EP2719869A1 - Étanchéification axiale dans une structure de boîtier pour une turbomachine - Google Patents

Étanchéification axiale dans une structure de boîtier pour une turbomachine Download PDF

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Publication number
EP2719869A1
EP2719869A1 EP12188322.7A EP12188322A EP2719869A1 EP 2719869 A1 EP2719869 A1 EP 2719869A1 EP 12188322 A EP12188322 A EP 12188322A EP 2719869 A1 EP2719869 A1 EP 2719869A1
Authority
EP
European Patent Office
Prior art keywords
cavity
housing structure
flow channel
housing wall
structure according
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.)
Pending
Application number
EP12188322.7A
Other languages
German (de)
English (en)
Inventor
Manfred Feldmann
Janine Dr. Sangl
Sebastian Kaltenbach
Joachim Lorenz
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 EP12188322.7A priority Critical patent/EP2719869A1/fr
Priority to US14/048,169 priority patent/US9605551B2/en
Publication of EP2719869A1 publication Critical patent/EP2719869A1/fr
Pending 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
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • 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

Definitions

  • the present invention relates to a housing structure for a turbomachine, in particular for a gas turbine or an aircraft engine.
  • turbomachines such as gas turbines or aircraft engines
  • air is drawn along a flow channel, compressed, and combusted in a combustion chamber along with fuel, and then the combustion gases are discharged through the flow channel, thereby driving in a turbine rotors.
  • the flow channel is circumferentially surrounded by a housing structure, wherein in particular in the region of the combustion chamber and the subsequent turbine, prevail by the combustion gases very high temperatures in the flow channel, so that surrounding the flow channel housing structure must be efficiently cooled in order to achieve that the lowest possible operating temperatures are present in order to use materials with lower requirements for high-temperature properties.
  • cooling air is passed into the area of the outer housing structure in order to bring about heat dissipation.
  • insulators and heat shields are used in such housing structures to protect the outer components from excessive temperatures.
  • the solution should be easy to implement.
  • the invention is based on the consideration that through cavities in the housing structure a pressure equalization in the axial direction, ie along the flow direction of the hot gas in the flow channel can be effected by the pressure equalization corresponding gas flows are caused, such as the outflow of hot gas from the flow channel in the housing structure or the inflow of cooling air from the housing structure in the flow channel.
  • a pressure equalization in the axial direction ie along the flow direction of the hot gas in the flow channel can be effected by the pressure equalization corresponding gas flows are caused, such as the outflow of hot gas from the flow channel in the housing structure or the inflow of cooling air from the housing structure in the flow channel.
  • the present invention proposes to provide an axial seal in a corresponding cavity between an inner housing wall and an outer housing wall of a housing structure of a turbomachine, so that an axial pressure equalization is prevented as much as possible.
  • the axial sealing at least two areas are created in a cavity, which are arranged one behind the other in the axial direction.
  • the axial sealing takes place in such a way that different pressure conditions can be established in the regions which correspond to the different pressure conditions in the flow channel along the axial direction. This means, for example, that the pressure in the flow channel before a blade stage is higher than after a blade stage, so that correspondingly in a cavity in the housing structure in a region axially corresponding to the region before a blade stage, the pressure ratios are higher than in a region corresponding in position to a blade stage in its axial position ,
  • the axial seal can be arranged in an axial position in the cavity, which corresponds to the axial position between an inlet edge and a trailing edge of a blade, in particular between a first and a second sealing tip of a blade.
  • the leading edge of the blade upstream is understood as the leading edge, which therefore first comes into contact with the flowing hot gases.
  • the trailing edge is the last region of the blade at which the flow gases leave the blade again.
  • axial seals for a cavity In addition to a single axial seal for a cavity of course, several axial seals for a single cavity can be provided and a plurality of cavities with axial seals.
  • the axial sealing can be realized by a cooperating with structural components sealing element, such as a flexible, heat-resistant sealing cord, which can cooperate with appropriately provided sealing walls.
  • structural components sealing element such as a flexible, heat-resistant sealing cord, which can cooperate with appropriately provided sealing walls.
  • other suitable structural components for producing the axial seal can be provided.
  • the cavity which is provided with the axial seal, may be a cavity disposed directly on the inner housing wall, which may be separated from the outer housing wall and in particular spaced apart.
  • that cavity is provided with an axial seal, which is arranged radially inwardly on the inner housing wall.
  • the cavity may be an annular space around the flow channel circumferential cavity or a cavity which is provided only in segments around the flow channel.
  • such cavities can be provided with axial seals, which have a cooling air supply.
  • the attached figure shows in a purely schematic way a part of a housing structure according to the invention in a sectional view.
  • the partial sectional view of the attached figure by an aircraft engine shows an outer housing wall 1 and an inner housing wall 2, which annularly surround a flow channel 15, in the blades 4 and vanes 5 are arranged.
  • the inner housing wall 2 is formed by a lining with a scuffing pad 3, wherein sealing tips 6, 7, which may also be referred to as sealing fins, are arranged on the moving blade 4 in order to provide, together with the scraper pad 3, a seal which may also be referred to as "outer Air seal "is called.
  • seal carrier 8 or heat shields 9, 10 are arranged, which should ensure that the outer housing wall 1 is as low as possible temperature, so as to select the material for the outer housing wall 1 not be limited by taking into account certain operating temperatures.
  • a cavity 11 is formed, which extends along the inner housing wall 2 and which is at least separated from the outer housing wall 1 by the heat shield 10, and at least partially by the outer housing wall 1 is spaced.
  • the cavity 11 is arranged in an annular manner around the flow channel 15 and is formed substantially closed, that is, that no defined openings are provided. Nevertheless, it comes due to the conditions prevailing in the flow channel 15 conditions and by the strong temperature change between operation and non-operation of the turbomachine and consequent structural conditions to a flow of hot gas from the flow channel 15 into the cavity 11. In addition, ambient air or in the Housing structure guided cooling air also penetrate into the cavity 11. Moreover, it is conceivable that the cavity 11 is also designed to guide cooling air and has corresponding openings for the entry of cooling air.
  • a seal is provided in the cavity 11, which comprises two sealing plates 12, 13 and a sealing cord 14, wherein the axial seal 12, 13, 14 divides the cavity 11 into two areas 16, 17.
  • the axial seal with the sealing walls 12 and 13 and the sealing cord 14 is arranged in an axial position corresponding to the axial position between the first and front sealing tip 6 and the second or rear sealing tip 7, so that the first region 16 with the flow channel in front of the Blade 4 corresponds, while the second region 17 corresponds to the region of the flow channel 15 after the blade.
  • the seal 12,13,14 ensures that in the areas 16, 17 different pressure conditions can be adjusted, as in the flow channel in the area in front of the blade 4 and in the area after the blade 4. This avoids that in the cavity 11th a pressure equalization between an axially forward position and an axially rearward position may occur, which could cause exchange flows between the hot gas passage and a possible cooling air flow.
  • the amount of hot gas that flows from the flow channel into the housing structure thus also reducing losses of cooling air, so that the efficiency of the machine is increased, and the temperatures in the housing structure can be lowered, or less cooling air is needed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12188322.7A 2012-10-12 2012-10-12 Étanchéification axiale dans une structure de boîtier pour une turbomachine Pending EP2719869A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP12188322.7A EP2719869A1 (fr) 2012-10-12 2012-10-12 Étanchéification axiale dans une structure de boîtier pour une turbomachine
US14/048,169 US9605551B2 (en) 2012-10-12 2013-10-08 Axial seal in a casing structure for a fluid flow machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12188322.7A EP2719869A1 (fr) 2012-10-12 2012-10-12 Étanchéification axiale dans une structure de boîtier pour une turbomachine

