SE9101655D0 - STATOR HAVING SELECTIVELY APPLIED THERMAL CONDUCTIVITY COATING - Google Patents

STATOR HAVING SELECTIVELY APPLIED THERMAL CONDUCTIVITY COATING

Info

Publication number
SE9101655D0
SE9101655D0 SE9101655A SE9101655A SE9101655D0 SE 9101655 D0 SE9101655 D0 SE 9101655D0 SE 9101655 A SE9101655 A SE 9101655A SE 9101655 A SE9101655 A SE 9101655A SE 9101655 D0 SE9101655 D0 SE 9101655D0
Authority
SE
Sweden
Prior art keywords
stator
thermal conductivity
axisymmetric
coating
distortion
Prior art date
Application number
SE9101655A
Other languages
Swedish (sv)
Other versions
SE9101655L (en
Inventor
L W Plemmons
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of SE9101655D0 publication Critical patent/SE9101655D0/en
Publication of SE9101655L publication Critical patent/SE9101655L/en

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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

A gas turbine engine stator 48 and method are disclosed which are effective for controlling non-axisymmetric radial running clearance variations between a stator flowpath surface 76 and rotor blade tips 74. A coating of higher or lower thermal conductivity than that of the stator is disposed along the circumference of the stator in such a way as to control thermally induced non-axisymmetric distortion and thereby control non-axisymmetric radial running clearance. In preferred embodiments of the invention, a high thermal conductivity coating eg of nickel may be applied to an annular flange 50 for reducing temperature gradients therein. In another embodiment of the present invention, low thermal conductivity coatings eg of ceramics may be applied to a stator to preferentially insulate parts of the stator for reducing thermal distortion. <IMAGE>
SE9101655A 1990-05-31 1991-05-30 STATOR WITH SELECTIVELY APPLIED THERMAL LEADING COATING SE9101655L (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US53128790A 1990-05-31 1990-05-31

Publications (2)

Publication Number Publication Date
SE9101655D0 true SE9101655D0 (en) 1991-05-30
SE9101655L SE9101655L (en) 1991-12-01

Family

ID=24117023

Family Applications (1)

Application Number Title Priority Date Filing Date
SE9101655A SE9101655L (en) 1990-05-31 1991-05-30 STATOR WITH SELECTIVELY APPLIED THERMAL LEADING COATING

Country Status (7)

Country Link
JP (1) JPH04231606A (en)
CA (1) CA2039756A1 (en)
DE (1) DE4117362A1 (en)
FR (1) FR2662741B1 (en)
GB (1) GB2244524B (en)
IT (1) IT1249317B (en)
SE (1) SE9101655L (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9210642D0 (en) * 1992-05-19 1992-07-08 Rolls Royce Plc Rotor shroud assembly
US5645399A (en) * 1995-03-15 1997-07-08 United Technologies Corporation Gas turbine engine case coated with thermal barrier coating to control axial airfoil clearance
GB2348466B (en) * 1999-03-27 2003-07-09 Rolls Royce Plc A gas turbine engine and a rotor for a gas turbine engine
US20050091984A1 (en) * 2003-11-03 2005-05-05 Robert Czachor Heat shield for gas turbine engine
US7246996B2 (en) * 2005-01-04 2007-07-24 General Electric Company Methods and apparatus for maintaining rotor assembly tip clearances
US8047763B2 (en) * 2008-10-30 2011-11-01 General Electric Company Asymmetrical gas turbine cooling port locations
EP2194236A1 (en) * 2008-12-03 2010-06-09 Siemens Aktiengesellschaft Turbine casing
US8197197B2 (en) * 2009-01-08 2012-06-12 General Electric Company Method of matching thermal response rates between a stator and a rotor and fluidic thermal switch for use therewith
US8231338B2 (en) * 2009-05-05 2012-07-31 General Electric Company Turbine shell with pin support
DE102013212741A1 (en) * 2013-06-28 2014-12-31 Siemens Aktiengesellschaft Gas turbine and heat shield for a gas turbine
GB201509771D0 (en) 2015-06-05 2015-07-22 Rolls Royce Plc Containment casing
CN114017134A (en) * 2021-11-12 2022-02-08 中国航发沈阳发动机研究所 Method for adjusting thermal deformation rate of casing by changing thermal capacity of casing

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1328426A (en) * 1971-08-28 1973-08-30 British Leyland Truck & Bus Gas turbine engines
BE792224A (en) * 1971-12-01 1973-03-30 Penny Robert N LONG COMPOSITE ELEMENT WITH A PREDETERMINED EFFECTIVE LINEAR EXPANSION COEFFICIENT
GB1501916A (en) * 1975-06-20 1978-02-22 Rolls Royce Matching thermal expansions of components of turbo-machines
GB2047354B (en) * 1979-04-26 1983-03-30 Rolls Royce Gas turbine engines
DE3019920C2 (en) * 1980-05-24 1982-12-30 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Device for the outer casing of the rotor blades of axial turbines for gas turbine engines
GB2062117B (en) * 1980-10-20 1983-05-05 Gen Electric Clearance control for turbine blades
US4433845A (en) * 1981-09-29 1984-02-28 United Technologies Corporation Insulated honeycomb seal
GB2115487B (en) * 1982-02-19 1986-02-05 Gen Electric Double wall compressor casing
DE3407945A1 (en) * 1984-03-03 1985-09-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München METHOD AND MEANS FOR AVOIDING THE DEVELOPMENT OF TITANIUM FIRE
FR2577281B1 (en) * 1985-02-13 1987-03-20 Snecma TURBOMACHINE HOUSING ASSOCIATED WITH A DEVICE FOR ADJUSTING THE GAP BETWEEN MOBILE BLADES AND HOUSING
JPS6267237A (en) * 1985-09-18 1987-03-26 Hitachi Ltd Two passage type exhaust gas driven turbo charger
US4764089A (en) * 1986-08-07 1988-08-16 Allied-Signal Inc. Abradable strain-tolerant ceramic coated turbine shroud
FR2646466B1 (en) * 1989-04-26 1991-07-05 Alsthom Gec INTERNAL STATOR HP-MP SINGLE STEAM TURBINE WITH CONTROLLED AIR CONDITIONING

Also Published As

Publication number Publication date
ITMI911425A1 (en) 1992-11-23
JPH04231606A (en) 1992-08-20
ITMI911425A0 (en) 1991-05-23
GB9110724D0 (en) 1991-07-10
SE9101655L (en) 1991-12-01
FR2662741B1 (en) 1995-06-09
CA2039756A1 (en) 1991-12-01
IT1249317B (en) 1995-02-22
FR2662741A1 (en) 1991-12-06
DE4117362A1 (en) 1991-12-05
GB2244524B (en) 1994-03-30
GB2244524A (en) 1991-12-04

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