EP2696039B1 - Étage de turbine à gaz - Google Patents

Étage de turbine à gaz Download PDF

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Publication number
EP2696039B1
EP2696039B1 EP12179978.7A EP12179978A EP2696039B1 EP 2696039 B1 EP2696039 B1 EP 2696039B1 EP 12179978 A EP12179978 A EP 12179978A EP 2696039 B1 EP2696039 B1 EP 2696039B1
Authority
EP
European Patent Office
Prior art keywords
gas
wall
guide
end faces
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.)
Not-in-force
Application number
EP12179978.7A
Other languages
German (de)
English (en)
Other versions
EP2696039A1 (fr
Inventor
Hans-Peter Dr. Hackenberg
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 AG
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 AG filed Critical MTU Aero Engines AG
Priority to ES12179978.7T priority Critical patent/ES2547340T3/es
Priority to EP12179978.7A priority patent/EP2696039B1/fr
Priority to US13/959,021 priority patent/US20140044537A1/en
Publication of EP2696039A1 publication Critical patent/EP2696039A1/fr
Application granted granted Critical
Publication of EP2696039B1 publication Critical patent/EP2696039B1/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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex

Definitions

  • the present invention relates to a gas turbine stage, in particular a low-pressure compressor stage, with a vane assembly and a sealing ring element, a gas turbine, in particular an aircraft gas turbine engine with one or more such gas turbine stages, and a vane assembly and a sealing ring member for such a gas turbine.
  • an inner wall of one of a vane assembly and a sealing ring member engages a circumferential groove of the other of the vane assembly and the sealing ring member.
  • the inner wall has, after Radiointemer practice in a development in the circumferential direction or in a plan view of the spokes center a rectangular cross-section with two opposite, the Nutinnen vom the circumferential groove facing end faces and two against this by 90 ° angled flanks in one edge into each other pass.
  • the object of the present invention is to provide an improved gas turbine.
  • a gas turbine in particular an aircraft gas turbine engine, one or more gas turbine stages, in particular low-pressure compressor stages, which according to another aspect of the present invention each have a vane assembly with one or more vanes with a radially inner Leitschaufelfuß. Two or more vanes may be connected together in a development, in particular integrally.
  • a sealing ring element On the vane a sealing ring element is supported by a spokes centering, which has an inner wall and a circumferential groove receiving this.
  • a circumferential groove is understood as meaning, in particular, a recess or recess circulating in the circumferential direction and bounded on both sides by, in particular, parallel, groove inner surfaces.
  • a sealing ring element may be part of a multi-part closed sealing ring.
  • a one-piece sealing ring is generally referred to as a sealing ring element in the sense of the present invention.
  • the inner wall has two mutually opposite, preferably parallel end faces, each facing a Nutinnen Chemistry the circumferential groove and in an undeformed state in particular, at least substantially, can be oriented normal to an axial direction of the gas turbine stage.
  • a rounding in particular a radius, is formed between at least one of these end faces and at least one of these flanks.
  • a rounding means in particular, a connecting surface which is mono- or multiply, in particular convexly curved, which may in particular have radially extending straight generatrices, wherein in one development the rounding can be formed kink-free or with continuous curvature.
  • the inner wall of the spoke centering can be connected to the guide blade root, in particular integrally, and the circumferential groove can be formed on the sealing ring element.
  • the inner wall with the sealing ring member, in particular integrally connected and the circumferential groove may be formed on the Leitschaufelfuß.
  • a vane assembly for the gas turbine (n-stage) described herein having an inner wall connected thereto for receiving in a circumferential groove to form a spoke centering of the seal member on the vane assembly, the inner wall at least one of a Nutinnen character the circumferential groove facing end face and one of these adjacent, against this angled edge, and wherein between the end face and the flank a rounding, in particular a radius is formed.
  • the present embodiments in particular advantageous developments, therefore relate equally to such a vane arrangement or such a sealing ring element, a gas turbine stage and a gas turbine with such a spoke centering.
  • the inner wall has at least one radial groove for receiving a sliding element, in particular a sliding block connected to the circumferential groove, for forming the spoke centering.
  • this radius has at least 25%, in particular at least 30%, of a width of the flank.
  • a width of a flank is understood in particular to mean its axial width or the wall thickness of the inner wall.
  • the radius may be at least 0.5 mm, in particular at least 10 mm, and preferably at least 15 mm.
  • a rounding can in particular together with the inner wall or its end face (s) and flank (s) urgeformt, in particular cast. Additionally or alternatively, the fillet may preferably be reshaped and / or machined or made.
  • a rounding can be hardened, in particular by a corresponding thermal method and / or a coating. As a result, in particular the wear in the area of the rounding can be further reduced.
  • the present invention is particularly advantageous for the spoke centering of a brush seal element.
  • a vane arrangement may have a torsion preferential direction, which may for example result from a setting and / or a profile of the guide vanes or the like.
  • this is understood in particular to mean a torsional direction about a radial axis, into which the guide vane (s) of the vane arrangement are twisted during operation with increasing flow and / or power of the gas turbine (n stage).
  • a rounding is then provided in particular also or only at one end of the end face (s) in the circumferential direction, which is delivered in torsion in the Torsionsvorzugsraum against the adjacent Nutinnen Diagram.
  • Fig. 1 shows a meridian section of a portion of a gas turbine with a gas turbine stage with a vane assembly according to an embodiment of the present invention.
  • Guide vane assembly shown in a perspective view has a plurality of integrally interconnected vanes 1 with a common, radially inner Leitschaufelfuß 1.1, from which a common inner wall 1.2 from a side facing away from the vane blade (bottom in Fig. 1 . 2 ) of the guide blade root 1.1 starting radially inward (down in Fig. 1 . 2 ).
  • a radial groove 1.3 is formed in the inner wall 1.2 a radial groove 1.3 is formed.
  • a sliding block is arranged radially movable, which is connected to a circumferential groove with two legs 2.1, 2.2, which is formed in a brush seal ring element 2.
  • the brush seal element 2 is mounted on the guide vane arrangement in a memory-centered manner.
  • the inner wall 1.2 which is disposed between the two legs 2.1, 2.2 of the circumferential groove of the brush seal member 2, two parallel planar axial end faces 1.4, which are oriented in an undeformed position of the vanes 3 normal to an axial direction of the gas turbine (n) stage ie in Fig. 3 run vertically.
  • These two end faces 1.4 are connected by two parallel planar flanks 1.5, which are angled perpendicular to the end faces 1.4.

