EP0589736B1 - Turbomaschine mit einer Vorrichtung zur Vermeidung von axialen Gasströmen um Statorstufen - Google Patents

Turbomaschine mit einer Vorrichtung zur Vermeidung von axialen Gasströmen um Statorstufen Download PDF

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Publication number
EP0589736B1
EP0589736B1 EP93402092A EP93402092A EP0589736B1 EP 0589736 B1 EP0589736 B1 EP 0589736B1 EP 93402092 A EP93402092 A EP 93402092A EP 93402092 A EP93402092 A EP 93402092A EP 0589736 B1 EP0589736 B1 EP 0589736B1
Authority
EP
European Patent Office
Prior art keywords
casing
shoe
turbomachine
leg
rib
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.)
Expired - Lifetime
Application number
EP93402092A
Other languages
English (en)
French (fr)
Other versions
EP0589736A1 (de
Inventor
Jean-Louis Charbonnel
Pierre Debeneix
Christopher Charles Glynn
Daniel Jean Marey
Jean-Pierre André Joseph Mourlan
Jacky Serge Naudet
Gérard Receveur
Roger Clayton Walker
Yann Joel Marie Rigaud
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.)
Safran Aircraft Engines SAS
General Electric Co
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
General Electric Co
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS, General Electric Co filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0589736A1 publication Critical patent/EP0589736A1/de
Application granted granted Critical
Publication of EP0589736B1 publication Critical patent/EP0589736B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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

Definitions

  • the invention relates to a turbomachine equipped with a device preventing the longitudinal or axial circulation of gas around the stages of vanes for straightening the flow in the machine.
  • the stator of many turbomachinery consists of a double envelope: an outer casing which surrounds a ferrule formed of elements assembled together and to which the blades of the rectifier stages are fixed.
  • the ferrule elements are screwed to the casing and provided with circular ribs of radial extension which maintain the spacing between the ferrule and the casing to which they touch by their end edge.
  • these ribs are responsible for a significant loss of heat to the outside due to their good thermal conductivity, they are perforated so as to only touch the casing by portions of circumference.
  • the invention represents a possible and particularly simple solution for this. It relates to a turbomachine comprising a casing surrounding ferrule elements to which blades of rectifier stages are fixed, the ferrule elements being connected to the casing by bolts, the ferrule elements being provided with ribs which separate them from the casing and s' extend to the casing, the ribs being provided with days so as to touch the casing only by portions of circumference, and comprising annular sealing parts characterized in that said annular sealing parts are composed of a sole circular and of a leg extending substantially radially inwards from the sole to a bearing surface extending in a radial plane of an associated rib, the leg covering the days of the rib and rubbing on the bearing surface, the casing being provided for each sealing part with a step delimited by a radial compression surface of the sole and a surface e longitudinal compression of the sole against the associated rib, and the bolts extend with a
  • the outer casing is a slightly conical envelope designated by 1 in FIG. 1 and which can be formed from parts assembled together.
  • the casing 1 surrounds ferrule elements 2, which are also substantially conical, placed end to end and assembled by interlocking seals 3 to form a single continuous ferrule and approximately parallel to the casing 1.
  • Each ferrule element 2 carries a stationary stator or stator vane stage 4.
  • a stage of movable rotor blades 5 extends between each pair of stages of fixed blades 4.
  • Each ferrule element 2 is provided with a rib 6 which extends from it outwards in a radial direction to touch the casing 1 by its outer edge 7. At each rib 6 is joined a sealing piece 8 characteristic of the invention and which will be described later.
  • Each rib 6 is finally provided with a circular outer sole 9 and completed from place to place by a block 10 which then faces another block 11 corresponding to a bulge of the casing 1 outwards.
  • the blocks 10 and 11 are crossed by holes which come in extension and which a bolt 12 occupies.
  • the assemblies constituted by the shell elements 2, the ribs 6 and the flanges 9 are then securely fixed to the casing 1.
  • the ribs 6 divide the volume between the casing 1 and the shell 2 into compartments into each of which opens a gas supply device. for adjusting the clearances between the ferrule portion 2 and the stages of movable blades 5 associated with these portions. These devices are not part of the invention.
  • each rib 6 is perforated over a large part of its length, and the edge 7 is formed of interrupted fragments. Days 14 (better visible in FIG. 3) extend over most of the height of the ribs 6 and up to the casing 1 in the radial direction so that the ribs 6 only touch the casing 1 by fairly large portions. tall and narrow which greatly limit the heat transmitted.
  • the ribs 6 are provided near the ferrule elements 2 with a bearing surface 15 situated in a radial plane and oriented towards the sealing part 8, and the flanges 9 comprise another bearing surface 16 belonging to the same plane.
  • the casing 1 is designed with a circular surface 17 on which the sole 9 rests in a radial direction and another sole 18 which forms the sealing part 8 with a leg 19, and with a compression surface 20 which extends in a transverse plane and serves to compress the sole 18 against the bearing surface 16; the two surfaces 17 and 20 form a step in the casing 1.
  • the sealing parts 8 are rings without interruptions on the circumference.
  • the legs 19 are composed of an upper part 21 which extends from the sole 18 radially, but with a longitudinal inclination towards the associated rib 6, and of a purely radial end portion 22 which terminates the upper part 21 and has a bearing surface 23 which is intended to be pressed against the bearing surface 15 of the rib 6.
  • the portion end 22 protrudes at least partially from the sole 18 in the longitudinal direction when the sealing part 8 is disassembled, which is shown by the dashes.
  • the tightening of the bolts 12 causes both a longitudinal displacement of the sealing part 8 towards the rib 6, which results in an elastic bending of the leg 19 when the surfaces 15 and 23 come to touch and to rub against each other, and a radial displacement by virtue of the contraction exerted on the sole 18 by the surface 17.
  • the surfaces 15, 17 and 20, as well as the surfaces of the sealing part 8 which rest on them, are of low roughness to prevent any significant passage of gas between the compartments: they can for example be rotated.
  • the axis X of the bolts 12 has an inclination, counted from the radial direction in a longitudinal plane, which can be approximately 40 or 50 ° depending on whether one seeks to promote axial or radial compression, which is a particular question to each achievement. It is also possible to choose another inclination.
  • the mounting of the sealing parts 8 does not raise any particular difficulties because they can be introduced through the enlarged mouth of the conical casing 1.
  • the shell elements 2 are then mounted and bolted.

