EP2464831A2 - Éléments de fixation d'aubes directrices dans une turbomachine - Google Patents

Éléments de fixation d'aubes directrices dans une turbomachine

Info

Publication number
EP2464831A2
EP2464831A2 EP10760227A EP10760227A EP2464831A2 EP 2464831 A2 EP2464831 A2 EP 2464831A2 EP 10760227 A EP10760227 A EP 10760227A EP 10760227 A EP10760227 A EP 10760227A EP 2464831 A2 EP2464831 A2 EP 2464831A2
Authority
EP
European Patent Office
Prior art keywords
turbomachine
housing
fastening element
vane ring
outer shroud
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
EP10760227A
Other languages
German (de)
English (en)
Other versions
EP2464831B1 (fr
Inventor
Wilfried Weidmann
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 EP2464831A2 publication Critical patent/EP2464831A2/fr
Application granted granted Critical
Publication of EP2464831B1 publication Critical patent/EP2464831B1/fr
Not-in-force 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
    • 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
    • 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
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, with a housing and at least one vane ring whose outer shroud by
  • Dividing joints is divided into segments.
  • Such a turbomachine is known for example from DE 198 07 247 C2.
  • the vane rings are mounted in the region of their outer shroud with bearing pins on the housing of the turbomachine, wherein the segments of the vane ring are radially freely movable in the region of the outer shroud.
  • Such storage is also referred to as storage centering.
  • the bearing pin takes all of the
  • the invention is based on the object, an improved attachment of a
  • a flow machine of the above-mentioned type wherein the outer shroud of the vane ring via a first fastening element for
  • Fastening element for toysskraftaufhahme is attached to the housing and wherein the first and the second fastening element for the segments of the outer shroud allow clearance in the radial direction.
  • the Axialkraftaufhahme and the designedskraftaufhahme via separate, independent fasteners.
  • the load on the fasteners is thereby reduced, and the fasteners can be optimally designed for their respective function.
  • Axial force and circumferential force are orthogonal to each other, allowing for independent force absorption while simultaneously applying forces in the radial direction are not received by the fasteners, whereby a clearance in the radial direction for the vane ring is made possible.
  • the fastening element for Axialkraftaufhahme is arranged in the direction of force behind an axial force transmitting component of the outer shroud. This allows the transmission of compressive forces on the fastener.
  • the axial force is transmitted via a plurality of separate contact surfaces between the vane ring and the fastening element for Axialkraftaufhahme. In this way, the friction between the mounting element for Axialkraftaufhahme and the vane ring can be reduced.
  • the fastening element for Axialkraftaufhahme is annular and forms a positive connection with the housing. This allows, for example, a rotationally symmetrical embodiment of the fastener for Axialkraftaufhahme.
  • the positive connection can be formed by a mounting extension on the housing and a groove in the annular fastener for Axialkraftaufhahme.
  • the inner radius of the mounting extension is greater than the outer radius of the outer shroud. This allows a mounting of the turbomachine in the axial direction.
  • a plurality of fastening elements for axial force transmission are provided, which in the force direction in front of an axial force
  • the fastening elements for axial force transmission are radially elastic elements. This ensures the mobility of the vane ring segments in the radial direction.
  • the fastening elements for Axialkraftübertragung can be positively secured to the housing and the vane ring.
  • the preferably positive connection between the fastening element for Axialkraftaufhahme and the housing can be secured by a fuse wire. In this way, an inadvertent release of the connection between the
  • FIG. 2 is a sectional view of a turbomachine with two vanes and a blade
  • FIG. 3 is a sectional view of a turbomachine with a radially movable vane
  • FIG. 4 shows a sectional view of a turbomachine according to a first embodiment of the invention
  • FIG. 5 shows a vane ring segment of the turbomachine according to FIG. 4.
  • FIGS. 1 to 3 show a turbomachine 10 with a vane ring 12. This has an outer shroud 16, which is divided by parting lines in individual segments 14. As indicated in Figure 1 and Figure 3 by the double-sided arrows, the segments 14 of the outer shroud 16 can move in the radial direction.
  • FIG. 2 shows a section of the turbomachine 10 with two vane rings 12 and a rotor blade 18.
  • the two vane rings 12 are connected by a honeycomb carrier 20.
  • FIG. 3 shows a vane ring 12 between two rotor blades 18
  • Vane ring 12 and the associated honeycomb carrier 20 are mounted in a housing 22 of the turbomachine 10, wherein the (not shown in Figure 3) attachment for the segments 14 of the outer shroud 16 of the vane ring 12 allows clearance in the radial direction for memory-centered attachment.
