JPS5666408A - Turbine for turbo equipment - Google Patents

Turbine for turbo equipment

Info

Publication number
JPS5666408A
JPS5666408A JP14843780A JP14843780A JPS5666408A JP S5666408 A JPS5666408 A JP S5666408A JP 14843780 A JP14843780 A JP 14843780A JP 14843780 A JP14843780 A JP 14843780A JP S5666408 A JPS5666408 A JP S5666408A
Authority
JP
Japan
Prior art keywords
turbine
turbo equipment
turbo
equipment
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.)
Pending
Application number
JP14843780A
Other languages
English (en)
Inventor
Ooburii Robaatsu Dereku
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of JPS5666408A publication Critical patent/JPS5666408A/ja
Priority to US06/310,816 priority Critical patent/US4376335A/en
Pending 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)
JP14843780A 1979-10-24 1980-10-24 Turbine for turbo equipment Pending JPS5666408A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US06/310,816 US4376335A (en) 1980-10-20 1981-10-13 Method of mounting a timing gear on a crankshaft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB7936915A GB2061396B (en) 1979-10-24 1979-10-24 Turbine blade tip clearance control

Publications (1)

Publication Number Publication Date
JPS5666408A true JPS5666408A (en) 1981-06-04

Family

ID=10508747

Family Applications (1)

Application Number Title Priority Date Filing Date
JP14843780A Pending JPS5666408A (en) 1979-10-24 1980-10-24 Turbine for turbo equipment

Country Status (4)

Country Link
JP (1) JPS5666408A (ja)
DE (1) DE3038603C2 (ja)
FR (1) FR2467979A1 (ja)
GB (1) GB2061396B (ja)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2117843B (en) * 1982-04-01 1985-11-06 Rolls Royce Compressor shrouds
EP0103260A3 (en) * 1982-09-06 1984-09-26 Hitachi, Ltd. Clearance control for turbine blade tips
US4720236A (en) * 1984-12-21 1988-01-19 United Technologies Corporation Coolable stator assembly for a gas turbine engine
GB2260371B (en) * 1991-10-09 1994-11-09 Rolls Royce Plc Turbine engines
US5372476A (en) * 1993-06-18 1994-12-13 General Electric Company Turbine nozzle support assembly
DE19850732A1 (de) * 1998-11-04 2000-05-11 Asea Brown Boveri Axialturbine
US6742987B2 (en) * 2002-07-16 2004-06-01 General Electric Company Cradle mounted turbine nozzle
DE10340825A1 (de) * 2003-09-04 2005-03-31 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit Laufspaltkontrolle
DE102004016222A1 (de) 2004-03-26 2005-10-06 Rolls-Royce Deutschland Ltd & Co Kg Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine
EP1712744B1 (de) * 2005-04-14 2009-01-07 Rolls-Royce Deutschland Ltd & Co KG Anordnung zur inneren passiven Laufspalteinstellung bei einer Hochdruckturbine
GB0909470D0 (en) * 2009-06-03 2009-07-15 Rolls Royce Plc A guide vane assembly
EP3026218B1 (en) * 2014-11-27 2017-06-14 Ansaldo Energia Switzerland AG First stage turbine vane arrangement
EP3075959A1 (en) * 2015-03-31 2016-10-05 Alstom Technology Ltd Gas turbine comprising a combustor with a combustor outlet and a first row of rocking vanes
GB201616197D0 (en) * 2016-09-23 2016-11-09 Rolls Royce Plc Gas turbine engine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH482915A (de) * 1967-11-03 1969-12-15 Sulzer Ag Leitvorrichtung für Axialturbine
US3807891A (en) * 1972-09-15 1974-04-30 United Aircraft Corp Thermal response turbine shroud
GB1504129A (en) * 1974-06-29 1978-03-15 Rolls Royce Matching differential thermal expansions of components in heat engines
US3986720A (en) * 1975-04-14 1976-10-19 General Electric Company Turbine shroud structure
GB1501916A (en) * 1975-06-20 1978-02-22 Rolls Royce Matching thermal expansions of components of turbo-machines

Also Published As

Publication number Publication date
GB2061396A (en) 1981-05-13
DE3038603A1 (de) 1982-03-04
DE3038603C2 (de) 1982-09-09
GB2061396B (en) 1983-05-18
FR2467979A1 (fr) 1981-04-30
FR2467979B1 (ja) 1983-05-20

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