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GB1368770A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
GB1368770A
GB1368770A GB5138571A GB5138571A GB1368770A GB 1368770 A GB1368770 A GB 1368770A GB 5138571 A GB5138571 A GB 5138571A GB 5138571 A GB5138571 A GB 5138571A GB 1368770 A GB1368770 A GB 1368770A
Authority
GB
United Kingdom
Prior art keywords
turbine
piston
annular
nozzle
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
GB5138571A
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.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of GB1368770A publication Critical patent/GB1368770A/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

Landscapes

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

Abstract

1368770 Gas turbine engines; turbine nozzles MOTOREN-UND TURBINEN-UNION MUNCHEN GmbH 4 Nov 1971 [7 Nov 1970] 51385/71 Heading FIT The invention relates to the mounting of a turbine nozzle of a gas turbine engine, the nozzle comprising guide vanes 6 and inner and outer shroud members 7 and 5. The inner shroud 7 is connected to turbine stator structure 8 while the outer shroud 5 is formed with an annular flange 15 which is received within an annular groove 16 formed in annular piston 13 whereby relative radial movement is permitted. The annular piston 13 is mounted for axial movement within a casing portion 3 which extends between the gas duct 9 and the flanged member 12 secured to the power turbine stator casing 4. The piston 13 is formed with an extension 14 which extends into a groove formed in stator casing 4. A piston ring seal 10 is disposed between the extension 14 and the member 12. The arrangement is such that the upstream surface of the annular piston is subjected to the pressure prevailing upstream of the turbine nozzle while the downstream face is subjected in part to compressor discharge pressure PV which is communicated to the space 17 through port 16 and in part to pressure prevailing downstream of the turbine.
GB5138571A 1970-11-07 1971-11-04 Gas turbine engine Expired GB1368770A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19702054926 DE2054926B2 (en) 1970-11-07 1970-11-07 MOUNTING A TURBINE WREAR

Publications (1)

Publication Number Publication Date
GB1368770A true GB1368770A (en) 1974-10-02

Family

ID=5787498

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5138571A Expired GB1368770A (en) 1970-11-07 1971-11-04 Gas turbine engine

Country Status (4)

Country Link
US (1) US3765791A (en)
DE (1) DE2054926B2 (en)
FR (1) FR2112872A5 (en)
GB (1) GB1368770A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6884026B2 (en) * 2002-09-30 2005-04-26 General Electric Company Turbine engine shroud assembly including axially floating shroud segment

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4274805A (en) * 1978-10-02 1981-06-23 United Technologies Corporation Floating vane support
US4478551A (en) * 1981-12-08 1984-10-23 United Technologies Corporation Turbine exhaust case design
US4566851A (en) * 1984-05-11 1986-01-28 United Technologies Corporation First stage turbine vane support structure
US4815933A (en) * 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US4883405A (en) * 1987-11-13 1989-11-28 The United States Of America As Represented By The Secretary Of The Air Force Turbine nozzle mounting arrangement
US6910853B2 (en) * 2002-11-27 2005-06-28 General Electric Company Structures for attaching or sealing a space between components having different coefficients or rates of thermal expansion
US8172522B2 (en) * 2008-03-31 2012-05-08 General Electric Company Method and system for supporting stator components
US8092163B2 (en) * 2008-03-31 2012-01-10 General Electric Company Turbine stator mount
US9506356B2 (en) * 2013-03-15 2016-11-29 Rolls-Royce North American Technologies, Inc. Composite retention feature
US9840933B2 (en) * 2014-12-19 2017-12-12 Schlumberger Technology Corporation Apparatus for extending the flow range of turbines
GB201616197D0 (en) * 2016-09-23 2016-11-09 Rolls Royce Plc Gas turbine engine
CN112302738B (en) * 2020-09-30 2023-03-07 北京航天动力研究所 Flexible and force classification method for high-pressure turbine air inlet shell structure

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3129922A (en) * 1961-11-27 1964-04-21 Frederick A Rosenthal Self centering ring seal
US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal
GB1277212A (en) * 1968-09-26 1972-06-07 Rolls Royce A sealing device
US3520635A (en) * 1968-11-04 1970-07-14 Avco Corp Turbomachine shroud assembly

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6884026B2 (en) * 2002-09-30 2005-04-26 General Electric Company Turbine engine shroud assembly including axially floating shroud segment

Also Published As

Publication number Publication date
US3765791A (en) 1973-10-16
DE2054926A1 (en) 1972-02-03
FR2112872A5 (en) 1972-06-23
DE2054926B2 (en) 1972-02-03

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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