EP0937864A3 - Guidevane assembly for an axial turbomachine - Google Patents

Guidevane assembly for an axial turbomachine Download PDF

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Publication number
EP0937864A3
EP0937864A3 EP99103156A EP99103156A EP0937864A3 EP 0937864 A3 EP0937864 A3 EP 0937864A3 EP 99103156 A EP99103156 A EP 99103156A EP 99103156 A EP99103156 A EP 99103156A EP 0937864 A3 EP0937864 A3 EP 0937864A3
Authority
EP
European Patent Office
Prior art keywords
housing
vane ring
shroud
outer shroud
guide vane
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.)
Granted
Application number
EP99103156A
Other languages
German (de)
French (fr)
Other versions
EP0937864A2 (en
EP0937864B1 (en
Inventor
Hermann Klingels
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.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0937864A2 publication Critical patent/EP0937864A2/en
Publication of EP0937864A3 publication Critical patent/EP0937864A3/en
Application granted granted Critical
Publication of EP0937864B1 publication Critical patent/EP0937864B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, 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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Strömungsmaschine mit Rotor und Stator in zumindest abschnittsweise axialer Bauart, mit Laufschaufeln am Rotor und gehäusefesten Leitschaufeln, wobei letztere als mindestens ein Leitschaufelkranz mit einem inneren und einem äußeren Deckband angeordnet sind.Turbomachine with rotor and stator in at least some sections of an axial design, with rotor blades and fixed guide vanes, the latter as at least one vane ring with an inner and an outer shroud are arranged.

Der mindestens eine Leitschaufelkranz ist als selbsttragendes Bauteil mit einer geschlossenen, das Bauteil gegen stülpende Axialverformung versteifenden Verstärkung am inneren Deckband ausgeführt, weist ein segmentiertes äußeres Deckband auf und ist über mindestens drei Deckbandsegmente mittels jeweils radiale Relativbewegungen zulassender Lagereinheiten im Gehäuse positioniert.The at least one guide vane ring is a self-supporting component with a closed, reinforcement reinforcing the component against inverting axial deformation executed on the inner shroud, has a segmented outer shroud and is over at least three shroud segments by means of radial relative movements permitting bearing units positioned in the housing.

Zwischen dem Gehäuse und dem äußeren Deckband des mindestens einen Leitschaufelkranzes ist eine Luftleitschale angeordnet, welche einen Kühlluftstrom längs der Gehäuseinnenseite führt und mit Öffnungen für die gehäusefesten Lagerelemente des mindestens einen Leitschaufelkranzes versehen ist.

Figure 00000001
An air guide shell is arranged between the housing and the outer shroud of the at least one guide vane ring, which guides a cooling air flow along the inside of the housing and is provided with openings for the bearing elements of the at least one guide vane ring fixed to the housing.
Figure 00000001
EP99103156A 1998-02-20 1999-02-18 Guidevane assembly for an axial turbomachine Expired - Lifetime EP0937864B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19807247A DE19807247C2 (en) 1998-02-20 1998-02-20 Turbomachine with rotor and stator
DE19807247 1998-02-20

Publications (3)

Publication Number Publication Date
EP0937864A2 EP0937864A2 (en) 1999-08-25
EP0937864A3 true EP0937864A3 (en) 2000-10-25
EP0937864B1 EP0937864B1 (en) 2003-08-13

Family

ID=7858458

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99103156A Expired - Lifetime EP0937864B1 (en) 1998-02-20 1999-02-18 Guidevane assembly for an axial turbomachine

Country Status (4)

Country Link
US (1) US6139263A (en)
EP (1) EP0937864B1 (en)
JP (1) JP4230040B2 (en)
DE (2) DE19807247C2 (en)

