IT1249317B - STATOR HAVING A SELECTIVE APPLIED THERMAL CONDUCTIVITY COATING - Google Patents

STATOR HAVING A SELECTIVE APPLIED THERMAL CONDUCTIVITY COATING

Info

Publication number
IT1249317B
IT1249317B ITMI911425A ITMI911425A IT1249317B IT 1249317 B IT1249317 B IT 1249317B IT MI911425 A ITMI911425 A IT MI911425A IT MI911425 A ITMI911425 A IT MI911425A IT 1249317 B IT1249317 B IT 1249317B
Authority
IT
Italy
Prior art keywords
stator
thermal conductivity
coating
reduce
control
Prior art date
Application number
ITMI911425A
Other languages
Italian (it)
Inventor
Larry Wayne Plemmons
William Charles Oakes
Ralph Adrian Kirkpatrick
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 ITMI911425A0 publication Critical patent/ITMI911425A0/en
Publication of ITMI911425A1 publication Critical patent/ITMI911425A1/en
Application granted granted Critical
Publication of IT1249317B publication Critical patent/IT1249317B/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

Sono rivelati un metodo ed uno statore per turbomotore a gas che sono efficaci per controllare un gioco d'accoppiamento radiale non a simmetria assiale tra una superficie di percorso di flusso di statore e l'estremità di pale rotoriche. Un rivestimento di conduttività termica preselezionata è disposto in modo predeterminato lungo la circonferenza dello statore per controllare la deformazione circonferenziale indotta termicamente e perciò controllare il gioco d'accoppiamento radiale non a simmetria assiale. Nelle realizzazioni preferite dell'invenzione un rivestimento ad elevata conduttività termica può essere applicato ad una flangia anulare per ridurre il gradiente di temperatura della medesima. In un'altra realizzazione della presente invenzione possono essere applicati allo statore rivestimenti a bassa conduttività termica per isolare di preferenza lo statore e ridurre la deformazione termica circonferenziale.A gas turbine engine method and stator which are effective for controlling a non-axially symmetrical radial coupling play between a stator flow path surface and the end of rotor blades are disclosed. A preselected thermal conductivity coating is predeterminedly arranged along the circumference of the stator to control the thermally induced circumferential deformation and therefore to control the radial coupling play not having axial symmetry. In the preferred embodiments of the invention a coating with high thermal conductivity can be applied to an annular flange to reduce the temperature gradient of the same. In another embodiment of the present invention, low thermal conductivity coatings can be applied to the stator to preferably isolate the stator and reduce the circumferential thermal deformation.

ITMI911425A 1990-05-31 1991-05-23 STATOR HAVING A SELECTIVE APPLIED THERMAL CONDUCTIVITY COATING IT1249317B (en)

Applications Claiming Priority (1)

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

Publications (3)

Publication Number Publication Date
ITMI911425A0 ITMI911425A0 (en) 1991-05-23
ITMI911425A1 ITMI911425A1 (en) 1992-11-23
IT1249317B true IT1249317B (en) 1995-02-22

Family

ID=24117023

Family Applications (1)

Application Number Title Priority Date Filing Date
ITMI911425A IT1249317B (en) 1990-05-31 1991-05-23 STATOR HAVING A SELECTIVE APPLIED THERMAL CONDUCTIVITY 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
GB9110724D0 (en) 1991-07-10
ITMI911425A0 (en) 1991-05-23
CA2039756A1 (en) 1991-12-01
GB2244524B (en) 1994-03-30
SE9101655D0 (en) 1991-05-30
GB2244524A (en) 1991-12-04
FR2662741A1 (en) 1991-12-06
FR2662741B1 (en) 1995-06-09
JPH04231606A (en) 1992-08-20
SE9101655L (en) 1991-12-01
ITMI911425A1 (en) 1992-11-23
DE4117362A1 (en) 1991-12-05

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Legal Events

Date Code Title Description
0001 Granted
TA Fee payment date (situation as of event date), data collected since 19931001

Effective date: 19940527