EP2129875B1 - Turbomachine avec controle de jeu actif - Google Patents

Turbomachine avec controle de jeu actif Download PDF

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Publication number
EP2129875B1
EP2129875B1 EP08706764A EP08706764A EP2129875B1 EP 2129875 B1 EP2129875 B1 EP 2129875B1 EP 08706764 A EP08706764 A EP 08706764A EP 08706764 A EP08706764 A EP 08706764A EP 2129875 B1 EP2129875 B1 EP 2129875B1
Authority
EP
European Patent Office
Prior art keywords
adjusting device
gap
ring
jacket ring
rotor
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.)
Not-in-force
Application number
EP08706764A
Other languages
German (de)
English (en)
Other versions
EP2129875A2 (fr
Inventor
Joachim Wulf
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 EP2129875A2 publication Critical patent/EP2129875A2/fr
Application granted granted Critical
Publication of EP2129875B1 publication Critical patent/EP2129875B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • 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
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • 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

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, according to the preamble of claim 1.
  • a turbomachine with a stator and a rotor wherein the rotor blades and the stator identifies a housing and vanes.
  • the rotor-side Laufscbaufeln form at least one Laufscbaufellaranz, which is adjacent to a radially outer end of a radially inner housing wall of the housing, surrounded by the same and limited with the same a radial gap
  • the radially inner housing wall of the housing is also referred to as a shroud and serves in particular as a carrier for an inlet lining.
  • the gap between the casing ring of the housing and the radially outer end of the or each blade ring for providing a so-called Active Clearance Control can be adjusted or adjusted via adjusting devices in its gap, so as to automatically influence the gap and on all Operating conditions to ensure optimum cleavage.
  • the radially inner housing wall or the shroud segmented in the circumferential direction wherein preferably each segment is assigned a separate actuating device
  • the actuating devices are preferably designed as electromechanical actuators.
  • the arrangement of the electro-mechanical actuators, which act on the segments of the radially inner housing wall and the shroud takes a relatively large amount of space, which increases the overall dimensions of the turbomachine.
  • the document EP 1 655 455 A1 relates to a turbomachine having an adjustable vane support for radial clearance adjustment between a shroud formed by the vane carrier and the tips of blades rotating within the shroud.
  • the shroud ring is segmented and concentrically indicated by a trained as a coupling ring adjusting device.
  • a plurality of circumferentially ramped surfaces are arranged, which cooperate with cylindrical rollers on the coupling ring.
  • the present invention is based on the problem to provide an alternative adjustment of the shroud, which is reliable and has small radial dimensions.
  • a turbomachine according to claim 1. Thereafter, the outer ring is concentrically surrounded by a trained as a coupling ring adjusting device, wherein opposing surfaces of the shroud and the actuator are contoured frustoconical, and wherein between the shroud and the adjusting device in the radial direction and circumferentially with respect to the axial obliquely hired, cylindrical rolling elements are positioned, so that the adjusting device with respect to the shroud with simultaneous adjustment of the gap is rotatable.
  • the inventive concept of an Active Clearance Control on a turbomachine comes with a relatively small space, so that only slightly increases the overall size of a turbomachine. Due to the relatively simple structural design, the turbomachine is also susceptible to wear. Furthermore, only small adjustment forces are required to rotate the ring-like adjusting device relative to the jacket ring for adjusting the gap. Another advantage is that the assemblies involved are predominantly subjected to tension and compression, but are exposed to little or no bending stress.
  • the present invention relates to a turbomachine, in particular a gas turbine, such as e.g. a gas turbine aircraft engine.
  • a turbomachine in particular a gas turbine, such as e.g. a gas turbine aircraft engine.
  • Such turbomachines have at least one compressor, at least one combustion chamber and at least one turbine, wherein both in the region of the or each compressor and in the region of the or each turbine, a stator and a rotor is present.