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT1318103B1 (en) * 2000-07-03 2003-07-23 Nuovo Pignone Spa CONNECTION SYSTEM BETWEEN A LOW PRESSURE NOZZLE AND UNTRANSITION DUCT IN A GAS TURBINE
DE10037837C2 (en) * 2000-08-03 2002-08-01 Mtu Aero Engines Gmbh suspension
JP2002129901A (en) * 2000-10-30 2002-05-09 Ishikawajima Harima Heavy Ind Co Ltd Chip shroud structure
DE10064272A1 (en) * 2000-12-22 2002-07-04 Alstom Switzerland Ltd Gas turbine blade has platform at base with end face turned towards gas flow, smaller blade whose surface is parallel to end face being mounted under platform which is at least as wide as projection of blade width on front edge of platform
DE10122464C1 (en) * 2001-05-09 2002-03-07 Mtu Aero Engines Gmbh Mantle ring for low pressure turbine stage of gas turbine uses segments each having seal carrier and relatively spaced security element with minimum contact between them
US7059821B2 (en) * 2003-05-07 2006-06-13 General Electric Company Method and apparatus to facilitate sealing within turbines
DE10359730A1 (en) 2003-12-19 2005-07-14 Mtu Aero Engines Gmbh Turbomachine, in particular gas turbine
DE102004016222A1 (en) * 2004-03-26 2005-10-06 Rolls-Royce Deutschland Ltd & Co Kg Arrangement for automatic running gap adjustment in a two-stage or multi-stage turbine
GB2448116B (en) * 2007-04-05 2009-05-27 Rolls Royce Plc Means for cooling a bearing assembly
US8090456B2 (en) * 2008-11-03 2012-01-03 United Technologies Corporation System and method for design and control of engineering systems utilizing component-level dynamic mathematical model
DE102009037620A1 (en) 2009-08-14 2011-02-17 Mtu Aero Engines Gmbh flow machine
US8668434B2 (en) * 2009-09-02 2014-03-11 United Technologies Corporation Robust flow parameter model for component-level dynamic turbine system control
US8315741B2 (en) * 2009-09-02 2012-11-20 United Technologies Corporation High fidelity integrated heat transfer and clearance in component-level dynamic turbine system control
DE102009042029A1 (en) * 2009-09-17 2011-03-24 Mtu Aero Engines Gmbh Blade ring for flow machine, particularly for gas turbine, has hardened reinforcement on inner shroud, where reinforcement is closed in circumferential direction
DE102009052314A1 (en) 2009-11-07 2011-05-12 Mtu Aero Engines Gmbh Sealing arrangement for a gas turbine and such a gas turbine
US20110255959A1 (en) * 2010-04-15 2011-10-20 General Electric Company Turbine alignment control system and method
ES2793725T3 (en) 2010-11-16 2020-11-16 Mtu Aero Engines Gmbh Rotor blade assembly for a turbine
DE102011083814A1 (en) 2011-09-30 2013-04-04 Mtu Aero Engines Gmbh Segmented component
EP2647795B1 (en) 2012-04-04 2018-11-07 MTU Aero Engines AG Seal system for a turbo engine
EP2647796A1 (en) * 2012-04-04 2013-10-09 MTU Aero Engines GmbH Seal system for a turbo engine
EP2947275A1 (en) 2012-04-04 2015-11-25 MTU Aero Engines GmbH Method for producing an abradable
KR101480089B1 (en) 2012-05-10 2015-01-08 이병화 Anchor Bolt for Wood
EP2719869A1 (en) 2012-10-12 2014-04-16 MTU Aero Engines GmbH Axial sealing in a housing structure for a turbomachine
ES2679343T3 (en) 2013-04-24 2018-08-24 MTU Aero Engines AG Sealing gasket
CN103482219B (en) * 2013-09-16 2016-06-01 沈阳黎明航空发动机(集团)有限责任公司 Rotor is carried out axle, radial localization method by a kind of internal combustion turbine transportation
DE102014209057A1 (en) 2014-05-14 2015-11-19 MTU Aero Engines AG Gas turbine casing assembly
US10975721B2 (en) * 2016-01-12 2021-04-13 Pratt & Whitney Canada Corp. Cooled containment case using internal plenum
IT201900014736A1 (en) 2019-08-13 2021-02-13 Ge Avio Srl Integral sealing elements for blades held in a rotatable annular outer drum rotor in a turbomachinery.
IT201900014739A1 (en) 2019-08-13 2021-02-13 Ge Avio Srl Elements for retaining blades for turbomachinery.
IT201900014724A1 (en) 2019-08-13 2021-02-13 Ge Avio Srl Elements for retaining blades for turbomachinery.
CN115387906B (en) * 2022-05-12 2024-04-16 中国航发四川燃气涡轮研究院 Air inlet bearing frame connecting structure of low inlet hub ratio engine and assembling method

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2968467A (en) * 1956-11-14 1961-01-17 Orenda Engines Ltd Connecting means, especially for securing annular stator elements between supports whose positions are fixed
US3588267A (en) * 1968-06-27 1971-06-28 Rolls Royce Blade assembly for a fluid flow machine
FR2534313A1 (en) * 1982-10-06 1984-04-13 Rolls Royce Turbine rotor emergency braking device

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3542483A (en) * 1968-07-17 1970-11-24 Westinghouse Electric Corp Turbine stator structure
GB1387866A (en) * 1972-06-21 1975-03-19 Rolls Royce Aerofoil members for gas turbine engines
GB1605310A (en) * 1975-05-30 1989-02-01 Rolls Royce Nozzle guide vane structure
DE2745130C2 (en) 1977-10-07 1980-01-03 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Sealing device for the free blade ends of axial turbines
US4679400A (en) * 1983-12-15 1987-07-14 General Electric Company Variable turbine vane support
DE3540943A1 (en) 1985-11-19 1987-05-21 Mtu Muenchen Gmbh GAS TURBINE JET ENGINE IN MULTI-SHAFT, TWO-STREAM DESIGN

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2968467A (en) * 1956-11-14 1961-01-17 Orenda Engines Ltd Connecting means, especially for securing annular stator elements between supports whose positions are fixed
US3588267A (en) * 1968-06-27 1971-06-28 Rolls Royce Blade assembly for a fluid flow machine
FR2534313A1 (en) * 1982-10-06 1984-04-13 Rolls Royce Turbine rotor emergency braking device

Also Published As

Publication number Publication date
JPH11294103A (en) 1999-10-26
DE59906550D1 (en) 2003-09-18
DE19807247A1 (en) 1999-09-09
DE19807247C2 (en) 2000-04-20
EP0937864A2 (en) 1999-08-25
JP4230040B2 (en) 2009-02-25
US6139263A (en) 2000-10-31
EP0937864B1 (en) 2003-08-13

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