GB1052324A - - Google Patents

Info

Publication number
GB1052324A
GB1052324A GB1052324DA GB1052324A GB 1052324 A GB1052324 A GB 1052324A GB 1052324D A GB1052324D A GB 1052324DA GB 1052324 A GB1052324 A GB 1052324A
Authority
GB
United Kingdom
Prior art keywords
blade
beams
casing
gas turbine
blades
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.)
Active
Application number
Publication of GB1052324A publication Critical patent/GB1052324A/en
Active 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
    • 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
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,052,324. Gas turbine engine blade mounting. ROLLS-ROYCE Ltd. May 19, 1965, No.21121/65. Heading F1T. The turbine or compressor stator blades 6 in a gas turbine engine are supported by a tubular member 8 attached at its upstream end to the engine casing 5 by bolts 12. The member 8 comprises axially spaced tubular end portions 9, 10 connected by circumferentially spaced flexible "beams" 11, Fig. 3 (not shown), inclined to the axis of the member 8. A projection 14 on each blade platform 13 is welded to a corresponding projection 15 on a beam so that each blade 6 is capable of limited individual radial movement and the maximum bending stresses in the beams on either side of the blades are substantially equal. The tubular end portion 10 has projections 16 and 18 co-operating respectively with the casing 5 and the platforms 13 of the downstream stator blades to reduce gas leakage.
GB1052324D Active GB1052324A (en)

Publications (1)

Publication Number Publication Date
GB1052324A true GB1052324A (en)

Family

ID=1756948

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1052324D Active GB1052324A (en)

Country Status (1)

Country Link
GB (1) GB1052324A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999031357A1 (en) * 1997-12-17 1999-06-24 Pratt & Whitney Canada Corp. Support for a turbine stator assembly
WO2005003519A1 (en) * 2003-07-04 2005-01-13 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
US6962482B2 (en) 2003-07-04 2005-11-08 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999031357A1 (en) * 1997-12-17 1999-06-24 Pratt & Whitney Canada Corp. Support for a turbine stator assembly
WO2005003519A1 (en) * 2003-07-04 2005-01-13 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
US6962482B2 (en) 2003-07-04 2005-11-08 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
CN1816683B (en) * 2003-07-04 2010-04-21 石川岛播磨重工业株式会社 Turbine shroud segment

Similar Documents

Publication Publication Date Title
CA2363669C (en) Turbine interstage sealing ring
US5271714A (en) Turbine nozzle support arrangement
US6260269B1 (en) Method for overhauling a steam turbine to increase its power
US5249920A (en) Turbine nozzle seal arrangement
US5289677A (en) Combined support and seal ring for a combustor
US7229249B2 (en) Lightweight annular interturbine duct
US6783324B2 (en) Compressor bleed case
US7229247B2 (en) Duct with integrated baffle
US4907944A (en) Turbomachinery blade mounting arrangement
US4391565A (en) Nozzle guide vane assemblies for turbomachines
US4863343A (en) Turbine vane shroud sealing system
US4502276A (en) Casing structure for a gas turbine engine
EP3564515B1 (en) Flow mixer stiffener ring springs
JP2947582B2 (en) Steam turbine
US4272955A (en) Diffusing means
JP4341294B2 (en) Cradle-supported turbine nozzle
US20090123275A1 (en) Apparatus for eliminating compressor stator vibration induced by TIP leakage vortex bursting
JPH0670378B2 (en) Transition duct seal structure
GB790854A (en) Improvements in or relating to axial-flow fluid machines
US20200400030A1 (en) Turbomachine sealing system and turbomachine including the sealing system
US4627233A (en) Stator assembly for bounding the working medium flow path of a gas turbine engine
GB1052324A (en)
US11053817B2 (en) Turbine shroud assembly with ceramic matrix composite blade track segments and full hoop carrier
US4725199A (en) Snap ring construction
US3364678A (en) Means for stabilizing fluid flow in diffuser-combustor systems in axial flow gas turbine engines