DE602005021803D1 - Construction arrangement of a gas turbine guide vane - Google Patents

Construction arrangement of a gas turbine guide vane

Info

Publication number
DE602005021803D1
DE602005021803D1 DE602005021803T DE602005021803T DE602005021803D1 DE 602005021803 D1 DE602005021803 D1 DE 602005021803D1 DE 602005021803 T DE602005021803 T DE 602005021803T DE 602005021803 T DE602005021803 T DE 602005021803T DE 602005021803 D1 DE602005021803 D1 DE 602005021803D1
Authority
DE
Germany
Prior art keywords
gas turbine
guide vane
tangs
adequate
turbine guide
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
DE602005021803T
Other languages
German (de)
Inventor
Stephen John Booth
Alison Jane Mcmillan
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 DE602005021803D1 publication Critical patent/DE602005021803D1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Landscapes

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

Abstract

Appropriate location of components such as vanes (1, 21, 31, 41, 51, 61, 71, 81, 91) in gas turbine engines is important. These components are located between tangs (7, 27, 37, 47, 57, 67, 87, 97) held in interference engagement. There are four relatively rigid mounting points constituted by the tangs (7, 27, 37, 47, 57, 67, 87, 97) engaging respective opposed slots (8) in a casing (3) or a mounting ring (2). Only three point limitation with respect to displacement and rotation is adequate so provision of a fourth locator causes unnecessary constraint. A relatively resilient or compliant locator (37, 47, 57, 67, 87, 97) means it is possible to reduce the amount of constraint upon the component mounting whilst the other locators (7, 27) are adequate for positioning of the component (1, 21, 31, 41, 51, 61, 71, 81, 91).
DE602005021803T 2005-12-19 2005-12-19 Construction arrangement of a gas turbine guide vane Active DE602005021803D1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05257826A EP1798378B1 (en) 2005-12-19 2005-12-19 A mounting arrangement of a gas turbine vane

Publications (1)

Publication Number Publication Date
DE602005021803D1 true DE602005021803D1 (en) 2010-07-22

Family

ID=36143218

Family Applications (1)

Application Number Title Priority Date Filing Date
DE602005021803T Active DE602005021803D1 (en) 2005-12-19 2005-12-19 Construction arrangement of a gas turbine guide vane

Country Status (4)

Country Link
EP (1) EP1798378B1 (en)
AT (1) ATE470784T1 (en)
DE (1) DE602005021803D1 (en)
DK (1) DK1798378T3 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2456770A (en) * 2008-01-22 2009-07-29 Rolls Royce Plc A stator vane for a gas turbine engine
FR2935430B1 (en) * 2008-08-26 2012-03-09 Snecma IMPROVED TURBOMACHINE HIGH-PRESSURE TURBINE, DISPENSER SECTOR AND AIRCRAFT ENGINE
US9447693B2 (en) * 2012-07-30 2016-09-20 United Technologies Corporation Compliant assembly

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3511577A (en) * 1968-04-10 1970-05-12 Caterpillar Tractor Co Turbine nozzle construction
GB2037901B (en) * 1978-11-25 1982-07-28 Rolls Royce Nozzle guide vane assembly
DE3003470C2 (en) * 1980-01-31 1982-02-25 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbine guide vane suspension for gas turbine jet engines
CA2070511C (en) * 1991-07-22 2001-08-21 Steven Milo Toborg Turbine nozzle support
US5584654A (en) * 1995-12-22 1996-12-17 General Electric Company Gas turbine engine fan stator
DE102004006706A1 (en) * 2004-02-11 2005-08-25 Mtu Aero Engines Gmbh Damping arrangement for vanes, especially for vanes of a gas turbine or aircraft engine, comprises a spring element in the form of a leaf spring arranged between an inner shroud of the vanes and a seal support

Also Published As

Publication number Publication date
EP1798378A1 (en) 2007-06-20
EP1798378B1 (en) 2010-06-09
ATE470784T1 (en) 2010-06-15
DK1798378T3 (en) 2010-10-04

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