas turbine rotor blades 29 are surrounded by a stationary annular shroud formed by a series of arcuate segments 28 each supported from a cylindrical casing member 26 by circumferentially spaced struts 27. To permit thermal expansion the latter are resilient and relatively thin with the exception of the central strut of each set. Casing member 26 is itself supported by a flange 24 from outer casing 22. Flange 24 also supports nozzle guide vanes 20, a further stage of guide vanes 32 being supported from member 26 by flange 31. Further shroud segments 36 supported by struts 35 surround lower-pressure rotor blades 33. The shafts 18, 17 of respective rotor discs 30, 34 run in bearings 23, 29 supported by struts 21, 38 passing through guide vanes 20, 37.
GB136572A 1972-01-12 1972-01-12 Turbine casing for a gas turbine engine Expired GB1335145A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB136572 1972-01-12

Publications (1)

Publication Number Publication Date
GB1335145A true GB1335145A (en) 1973-10-24

Family

ID=9720760

Family Applications (1)

Application Number Title Priority Date Filing Date
GB136572A Expired GB1335145A (en) 1972-01-12 1972-01-12 Turbine casing for a gas turbine engine

Country Status (6)

Country Link
US (1) US3824031A (en)
JP (1) JPS549247B2 (en)
DE (1) DE2300354C3 (en)
FR (1) FR2167837B1 (en)
GB (1) GB1335145A (en)
IT (1) IT973079B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2282856A (en) * 1993-10-15 1995-04-19 United Technologies Corp Reducing stress on the tips of turbine or compressor blades

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4248569A (en) * 1978-11-13 1981-02-03 General Motors Corporation Stator mounting
DE2907748C2 (en) * 1979-02-28 1987-02-12 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Device for minimising and maintaining constant the blade tip clearance of an axial-flow high-pressure turbine of a gas turbine engine
DE2907749C2 (en) * 1979-02-28 1985-04-25 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Device for minimizing constant maintenance of the blade tip clearance that exists in axial turbines of gas turbine engines
GB2051962B (en) * 1979-06-30 1982-12-15 Rolls Royce Turbine shroud ring support
DE3018621C2 (en) * 1980-05-16 1982-06-03 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Outer casing for axial compressors or turbines of flow machines, in particular gas turbine engines
FR2577282B1 (en) * 1985-02-13 1987-04-17 Snecma TURBOMACHINE HOUSING ASSOCIATED WITH A DEVICE FOR ADJUSTING THE GAME BETWEEN ROTOR AND STATOR
FR2607198B1 (en) * 1986-11-26 1990-05-04 Snecma COMPRESSOR HOUSING SUITABLE FOR ACTIVE PILOTAGE OF ITS EXPANSIONS AND MANUFACTURING METHOD THEREOF
US4987736A (en) * 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
US4989406A (en) * 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
GB2388407B (en) * 2002-05-10 2005-10-26 Rolls Royce Plc Gas turbine blade tip clearance control structure
JP6441611B2 (en) * 2014-08-25 2018-12-19 三菱日立パワーシステムズ株式会社 Gas turbine exhaust member and exhaust chamber maintenance method
US10830097B2 (en) 2016-02-04 2020-11-10 General Electric Company Engine casing with internal coolant flow patterns
US20200072070A1 (en) * 2018-09-05 2020-03-05 United Technologies Corporation Unified boas support and vane platform

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US841650A (en) * 1903-04-29 1907-01-15 Gen Electric Means for decreasing leakage in turbines.
NL103792C (en) * 1954-12-16
GB856599A (en) * 1958-06-16 1960-12-21 Gen Motors Corp Improvements relating to axial-flow compressors

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2282856A (en) * 1993-10-15 1995-04-19 United Technologies Corp Reducing stress on the tips of turbine or compressor blades
GB2282856B (en) * 1993-10-15 1998-05-13 United Technologies Corp Method and apparatus for reducing stress on the tips of turbine or compressor blades

Also Published As

Publication number Publication date
FR2167837B1 (en) 1977-04-22
FR2167837A1 (en) 1973-08-24
JPS4880906A (en) 1973-10-30
US3824031A (en) 1974-07-16
DE2300354B2 (en) 1974-06-20
JPS549247B2 (en) 1979-04-23
DE2300354C3 (en) 1975-02-06
IT973079B (en) 1974-06-10
DE2300354A1 (en) 1973-07-26

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee