GB2062117B - Clearance control for turbine blades - Google Patents

Clearance control for turbine blades

Info

Publication number
GB2062117B
GB2062117B GB8033798A GB8033798A GB2062117B GB 2062117 B GB2062117 B GB 2062117B GB 8033798 A GB8033798 A GB 8033798A GB 8033798 A GB8033798 A GB 8033798A GB 2062117 B GB2062117 B GB 2062117B
Authority
GB
United Kingdom
Prior art keywords
turbine blades
clearance control
clearance
control
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
GB8033798A
Other versions
GB2062117A (en
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to GB8033798A priority Critical patent/GB2062117B/en
Publication of GB2062117A publication Critical patent/GB2062117A/en
Application granted granted Critical
Publication of GB2062117B publication Critical patent/GB2062117B/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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
GB8033798A 1980-10-20 1980-10-20 Clearance control for turbine blades Expired GB2062117B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB8033798A GB2062117B (en) 1980-10-20 1980-10-20 Clearance control for turbine blades

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB8033798A GB2062117B (en) 1980-10-20 1980-10-20 Clearance control for turbine blades

Publications (2)

Publication Number Publication Date
GB2062117A GB2062117A (en) 1981-05-20
GB2062117B true GB2062117B (en) 1983-05-05

Family

ID=10516790

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8033798A Expired GB2062117B (en) 1980-10-20 1980-10-20 Clearance control for turbine blades

Country Status (1)

Country Link
GB (1) GB2062117B (en)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4525998A (en) * 1982-08-02 1985-07-02 United Technologies Corporation Clearance control for gas turbine engine
GB2136508B (en) * 1983-03-11 1987-12-31 United Technologies Corp Coolable stator assembly for a gas turbine engine
US4826397A (en) * 1988-06-29 1989-05-02 United Technologies Corporation Stator assembly for a gas turbine engine
CA2039756A1 (en) * 1990-05-31 1991-12-01 Larry Wayne Plemmons Stator having selectively applied thermal conductivity coating
US5407320A (en) * 1991-04-02 1995-04-18 Rolls-Royce, Plc Turbine cowling having cooling air gap
US5152666A (en) * 1991-05-03 1992-10-06 United Technologies Corporation Stator assembly for a rotary machine
FR2751694B1 (en) * 1996-07-25 1998-09-04 Snecma ARRANGEMENT AND METHOD FOR ADJUSTING THE STATOR RING DIAMETER
GB9820226D0 (en) * 1998-09-18 1998-11-11 Rolls Royce Plc Gas turbine engine casing
GB2388407B (en) * 2002-05-10 2005-10-26 Rolls Royce Plc Gas turbine blade tip clearance control structure
US8662824B2 (en) * 2010-01-28 2014-03-04 Pratt & Whitney Canada Corp. Rotor containment structure for gas turbine engine
US8834105B2 (en) * 2010-12-30 2014-09-16 General Electric Company Structural low-ductility turbine shroud apparatus

Also Published As

Publication number Publication date
GB2062117A (en) 1981-05-20

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Legal Events

Date Code Title Description
PE20 Patent expired after termination of 20 years

Effective date: 20001019