EP1714007A1 - Dispositif de suspension d'aubes directrices - Google Patents

Dispositif de suspension d'aubes directrices

Info

Publication number
EP1714007A1
EP1714007A1 EP04802944A EP04802944A EP1714007A1 EP 1714007 A1 EP1714007 A1 EP 1714007A1 EP 04802944 A EP04802944 A EP 04802944A EP 04802944 A EP04802944 A EP 04802944A EP 1714007 A1 EP1714007 A1 EP 1714007A1
Authority
EP
European Patent Office
Prior art keywords
plate
elements
shaped elements
shaped
gas channel
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
EP04802944A
Other languages
German (de)
English (en)
Other versions
EP1714007B1 (fr
Inventor
Stefan Morgenstern
Rudolf Stanka
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 Aero Engines 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 Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1714007A1 publication Critical patent/EP1714007A1/fr
Application granted granted Critical
Publication of EP1714007B1 publication Critical patent/EP1714007B1/fr
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
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape

Definitions

  • the invention relates to a device for suspending gas channel elements.
  • Gas channel elements such as guide vanes, guide vane segments, gas channel plates or gas channel plate segments, serve, among other things, to form a flow channel or gas channel of the gas turbine and must be suspended or attached to a housing of the gas turbine.
  • the gas channel elements for example the guide blades, protrude into the gas channel with a first end and are attached to a housing of the gas turbine with a second end.
  • the gas channel elements are fastened to the housing by a device for suspending gas channel elements, which can also be referred to as a suspension device or suspension element.
  • the gas duct elements in particular the guide blades projecting into the gas duct, are subject to severe thermal stress, particularly in the area of the high-pressure turbine of a gas turbine.
  • the gas duct elements are accordingly strongly heated, particularly in the area of the high-pressure turbine.
  • the case is relatively cold, so it has a low temperature.
  • the suspension elements for suspending gas channel elements on a housing of a gas turbine are therefore in contact with the relatively hot gas channel elements on the one hand and with the relatively cold housing on the other hand.
  • a strong temperature gradient is therefore formed in the suspension devices or suspension elements, as a result of which the same are exposed to high thermal stresses. This can lead to stress cracks within the suspension devices and thus to a reduced service life of the same.
  • the devices known from the prior art for suspending gas channel elements on a housing of the gas turbine can only inadequately absorb the thermal stresses described above due to the differences between the relatively cold housing of the gas turbine and the relatively hot gas channel elements.
  • the devices known from the prior art for suspending gas channel elements therefore have a limited service life. Proceeding from this, the present invention is based on the problem of creating a novel device for suspending gas channel elements.
  • the device according to the invention for suspending gas channel elements has first plate-shaped elements and second plate-shaped elements, the first plate-shaped elements and the second plate-shaped elements being connected to one another by web-like elements running approximately perpendicularly to the same, forming a meandering or castle-shaped profile.
  • the thermal expansion of the gas channel elements is not transferred to the device according to the invention in such a way that the service life of the device according to the invention is reduced.
  • the shape of the device according to the invention is selected such that different expansions within the device according to the invention at the contact area to the relatively cold housing and at the contact area to the relatively hot gas channel are absorbed by avoiding a rigid ring structure in such a way that stresses due to the different thermal expansions are low and so the life of the device according to the invention is not impaired.
  • a second plate-shaped element is positioned between each two adjacent, first plate-shaped elements such that the second plate-shaped element is connected at opposite ends to a respective one of the two adjacent, first plate-shaped elements via a web-like element.
  • the web-like elements preferably extend over the entire width of the first plate-shaped elements and / or the second plate-shaped elements.
  • bores are made in the first plate-shaped elements, in which holes for connection to the housing of the gas turbine Bolt-like fastening elements on the housing side can be inserted.
  • the second plate-shaped elements can be inserted for connection to the or each gas channel element in recesses assigned to projections of the gas channel elements.
  • Fig. 1 is a perspective view of an inventive device for
  • FIG. 2 shows the device according to the invention for suspending gas channel elements together with a gas channel element and a housing of a gas turbine
  • FIG. 3 shows a cross section through the arrangement according to FIG. 2.
  • 1 shows a device 10 according to the invention for suspending gas channel elements on a housing of a gas turbine in a perspective, sole representation.
  • 1 has a plurality of first plate-shaped elements 11, 12, 13 and 14 and a plurality of second plate-shaped elements 15, 16 and 17.
  • the first plate-shaped elements 11, 12, 13 and 14 are with the second plate-shaped elements