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)

Claims (3)

  1. Turbomaschine mit einem Gehäuse (1), das Kranzelemente (2) umgibt, an denen die Schaufeln (4) der Statorstufen befestigt sind, wobei die Kranzelemente mit dem Gehäuse durch Bolzen (12) verbunden und mit Ansätzen (6) versehen sind, die sie von dem Gehäuse trennen und sich bis zu dem Gehäuse erstrecken, wobei die Ansätze mit Ausnehmungen (14) versehen sind, so daß sie das Gehäuse nur mit Umfangsabschnitten berühren, und ringförmige Dichtteile (8) aufweisen,
    dadurch gekennzeichnet,
    daß die ringförmigen Dichtteile aus einer kreisringförmigen Sohle (18) und einer Strebe (19) bestehen, die sich im wesentlichen radial nach innen ausgehend von der Sohle bis zu einer Anschlagfläche (15) erstreckt, die sich in einer Radialebene eines zugeordneten Ansatzes erstreckt, wobei die Strebe die Ausnehmungen des Ansatzes überdeckt und auf der Anschlagfläche (15) schleift, das Gehäuse für jedes Dichtteil mit einer Stufe versehen ist, die durch eine radiale Kompressionsfläche (17) der Sohle (18) und eine longitudinale Kompressionsfläche (20) der Sohle gegen den zugeordneten Ansatz abgegrenzt ist, und sich die Bolzen (12) mit einer Längsneigung erstrecken, die gleichzeitig die beiden Kompressionen hervorruft.
  2. Turbomaschine nach Anspruch 1,
    dadurch gekennzeichnet,
    daß die Neigung der Bolzen zwischen 40° und 50° bezüglich der Radialrichtung beträgt.
  3. Turbomaschine nach einem der Ansprüche 1 oder 2,
    dadurch gekennzeichnet,
    daß die Strebe eine Fläche (23) aufweist, die sich in einer Radialebene erstreckt und dazu bestimmt ist, gegen die Anschlagfläche gedrückt zu werden, wobei die Fläche der Strebe in der Längsrichtung über die Sohle hinausgeht, wenn das Dichtteil (8) abgebaut ist.
EP93402092A 1992-08-26 1993-08-25 Turbomaschine mit einer Vorrichtung zur Vermeidung von axialen Gasströmen um Statorstufen Expired - Lifetime EP0589736B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9210278A FR2695164B1 (fr) 1992-08-26 1992-08-26 Turbomachine munie d'un dispositif empêchant une circulation longitudinale de gaz autour des étages d'aubes de redressement.
FR9210278 1992-08-26

Publications (2)

Publication Number Publication Date
EP0589736A1 EP0589736A1 (de) 1994-03-30
EP0589736B1 true EP0589736B1 (de) 1996-04-03