  • the outer shroud 16 of the vane ring 12 can move in the radial direction between the radially inwardly and outwardly located positions shown with dashed lines.
  • Figure 4 shows a first embodiment of the attachment of the vane ring 12 on the housing 22 of the turbomachine 10.
  • Peripheral force space is a substantially annular, radially inwardly projecting housing member 26, in which a plurality of slots are provided.
  • the vane ring 12 has a radially outwardly projecting component 28 in the region of the outer cover strip 16, which forms lugs which are positively connected to the slots in the housing member 26 and fix the vane ring 12 in the circumferential direction.
  • the housing member 26 has lugs which engage in slots in the component 28 of the vane ring 12, or that on both the housing member 26 and the component 28 of the vane ring 12 lugs and slots are provided which mutually engage in order to establish the positive connection.
  • a force acting on the vane ring 12 in the circumferential direction is transmitted from the component 28 via the interlocking lugs and slots on the housing member 26, which receives the circumferential force and thus fixes the vane ring 12 in the circumferential direction in the housing 22 of the turbomachine 10.
  • a fastener 30 for Axialkraftaufhahme is in the direction of force behind a
  • Axialkraftübertragende member 32 of the vane ring 12 is arranged.
  • the direction of the axial force has in the embodiment shown from left to right. In this
  • the axial force from the vane ring 12 via the axial force transmitting member 32 is transmitted to the mounting member 30 for Axialkraftaufhahme as a compressive force.
  • the axial force transmitting member 32 has a plurality of separate contact surfaces 34 via which the axial force between the vane ring 12 and the
  • Fastening element 30 is transmitted to Axialkraftaufhahme.
  • Figure 5 a segment 14 of the shroud 16 of the vane ring 12 is shown, which at its in
  • Circumferentially located ends each have a contact surface 34.
  • the contact surface 34 over the entire circumference of
  • Guide vane ring 12 extends.
  • a special surface structure or a special coating, such as armor be provided to keep the friction between the vane ring 12 and the fastener 30 for Axialkraftaufhahme as low as possible.
  • the slotted for mounting on the circumference fastener 30 for Axialkraftaufhahme is annular and has a running at its outer radius in the circumferential direction groove, with which it is positively connected to a mounting extension 36 which is formed on the housing 22.
  • the inner radius of the mounting extension 36 is greater than the outer radius of the vane ring 12.
  • the inner radius of the Axialkraftaufhahme mounting member 30 is smaller than the outer radius of the Leitschaufelkranzes 12. In this way, the Leitschaufelkranz 12 is located with the contact surfaces 34 on the mounting member 30 for Axialkraftaufhahme and the Leitschaufelkranz 12 is fixed by the fastener 30 in its axial position.
  • the axial force transmitting member 32 is in the direction opposite to the axial force on the fastener 24 to
  • the two fasteners 24, 30 for for memoriskraftaufhahme and
  • Axialkraftaufhahme together form a guide for the components 28, 32 of the segment 14 of the outer shroud 16 of the vane ring 12, which allows movement of the segment 14 in the radial direction.
  • Axialkraftierhahme and the mounting extension 36 of the housing 22 is by a
  • Safety wire 38 secured. It is also possible that the fastening element 30 is secured directly to the housing 22 by the safety wire 38 for Axialkraftaufhahme.
  • a second embodiment of the fastening element 30 for Axialkraftaufhahme is shown in Figure 6.
  • the fastening element 30 for Axialkraftaufhahme is in this case
  • Embodiment arranged in the direction of force in front of an axial force transmitting member 32 of the vane ring 12, whereby tensile forces between the axial force
  • One or more fasteners 30 are provided for axial force per segment 14 of the outer shroud of the vane ring 12.
  • the fasteners 30 are positively secured to the housing 22 and the vane ring 12. On the housing 22, the positive connection with the fastening element 30 by a
  • Fastener 30 and vane ring 12 is secured by a clamp 40, which may be part of honeycomb support 20 or a separate part.
  • the fastening elements 30 for Axialkraftaumahme are radially elastic elements.
  • the attached to the vane ring 12 end of the fastening element 30 for Axialkraftaufhahme can along a circular path around the attached to the housing 22 end of the
  • fastening elements 30 for Axialkraftaumahme are completely separate components. Alternatively, several and in particular all
  • Fastening elements 30 may be connected to each other at the end fixed to the housing 22, whereby a substantially annular fastening element 30 is formed, with a plurality of radially elastic extensions which are fixed at their end to the guide vane ring 12.
  • Guide vane ring 12 is in execution and function analogous to the embodiment described in Figure 4.