Claims (13)

  1. Etage de turbine à gaz, en particulier étage de compresseur basse pression, destiné à une turbine à gaz, en particulier à une turbine à gaz d'un système de propulsion d'aéronef, comprenant un ensemble d'aubes directrices pourvu d'au moins une aube directrice (1) dotée d'une emplanture d'aube directrice (1.1) intérieure radialement, au niveau de laquelle est monté un élément de bague d'étanchéité (2) à travers un centrage à rayons, qui présente une paroi intérieure (1.2) et une rainure périphérique (2.1, 2.2) accueillant celle-ci, la paroi intérieure présentant, selon une projection dans le sens périphérique, deux faces frontales (1.4) se faisant face l'une l'autre, tournées respectivement vers une face intérieure de rainure de la rainure périphérique et deux flancs (1.5) se faisant face l'un l'autre, reliant lesdites faces frontales et accoudés contre celles-ci,
    caractérisé en ce
    qu'un arrondi, en particulier un rayon (R), est réalisé entre au moins une desdites faces frontales et au moins un desdits flancs.
  2. Etage de turbine à gaz selon la revendication 1, caractérisé en ce que la paroi intérieure (1.2) est reliée, en particulier intégralement, à l'emplanture d'aube directrice (1.1), et en ce que la rainure périphérique (2.1, 2.2) est réalisée au niveau de l'élément de bague d'étanchéité (2).
  3. Etage de turbine à gaz selon la revendication 1, caractérisé en ce que la paroi intérieure est reliée, en particulier intégralement, à l'élément de bague d'étanchéité, et en ce que la rainure périphérique est réalisée au niveau de l'emplanture d'aube directrice.
  4. Etage de turbine à gaz selon l'une quelconque des revendications précédentes, caractérisé par au moins deux aubes directrices (1) reliées, en particulier intégralement, les unes aux autres, pourvues d'une paroi intérieure (1.2) ou d'une rainure périphérique commune.
  5. Etage de turbine à gaz selon l'une quelconque des revendications précédentes, caractérisé en ce que la paroi intérieure présente une rainure radiale (1.3) servant à accueillir un élément coulissant servant à réaliser le centrage à rayons.
  6. Etage de turbine à gaz selon l'une quelconque des revendications précédentes, caractérisé en ce que le rayon (R) présente au moins 25 %, en particulier au moins 30 % d'une largeur du flanc.
  7. Etage de turbine à gaz selon l'une quelconque des revendications précédentes, caractérisé en ce que le rayon (R) est égal à au moins 0,5 mm, en particulier à au moins 10 mm, de préférence à au moins 15 mm.
  8. Etage de turbine à gaz selon l'une quelconque des revendications précédentes, caractérisé en ce que l'arrondi (R) est fabriqué par une première transformation, par une transformation ou par enlèvement de copeaux et/ou est durci.
  9. Etage de turbine à gaz selon l'une quelconque des revendications précédentes, caractérisé en ce que l'élément de bague d'étanchéité est un élément de bague d'étanchéité à brosses (2).
  10. Etage de turbine à gaz selon l'une quelconque des revendications précédentes, caractérisé en ce que l'arrondi (R) est prévu au niveau d'une extrémité de la face frontale (1.4) dans le sens périphérique, laquelle est approchée, en cas de torsion dans un sens préférentiel de torsion de l'ensemble d'aubes directrices, contre la face intérieure de rainure adjacente.
  11. Turbine à gaz, en particulier turbine à gaz d'un système de propulsion d'aéronef, comprenant au moins un étage de turbine à gaz selon l'une quelconque des revendications précédentes.
  12. Ensemble d'aubes directrices pour une turbine à gaz selon la revendication précédente, comprenant au moins une aube directrice (1) pourvue d'une emplanture d'aube directrice (1.1) intérieure radialement et d'une paroi intérieure (1.2) reliée à celle-ci, qui est prévue pour être accueillie dans une rainure périphérique (2.1, 2.2) d'un élément de bague d'étanchéité (2) de la turbine à gaz, la paroi intérieure présentant, selon une projection dans le sens périphérique, deux faces frontales (1.4) se faisant face l'une l'autre, tournées respectivement vers une face intérieure de rainure de la rainure périphérique et deux flancs (1.5) se faisant face l'un l'autre, reliant lesdites faces frontales et accoudés contre celles-ci, et un arrondi, en particulier un rayon (R), étant réalisé entre au moins une desdites faces frontales et au moins un desdits flancs.
  13. Elément de bague d'étanchéité pour une turbine à gaz selon la revendication précédente, comprenant une paroi intérieure reliée à celle-ci, qui est prévue pour être reçue dans une rainure périphérique d'un ensemble d'aubes directrices de la turbine à gaz, la paroi intérieure présentant, selon une projection dans le sens périphérique, deux faces frontales se faisant face l'une l'autre, tournées respectivement vers une face intérieure de rainure de la rainure périphérique et deux flancs se faisant face l'un l'autre, reliant lesdites faces frontales et accoudés contre celles-ci, et un arrondi, en particulier un rayon (R), étant réalisé entre au moins une desdites faces frontales et au moins un desdits flancs.
EP12179978.7A 2012-08-10 2012-08-10 Étage de turbine à gaz Not-in-force EP2696039B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES12179978.7T ES2547340T3 (es) 2012-08-10 2012-08-10 Grado de turbina de gas
EP12179978.7A EP2696039B1 (fr) 2012-08-10 2012-08-10 Étage de turbine à gaz
US13/959,021 US20140044537A1 (en) 2012-08-10 2013-08-05 Gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12179978.7A EP2696039B1 (fr) 2012-08-10 2012-08-10 Étage de turbine à gaz