  • Elements 15, 16 and 17 are connected to one another by web-like elements 18 running approximately perpendicular to them, forming a meandering or castle-shaped profile.
  • a second plate-shaped element 15 or 16 or 17 is positioned between two adjacent, first plate-shaped elements 11 and 12 or 12 and 13 or 13 and 14. Each of these second plate-shaped elements 15 or 16 or 17 is connected at opposite ends via a web-like element 18 to one of the two adjacent, first plate-shaped elements 11 or 12 or 12 or 13 or 13 or 14. As already mentioned, the plate-shaped elements 18 run approximately perpendicular to the first plate-shaped elements 11 to 14 and the second plate-shaped elements 15 to 17. The web-like elements 18 extend over the entire width of the first plate-shaped elements 11, 12, 13, 14 and over the entire width of the second plate-shaped elements 15, 16 and 17 at the connection area with the same.
  • the meandering or castle-shaped profiling or contouring of the device 10 according to the invention for suspending gas channel elements on a housing of a gas turbine guarantees the greatest possible reduction of stresses due to temperature gradients, which result in the thermal differences between the relatively hot gas channel elements and the relative cold case arise.
  • the web-like elements 18, which run essentially at right angles or perpendicular to the plate-shaped elements 11 to 17, are deformed by thermal loads only in the elastic region, so that there is no material stress that shortens the service life.
  • the device 10 according to the invention for suspending gas channel elements shown in FIG. 1 has four first plate-shaped elements 11 to 14, three second plate-shaped elements 15 to 17 and six web-like elements 18 for connecting the second plate-shaped elements 15 to 17 to the first plate-shaped elements 11 to 14.
  • a number of such devices 10 are combined to form an annular suspension structure in order to fasten all the necessary gas channel elements to the housing along the circumference of the housing.
  • the device 10 according to FIG. 1 is therefore designed as a ring segment.
  • the device 10 according to the invention serves to suspend gas channel elements on a housing of a gas turbine.
  • the first plate-shaped elements 11 to 14 serve to connect the device 10 according to the invention to a housing 19 of the gas turbine. This can be seen in particular in FIG. 2.
  • bores 20 are made in the first plate-shaped elements 11 to 14. The bores 20 can best be seen in FIG. 1.
  • Bolt-shaped fastening elements 21 associated with the housing 19 engage in the bores 20 for fastening to the housing 19.
  • the meandering or castle-shaped contouring of the device 10 according to the invention enables a very direct flow of force in the direction of the arrow 22 (see in particular FIG. 3) starting from the fastening elements 21 into the device 10 according to the invention, since the load-bearing elements of the fastening are in the direct direction Force flow between the housing 19 and the device 10 according to the invention are arranged. In this respect, bending stresses are reduced to a minimum in the sense of the invention.
  • 2 and 3 show, as such a gas channel element 23, a profiled strut, a plurality of such profiled struts in a turbine bearing intermediate housing, which is also referred to as a turbine center frame, forming a bearing star for supporting shafts or rotors of the gas turbine.
  • the device according to the invention can of course also be used for suspending other gas channel elements, for example gas channel plate segments or guide vane segments or also individual guide vanes and individual gas channel plates.
  • the second plate-shaped elements 15 to 17 serve to connect to the gas channel element 23.
  • the second plate-shaped elements 15 to 17 can be inserted into the recesses associated with the gas channel element 23.
  • the two outer second plate-shaped elements 15 and 17 of the, connection to the gas channel element 23 are assigned projections 25 which extend essentially radially outward, a recess 26 being made in each of the projections 25, into which the two outer, plate-shaped elements 15 and 17 can be inserted.
  • the gas channel element 23 is accordingly hooked into the second plate-shaped elements 15 and 17 via the recesses 26.
  • the central, second plate-shaped element 16 is assigned a guide pin 27 which extends inwards in the radial direction.
  • the guide pin 27 engages in a corresponding recess 28 which is assigned to the outer shroud 24 of the gas channel element 23.
  • a circumferential fixation or circumferential centering of the gas channel element 23 is possible via the guide pin 27 engaging in the recess 28.
  • the middle, second plate-shaped element 16 is offset radially inwards in relation to the outer, second plate-shaped elements 15 to 17.
  • the above connection of the gas channel element 23 to the device 10 according to the invention has the advantage that fastening elements projecting into the gas channel, such as screws, in which large thermal stresses are then induced, can be avoided.
  • the fastening described above enables a relative movement between the gas channel element 23 and the device 10 according to the invention. This relative movement brings about an improved reduction of thermal peripheral stresses and can take over the function of a floating bearing in the direction of flow.
  • the device according to the invention described above can be manufactured in one piece with simple means as a cast part.
  • the one-piece design of the device 10 according to the invention makes it easy to assemble it.