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

L'invention concerne une turbomachine (10), en particulier une turbine à gaz, comprenant une carcasse (22) et une couronne d'aubes directrices (12) dont la bande extérieure de recouvrement (16) est subdivisée par des joints de séparation, en segments (14), caractérisée en ce que la bande extérieure de recouvrement (16) est fixée à la carcasse (22), au moyen d'un premier élément de fixation (30) pour la réception d'une force axiale, et d'un second élément de fixation (24) indépendant du premier élément de fixation (30), pour la réception d'une force périphérique, et en ce que le premier et le second élément de fixation (24, 30) permettent, pour les segments (14) de la bande extérieure de recouvrement (16), un jeu en direction radiale.
EP10760227.8A 2009-08-14 2010-08-05 Éléments de fixation d'aubes directrices dans une turbomachine Not-in-force EP2464831B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009037620A DE102009037620A1 (de) 2009-08-14 2009-08-14 Strömungsmaschine
PCT/DE2010/000927 WO2011018072A2 (fr) 2009-08-14 2010-08-05 Turbomachine

Publications (2)

Publication Number Publication Date
EP2464831A2 true EP2464831A2 (fr) 2012-06-20
EP2464831B1 EP2464831B1 (fr) 2018-04-25

Family

ID=43448339

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10760227.8A Not-in-force EP2464831B1 (fr) 2009-08-14 2010-08-05 Éléments de fixation d'aubes directrices dans une turbomachine

Country Status (5)

Country Link
US (1) US20120141253A1 (fr)
EP (1) EP2464831B1 (fr)
DE (1) DE102009037620A1 (fr)
ES (1) ES2669120T3 (fr)
WO (1) WO2011018072A2 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2984428B1 (fr) * 2011-12-19 2018-12-07 Safran Aircraft Engines Redresseur de compresseur pour turbomachine.
ES2704485T3 (es) 2012-10-30 2019-03-18 MTU Aero Engines AG Fijación de soporte de junta para una turbomáquina
FR3009740B1 (fr) * 2013-08-13 2017-12-15 Snecma Amelioration pour le verrouillage de pieces de support d'aubage
EP2937517B1 (fr) * 2014-04-24 2019-03-06 Safran Aero Boosters SA Stator de turbomachine axiale et turbomachine associée
DE102015202070A1 (de) 2015-02-05 2016-08-25 MTU Aero Engines AG Gasturbinenbauteil
USD871468S1 (en) * 2017-03-28 2019-12-31 General Electric Company Flow ingestion discourager with ridged pattern for a turbomachine shroud

Family Cites Families (24)

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BE543281A (fr) * 1954-12-16
US3302926A (en) * 1965-12-06 1967-02-07 Gen Electric Segmented nozzle diaphragm for high temperature turbine
US3443791A (en) * 1966-11-23 1969-05-13 United Aircraft Corp Turbine vane assembly
GB1385666A (en) * 1973-07-06 1975-02-26 Rolls Royce Sealing of vaned assemblies of gas turbine engines
US4314793A (en) * 1978-12-20 1982-02-09 United Technologies Corporation Temperature actuated turbine seal
US4492517A (en) * 1983-01-06 1985-01-08 General Electric Company Segmented inlet nozzle for gas turbine, and methods of installation
IT1167241B (it) * 1983-10-03 1987-05-13 Nuovo Pignone Spa Sistema perfezionato per il fissaggio degli ugelli statorici alla cassa di una turbina di potenza
US4639189A (en) * 1984-02-27 1987-01-27 Rockwell International Corporation Hollow, thermally-conditioned, turbine stator nozzle
US4767267A (en) * 1986-12-03 1988-08-30 General Electric Company Seal assembly
US4916892A (en) * 1988-05-06 1990-04-17 General Electric Company High pressure seal
US4957412A (en) * 1988-09-06 1990-09-18 Westinghouse Electric Corp. Apparatus and method for supporting the torque load on a gas turbine vane
US5224825A (en) * 1991-12-26 1993-07-06 General Electric Company Locator pin retention device for floating joint
GB9304994D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc Improvements in or relating to gas turbine engines
DE19507673C2 (de) * 1995-03-06 1997-07-03 Mtu Muenchen Gmbh Leitrad für Turbomaschinen
US5846050A (en) * 1997-07-14 1998-12-08 General Electric Company Vane sector spring
DE19807247C2 (de) * 1998-02-20 2000-04-20 Mtu Muenchen Gmbh Strömungsmaschine mit Rotor und Stator
DE50112597D1 (de) * 2001-04-12 2007-07-19 Siemens Ag Gasturbine mit axial verschiebbaren Gehäuseteilen
US6517313B2 (en) * 2001-06-25 2003-02-11 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
US6916154B2 (en) * 2003-04-29 2005-07-12 Pratt & Whitney Canada Corp. Diametrically energized piston ring
DE10359730A1 (de) * 2003-12-19 2005-07-14 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine
US7144218B2 (en) * 2004-04-19 2006-12-05 United Technologies Corporation Anti-rotation lock
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FR2899275A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Dispositif de fixation de secteurs d'anneau sur un carter de turbine d'une turbomachine
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Also Published As

Publication number Publication date
EP2464831B1 (fr) 2018-04-25
WO2011018072A3 (fr) 2011-09-15
WO2011018072A2 (fr) 2011-02-17
ES2669120T3 (es) 2018-05-24
US20120141253A1 (en) 2012-06-07
DE102009037620A1 (de) 2011-02-17

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