Publications (2)

Publication Number Publication Date
EP2696039A1 EP2696039A1 (fr) 2014-02-12
EP2696039B1 true EP2696039B1 (fr) 2015-07-29

Family

ID=46967917

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12179978.7A Not-in-force EP2696039B1 (fr) 2012-08-10 2012-08-10 Étage de turbine à gaz

Country Status (3)

Country Link
US (1) US20140044537A1 (fr)
EP (1) EP2696039B1 (fr)
ES (1) ES2547340T3 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016202519A1 (de) 2016-02-18 2017-08-24 MTU Aero Engines AG Leitschaufelsegment für eine Strömungsmaschine
DE102016222608A1 (de) 2016-11-17 2018-05-17 MTU Aero Engines AG Dichtungsanordnung für eine Leitschaufelanordnung einer Gasturbine
ES2828719T3 (es) * 2017-11-09 2021-05-27 MTU Aero Engines AG Disposición de sellado para una turbomáquina, método para la fabricación de una disposición de sellado y turbomáquina
DE102018213983A1 (de) 2018-08-20 2020-02-20 MTU Aero Engines AG Verstellbare Leitschaufelanordnung, Leitschaufel, Dichtungsträger und Turbomaschine
DE102020203840A1 (de) 2020-03-25 2021-09-30 MTU Aero Engines AG Gasturbinenbauteil

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3829233A (en) * 1973-06-27 1974-08-13 Westinghouse Electric Corp Turbine diaphragm seal structure
US5224822A (en) * 1991-05-13 1993-07-06 General Electric Company Integral turbine nozzle support and discourager seal
US5749584A (en) * 1992-11-19 1998-05-12 General Electric Company Combined brush seal and labyrinth seal segment for rotary machines
US6832891B2 (en) * 2001-10-29 2004-12-21 Man Turbomaschinen Ag Device for sealing turbomachines
US20110150640A1 (en) * 2003-08-21 2011-06-23 Peter Tiemann Labyrinth Seal in a Stationary Gas Turbine
US7160078B2 (en) * 2004-09-23 2007-01-09 General Electric Company Mechanical solution for rail retention of turbine nozzles
GB2425155B (en) * 2005-04-13 2007-09-19 Rolls Royce Plc A mounting arrangement
US7360988B2 (en) * 2005-12-08 2008-04-22 General Electric Company Methods and apparatus for assembling turbine engines
DE102010007724A1 (de) * 2010-02-12 2011-08-18 Rolls-Royce Deutschland Ltd & Co KG, 15827 Schraubenlose Zwischenstufendichtung einer Gasturbine

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Publication number Publication date
EP2696039A1 (fr) 2014-02-12
ES2547340T3 (es) 2015-10-05
US20140044537A1 (en) 2014-02-13

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