  • the rotor of a compressor or a turbine comprises a plurality of rotating blades.
  • the stator of a compressor or a turbine comprises a housing and a plurality of stationary vanes.
  • the blades associated with the rotor rotate with respect to the fixed housing and fixed stator vanes, the vanes forming vane rings and the rotor blades forming rotor blades.
  • a rotor blade ring is positioned between two guide vane rings arranged one behind the other in the direction of flow.
  • a gap is formed between a radially outer end of a blade ring and a radially inner housing wall of the housing, which is referred to as a shroud, which optimally optimizes the efficiency of the turbomachine must be small.
  • the present invention now relates to such details of a turbomachine, by means of which the gap between the radially outer end of a blade ring and the radially inner housing wall or the outer ring of a housing in the sense of an Active Clearance Control can be automatically influenced or changed.
  • the invention is preferably used in the region of a compressor of a turbomachine.
  • the invention is not limited to use in the area of the compressor, but the invention can also be used in the area of a turbine of a turbomachine.
  • Fig. 1 shows a highly schematic section of a turbomachine according to the invention according to a first aspect of the present invention.
  • Fig. 1 a radially inner housing wall or a shroud 10 of a stator of a compressor of a gas turbine, wherein the shroud 10 encloses a rotor blade, not shown. Between the shroud 10 and a radially outer end of the rotor blade ring, not shown, a likewise not shown gap is formed.
  • the shroud 10 is concentrically surrounded by a trained as a coupling ring adjusting device 11.
  • Fig. 1 are opposing surfaces 12, 13 of the outer ring 10 and adjusting device 11 frustoconically contoured, being formed between the opposing surfaces 12 and 13 of the outer ring 10 and adjusting device 11 and thus formed between the outer ring 10 and actuator 11 as cylindrical rollers rolling elements 14, the relatively are employed obliquely to the axial direction of the shroud 10 in the radial direction and in the circumferential direction.
  • the adjusting device 11 can be rotated relative to the shroud 10. Since the opposing surfaces 12 and 13 of the outer ring 10 and adjusting device 11 are frustoconical contoured and the rolling elements 14 are employed obliquely relative to the axial direction of the shroud 10, this rotation of the actuating device 11 relative to the housing wall 10 in the direction of the arrow 15 continues in the sense of Arrow 16 a translational displacement of the adjusting device 11 relative to the shroud 10, due to which the diameter of the shroud 10 and thus the gap between the shroud 10 and the blade ring, not shown, can be adjusted simultaneously.
  • rolling elements 14 are preferably formed as so-called cage-guided rollers.
  • the gap of the gap reduced in size in relation to an initial dimension, in a second direction of rotation of the adjusting device 11, the gap dimension can be increased relative to the initial dimension.
  • These rolling elements 14 are inclined relative to the axial extension of the housing wall 10 and thus relative to the axial extension of the turbomachine in the circumferential direction and in the radial direction, wherein the opposing surfaces 12, 13 of the outer ring 10 and adjusting device 11, between which the rolling elements 14 are arranged frustoconically contoured are.
  • the rotation of the actuating device 11 relative to the shroud 10 further causes an axial displacement of the adjusting device 11 relative to the shroud 10.
  • the actuating device 11 is screwed onto the shroud 10, so to speak.
  • the executed in a relatively thick wall thickness adjusting device 11 deforms the executed in a relatively thin wall thickness shroud 10 in the sense of elastic deformation, so adjusted by turning the actuator 11 relative to the shroud 10, the diameter of the shroud 10 and thus the gap between the shroud and the blade ring can be adjusted. It is also possible to manufacture the adjusting device 11 from a stiffer material than the shroud 10,
  • the inventive mechanism for providing an active clearance control on a turbomachine is characterized by a compact design with a low Height from. There are only small adjustment forces and no holding forces required. Components are mainly loaded on train and pressure, but are exposed to little or no bending load

