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GB1188887A - Turbine Vane Retaining Construction. - Google Patents

Turbine Vane Retaining Construction.

Info

Publication number
GB1188887A
GB1188887A GB28434/68A GB2843468A GB1188887A GB 1188887 A GB1188887 A GB 1188887A GB 28434/68 A GB28434/68 A GB 28434/68A GB 2843468 A GB2843468 A GB 2843468A GB 1188887 A GB1188887 A GB 1188887A
Authority
GB
United Kingdom
Prior art keywords
ring
flange
blade
casing
flanges
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
GB28434/68A
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.)
RTX Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB1188887A publication Critical patent/GB1188887A/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)
  • Control Of Turbines (AREA)

Abstract

1,188,887. Stator blade fixing. UNITED AIRCRAFT CORP. June 14, 1968 [July 17, 1967], No.28434/68. Heading F1T. Turbine nozzle guide blades 4 of a gas turbine engine are mounted between outer and inner casings 8, 10 for easy disassembly by means of flanges 14, 16 at the outer end 12 of each blade and L- shaped flanges 36, 38 at the inner end 34. Each outer end 12 is located by the co-operation of flange 16 with a flange 20 on the casing 8 and by a ring 26 bolted to a flange 18 on casing 8, the ring having holes 28 in alignment with corresponding holes in the flange 14 containing locating means 32. The inner end 34 of each blade engages within a retaining ring 44 by means of flanges 36, 38 and a lug 42 engaging a corresponding slot in the ring. The latter in turn is positioned within a channel 50 defined by a flange 52 on the inner casing 10. Thus an individual blade 4 can be removed by removing ring 26, moving retaining ring 44 axially forward to disengage channel 50 and then removing the blade from the ring 44.
GB28434/68A 1967-07-17 1968-06-14 Turbine Vane Retaining Construction. Expired GB1188887A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US65371667A 1967-07-17 1967-07-17

Publications (1)

Publication Number Publication Date
GB1188887A true GB1188887A (en) 1970-04-22

Family

ID=24622038

Family Applications (1)

Application Number Title Priority Date Filing Date
GB28434/68A Expired GB1188887A (en) 1967-07-17 1968-06-14 Turbine Vane Retaining Construction.

Country Status (5)

Country Link
US (1) US3423071A (en)
DE (1) DE1751567A1 (en)
FR (1) FR1576055A (en)
GB (1) GB1188887A (en)
SE (1) SE343916B (en)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE411931B (en) * 1975-03-25 1980-02-11 United Technologies Corp DEVICE AT THE TURBINE NOZZLE FOR GAS TURBINE ENGINE
US3992126A (en) * 1975-03-25 1976-11-16 United Technologies Corporation Turbine cooling
US3957391A (en) * 1975-03-25 1976-05-18 United Technologies Corporation Turbine cooling
US4011718A (en) * 1975-08-01 1977-03-15 United Technologies Corporation Gas turbine construction
US4431373A (en) * 1980-05-16 1984-02-14 United Technologies Corporation Flow directing assembly for a gas turbine engine
US4511306A (en) * 1982-02-02 1985-04-16 Westinghouse Electric Corp. Combustion turbine single airfoil stator vane structure
DE3333436C1 (en) * 1983-09-16 1985-02-14 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Device for the axial and circumferential securing of static housing components for flow machines
US4712979A (en) * 1985-11-13 1987-12-15 The United States Of America As Represented By The Secretary Of The Air Force Self-retained platform cooling plate for turbine vane
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
US5131813A (en) * 1990-04-03 1992-07-21 General Electric Company Turbine blade outer end attachment structure
US5131814A (en) * 1990-04-03 1992-07-21 General Electric Company Turbine blade inner end attachment structure
US5222360A (en) * 1991-10-30 1993-06-29 General Electric Company Apparatus for removably attaching a core frame to a vane frame with a stable mid ring
US5653580A (en) * 1995-03-06 1997-08-05 Solar Turbines Incorporated Nozzle and shroud assembly mounting structure
US5584654A (en) * 1995-12-22 1996-12-17 General Electric Company Gas turbine engine fan stator
US5961278A (en) * 1997-12-17 1999-10-05 Pratt & Whitney Canada Inc. Housing for turbine assembly
US6234750B1 (en) * 1999-03-12 2001-05-22 General Electric Company Interlocked compressor stator
US6364606B1 (en) 2000-11-08 2002-04-02 Allison Advanced Development Company High temperature capable flange
US6517313B2 (en) 2001-06-25 2003-02-11 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
US7094025B2 (en) * 2003-11-20 2006-08-22 General Electric Company Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction
FR2935430B1 (en) * 2008-08-26 2012-03-09 Snecma IMPROVED TURBOMACHINE HIGH-PRESSURE TURBINE, DISPENSER SECTOR AND AIRCRAFT ENGINE
EP2952693B1 (en) * 2014-06-06 2021-04-28 Raytheon Technologies Corporation Case with vane retention feature
CN108729957A (en) * 2018-03-26 2018-11-02 北京理工大学 A kind of sound compartment end-clearance-free turbine nozzle ring blade assembly
US11674400B2 (en) * 2021-03-12 2023-06-13 Ge Avio S.R.L. Gas turbine engine nozzles
US12492640B2 (en) * 2024-05-30 2025-12-09 General Electric Company Turbine engine including a vane support and a vane

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE487115A (en) * 1946-04-05
GB618525A (en) * 1946-06-18 1949-02-23 Adrian Albert Lombard Improvements in or relating to gas-turbine engines
NL104794C (en) * 1957-08-16
NL99435C (en) * 1957-08-22
US3062499A (en) * 1960-05-18 1962-11-06 United Aircraft Corp Vane mounting and seal
US3075744A (en) * 1960-08-16 1963-01-29 United Aircraft Corp Turbine nozzle vane mounting means
GB1086432A (en) * 1965-09-21 1967-10-11 Bristol Siddeley Engines Ltd Gas turbine engines
US3365173A (en) * 1966-02-28 1968-01-23 Gen Electric Stator structure

Also Published As

Publication number Publication date
SE343916B (en) 1972-03-20
FR1576055A (en) 1969-07-25
US3423071A (en) 1969-01-21
DE1751567A1 (en) 1971-12-23

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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