Family

ID=9433022

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93402092A Expired - Lifetime EP0589736B1 (de) 1992-08-26 1993-08-25 Turbomaschine mit einer Vorrichtung zur Vermeidung von axialen Gasströmen um Statorstufen

Country Status (4)

Country Link
US (1) US5320484A (de)
EP (1) EP0589736B1 (de)
DE (1) DE69302065T2 (de)
FR (1) FR2695164B1 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2711730B1 (fr) * 1993-10-27 1995-12-01 Snecma Turbomachine équipée de moyens de pilotage des jeux entre rotor et stator.
FR2794816B1 (fr) * 1999-06-10 2001-07-06 Snecma Stator de compresseur a haute pression
EP1118806A1 (de) * 2000-01-20 2001-07-25 Siemens Aktiengesellschaft Thermisch belastbare Wand und Verfahren zur Abdichtung eines Spaltes in einer thermisch belasteten Wand
FR2817285B1 (fr) 2000-11-30 2003-06-13 Snecma Moteurs Virole interne de stator
DE10213402A1 (de) * 2002-03-26 2003-12-24 Mtu Aero Engines Gmbh Anordnung zur Befestigung von als Lagerträger für den Rotor einer Fluggasturbine dienenden Streben an der Gehäusestruktur der Fluggasturbine
DE60213621T2 (de) * 2002-12-03 2007-03-08 Techspace Aero S.A. Dichtung für den Niederdruckverdichter eines Flugtriebwerks
US7025563B2 (en) 2003-12-19 2006-04-11 United Technologies Corporation Stator vane assembly for a gas turbine engine
FR2868125B1 (fr) * 2004-03-26 2006-07-21 Snecma Moteurs Sa Turbomachine comprenant deux sous-ensembles assembles sous contrainte axiale
CN104024601B (zh) * 2012-01-16 2017-10-03 博格华纳公司 排气涡轮增压器
CN110284929B (zh) * 2019-07-19 2021-10-22 中国航发沈阳发动机研究所 一种涡轮机匣封严结构

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR896166A (fr) * 1942-07-09 1945-02-14 Wagner Hochdruck Dampfturbinen Support d'aubes directrices pour turbines à vapeur et à gaz, en particulier pour hautes pressions et températures élevées
GB961588A (en) * 1960-02-05 1964-06-24 Licentia Gmbh A stationary-blade carrier for axial-flow turbines
GB1126468A (en) * 1964-09-25 1968-09-05 English Electric Co Ltd Improvements relating to turbines
FR2280791A1 (fr) * 1974-07-31 1976-02-27 Snecma Perfectionnements au reglage du jeu entre les aubes et le stator d'une turbine
US4023919A (en) * 1974-12-19 1977-05-17 General Electric Company Thermal actuated valve for clearance control
US4314793A (en) * 1978-12-20 1982-02-09 United Technologies Corporation Temperature actuated turbine seal
US4318668A (en) * 1979-11-01 1982-03-09 United Technologies Corporation Seal means for a gas turbine engine
GB2076071B (en) * 1980-05-16 1983-11-02 United Technologies Corp Flow directing assembly for a gas turbine engine
US4431373A (en) * 1980-05-16 1984-02-14 United Technologies Corporation Flow directing assembly for a gas turbine engine
US4426191A (en) * 1980-05-16 1984-01-17 United Technologies Corporation Flow directing assembly for a gas turbine engine
US4416111A (en) * 1981-02-25 1983-11-22 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Air modulation apparatus
US4541775A (en) * 1983-03-30 1985-09-17 United Technologies Corporation Clearance control in turbine seals
US4807433A (en) * 1983-05-05 1989-02-28 General Electric Company Turbine cooling air modulation
US4720236A (en) * 1984-12-21 1988-01-19 United Technologies Corporation Coolable stator assembly for a gas turbine engine
DE3708949A1 (de) * 1986-03-21 1987-09-24 Rolls Royce Plc Haltering zur lagesicherung eines bauteils
GB2236147B (en) * 1989-08-24 1993-05-12 Rolls Royce Plc Gas turbine engine with turbine tip clearance control device and method of operation
US5100291A (en) * 1990-03-28 1992-03-31 General Electric Company Impingement manifold

Also Published As

Publication number Publication date
DE69302065D1 (de) 1996-05-09
FR2695164B1 (fr) 1994-11-04
DE69302065T2 (de) 1996-09-12
US5320484A (en) 1994-06-14
FR2695164A1 (fr) 1994-03-04
EP0589736A1 (de) 1994-03-30

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