Landscapes

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

Claims (5)

  1. Turbomachine avec un stator et un rotor, le rotor présentant des aubes mobiles et le stator un boîtier et des aubes directrices, les aubes mobiles côté rotor formant au moins une couronne d'aubes mobiles qui est contiguë au niveau de son extrémité radialement extérieure à une paroi radialement intérieure, réalisée comme un anneau d'enveloppe du boîtier, est entourée par celui-ci et délimite une fente avec celui-ci, et la fente entre l'anneau d'enveloppe du boîtier et l'extrémité radialement extérieure de la ou de chaque couronne d'aubes mobiles pouvant être réglée par déformation de l'anneau d'enveloppe, l'anneau d'enveloppe (10) étant entouré de manière concentrique par un dispositif de réglage (11) réalisé comme un anneau d'accouplement, caractérisée en ce que des surfaces opposées (12, 13) de l'anneau d'enveloppe (10) et du dispositif de réglage (11) présentent un contour tronconique et en ce qu'entre l'anneau d'enveloppe (10) et le dispositif de réglage (11) sont positionnés des corps de roulement (14) cylindriques, placés en biais dans le sens radial et dans le sens périphérique par rapport au sens axial de sorte que le dispositif de réglage (11) puisse être tourné par rapport à l'anneau d'enveloppe (10) en réglant simultanément la fente.
  2. Turbomachine selon la revendication 1, caractérisée en ce que lors de la rotation du dispositif de réglage (11) réalisé comme anneau d'accouplement par rapport à l'anneau d'enveloppe (10), le dispositif de réglage peut être réglé par rapport à l'anneau d'enveloppe (10) dans le sens axial en déformant élastiquement simultanément l'anneau d'enveloppe (10) pour le réglage de la fente.
  3. Turbomachine selon la revendication 1 ou 2, caractérisée en ce que dans un premier sens de rotation du dispositif de réglage (11), une dimension de la fente peut être réduite par rapport à une dimension de départ définie par une position de départ du dispositif de réglage (11), et en ce que dans un second sens de rotation du dispositif de réglage (11), une dimension de la fente peut être agrandie par rapport à une dimension de départ définie par une position de départ du dispositif de réglage (11).
  4. Turbomachine selon l'une ou plusieurs quelconques des revendications 1 à 3, caractérisée en ce que le dispositif de réglage (11) est réalisée relativement à paroi épaisse et l'anneau d'enveloppe (10) est réalisé relativement à paroi mince.
  5. Turbomachine selon l'une ou plusieurs quelconques des revendications 1 à 4, caractérisée en ce que le dispositif de réglage (11) est fabriqué dans un matériau plus rigide que l'anneau d'enveloppe (10).
EP08706764A 2007-01-20 2008-01-16 Turbomachine avec controle de jeu actif Not-in-force EP2129875B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007003028A DE102007003028A1 (de) 2007-01-20 2007-01-20 Turbomaschine
PCT/DE2008/000067 WO2008086782A2 (fr) 2007-01-20 2008-01-16 Turbomachine

Publications (2)

Publication Number Publication Date
EP2129875A2 EP2129875A2 (fr) 2009-12-09
EP2129875B1 true EP2129875B1 (fr) 2011-03-09

Family

ID=39530809

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08706764A Not-in-force EP2129875B1 (fr) 2007-01-20 2008-01-16 Turbomachine avec controle de jeu actif

Country Status (7)

Country Link
US (1) US8376691B2 (fr)
EP (1) EP2129875B1 (fr)
AT (1) ATE501340T1 (fr)
CA (1) CA2676012A1 (fr)
DE (2) DE102007003028A1 (fr)
ES (1) ES2358165T3 (fr)
WO (1) WO2008086782A2 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070162152A1 (en) * 2005-03-31 2007-07-12 Massachusetts Institute Of Technology Artificial joints using agonist-antagonist actuators
DE102008042262B4 (de) 2008-09-22 2010-05-27 Bundesdruckerei Gmbh Verfahren zur Speicherung von Daten, Computerprogrammprodukt, ID-Token und Computersystem
DE102008042582A1 (de) 2008-10-02 2010-04-08 Bundesdruckerei Gmbh Telekommunikationsverfahren, Computerprogrammprodukt und Computersystem
EP2233701A1 (fr) 2009-03-26 2010-09-29 Siemens Aktiengesellschaft Turbomachine axiale avec support d'aube directrice axialement mobile
US9784117B2 (en) 2015-06-04 2017-10-10 United Technologies Corporation Turbine engine tip clearance control system with rocker arms
US9752450B2 (en) * 2015-06-04 2017-09-05 United Technologies Corporation Turbine engine tip clearance control system with later translatable slide block

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3227418A (en) * 1963-11-04 1966-01-04 Gen Electric Variable clearance seal
US4127357A (en) * 1977-06-24 1978-11-28 General Electric Company Variable shroud for a turbomachine
GB2416194B (en) * 2004-07-15 2006-08-16 Rolls Royce Plc A spacer arrangement
DE102004037955A1 (de) 2004-08-05 2006-03-16 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine
EP1655455A1 (fr) * 2004-11-05 2006-05-10 Siemens Aktiengesellschaft Dispositif pour régler le jeu radial des aubes de guidage d'une turbomachine

Also Published As

Publication number Publication date
WO2008086782A2 (fr) 2008-07-24
EP2129875A2 (fr) 2009-12-09
WO2008086782A3 (fr) 2009-11-19
US20100054921A1 (en) 2010-03-04
DE502008002810D1 (en) 2011-04-21
US8376691B2 (en) 2013-02-19
DE102007003028A1 (de) 2008-07-24
ES2358165T3 (es) 2011-05-06
ATE501340T1 (de) 2011-03-15
CA2676012A1 (fr) 2008-07-24

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