Landscapes

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

Abstract

L'invention concerne un dispositif (10) servant à suspendre des éléments à canaux à gaz, notamment des aubes directrices, des segments d'aubes directrices, des plaques à canaux à gaz ou des segments de plaques à canaux à gaz, sur un carter d'une turbine à gaz. Ce dispositif présente des premiers éléments (11, 12, 13, 14) en forme de plaques et des deuxièmes éléments (15, 16, 17) en forme de plaques qui sont raccordés par des éléments (18), de type éléments jointifs, s'étendant sensiblement perpendiculairement aux premiers et aux deuxièmes éléments en créant un profil en forme de méandres ou de créneaux.
EP04802944.1A 2004-01-09 2004-12-15 Dispositif de suspension d'aubes directrices Active EP1714007B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004001393A DE102004001393A1 (de) 2004-01-09 2004-01-09 Vorrichtung zur Aufhängung von Gaskanalelementen
PCT/DE2004/002745 WO2005066462A1 (fr) 2004-01-09 2004-12-15 Dispositif de suspension d'aubes directrices

Publications (2)

Publication Number Publication Date
EP1714007A1 true EP1714007A1 (fr) 2006-10-25
EP1714007B1 EP1714007B1 (fr) 2016-11-09

Family

ID=34716392

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04802944.1A Active EP1714007B1 (fr) 2004-01-09 2004-12-15 Dispositif de suspension d'aubes directrices

Country Status (4)

Country Link
US (1) US8591182B2 (fr)
EP (1) EP1714007B1 (fr)
DE (1) DE102004001393A1 (fr)
WO (1) WO2005066462A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9206700B2 (en) * 2013-10-25 2015-12-08 Siemens Aktiengesellschaft Outer vane support ring including a strong back plate in a compressor section of a gas turbine engine
US10094244B2 (en) * 2015-09-18 2018-10-09 General Electric Company Ceramic matrix composite ring shroud retention methods-wiggle strip spring seal
EP3228837B1 (fr) * 2016-04-08 2019-08-28 Ansaldo Energia Switzerland AG Ensemble de composants de moteur turbomachine
EP3409905B1 (fr) * 2017-06-01 2019-12-11 MTU Aero Engines GmbH Boîtier intermédiaire de turbine comprenant un élément de centrage

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2995294A (en) * 1954-12-02 1961-08-08 Studebaker Packard Corp Stator casing and blade assembly
US3043103A (en) 1958-10-10 1962-07-10 Gen Motors Corp Liquid cooled wall
GB904138A (en) * 1959-01-23 1962-08-22 Bristol Siddeley Engines Ltd Improvements in or relating to stator structures, for example for axial flow gas turbine engines
US4361010A (en) * 1980-04-02 1982-11-30 United Technologies Corporation Combustor liner construction
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
US4655682A (en) 1985-09-30 1987-04-07 United Technologies Corporation Compressor stator assembly having a composite inner diameter shroud
US4868963A (en) * 1988-01-11 1989-09-26 General Electric Company Stator vane mounting method and assembly
FR2646880A1 (fr) * 1989-05-11 1990-11-16 Snecma Chemise de protection thermique pour canal de post-combustion ou de transition d'un turboreacteur
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
GB9623615D0 (en) * 1996-11-13 1997-07-09 Rolls Royce Plc Jet pipe liner
US6517313B2 (en) * 2001-06-25 2003-02-11 Pratt & Whitney Canada Corp. Segmented turbine vane support structure

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2005066462A1 *

Also Published As

Publication number Publication date
EP1714007B1 (fr) 2016-11-09
WO2005066462A1 (fr) 2005-07-21
US20080292457A1 (en) 2008-11-27
US8591182B2 (en) 2013-11-26
DE102004001393A1 (de) 2005-08-04

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