Publications (1)

Publication Number Publication Date
EP2719869A1 true EP2719869A1 (fr) 2014-04-16

Family

ID=47080314

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12188322.7A Pending EP2719869A1 (fr) 2012-10-12 2012-10-12 Étanchéification axiale dans une structure de boîtier pour une turbomachine

Country Status (2)

Country Link
US (1) US9605551B2 (fr)
EP (1) EP2719869A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3179053A1 (fr) * 2015-12-07 2017-06-14 MTU Aero Engines GmbH Structure de carter de turbomachine avec écran de protection thermique
EP2725203B1 (fr) * 2012-10-23 2019-04-03 MTU Aero Engines AG Conduite d'air froid dans une structure de boîtier d'une turbomachine
EP3000990B1 (fr) 2014-09-26 2019-05-29 Rolls-Royce plc Dispositif de retenue de virole d'une turbine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2984296B1 (fr) * 2013-04-12 2020-01-08 United Technologies Corporation Joint étanche à l'air extérieur de pale comportant une étanchéité à l'air secondaire
WO2015084550A1 (fr) * 2013-12-03 2015-06-11 United Technologies Corporation Écrans thermiques pour joints d'étanchéité à l'air
US10196912B2 (en) * 2014-10-24 2019-02-05 United Technologies Corporation Bifurcated sliding seal
US10370994B2 (en) 2015-05-28 2019-08-06 Rolls-Royce North American Technologies Inc. Pressure activated seals for a gas turbine engine
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
DE102021124357A1 (de) 2021-09-21 2023-03-23 MTU Aero Engines AG Hitzeschutzelement für eine Lagerkammer einer Gasturbine

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3656862A (en) * 1970-07-02 1972-04-18 Westinghouse Electric Corp Segmented seal assembly
US4053254A (en) * 1976-03-26 1977-10-11 United Technologies Corporation Turbine case cooling system
DE2745130A1 (de) * 1977-10-07 1979-04-12 Motoren Turbinen Union Einrichtung zur einhaltung bestimmter ausmasse von dichtspalten zwischen laufschaufel- und/oder leitschaufelspitzen und der damit zusammenwirkenden dichtungen fuer gasturbinentriebwerke
US4925365A (en) * 1988-08-18 1990-05-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine stator ring assembly
GB2226365A (en) * 1988-12-22 1990-06-27 Rolls Royce Plc Turbomachine clearance control
EP0937864A2 (fr) * 1998-02-20 1999-08-25 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Configuration des aubes de guidage pour une turbomachine axiale
EP0940562A2 (fr) * 1998-03-03 1999-09-08 Mitsubishi Heavy Industries, Ltd. Turbine à gaz
EP1106785A1 (fr) * 1999-12-07 2001-06-13 Rolls-Royce Deutschland Ltd & Co KG Conduit pour fluide de fuite dans le rotor d'une turbomachine
US20050232752A1 (en) * 2004-04-15 2005-10-20 David Meisels Turbine shroud cooling system
US8011879B2 (en) * 2006-10-06 2011-09-06 Snecma Transition channel between two turbine stages

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4728257A (en) * 1986-06-18 1988-03-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal stress minimized, two component, turbine shroud seal
GB9027986D0 (en) 1990-12-22 1991-02-13 Rolls Royce Plc Gas turbine engine clearance control
DE10122464C1 (de) 2001-05-09 2002-03-07 Mtu Aero Engines Gmbh Mantelring
US6997673B2 (en) * 2003-12-11 2006-02-14 Honeywell International, Inc. Gas turbine high temperature turbine blade outer air seal assembly

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3656862A (en) * 1970-07-02 1972-04-18 Westinghouse Electric Corp Segmented seal assembly
US4053254A (en) * 1976-03-26 1977-10-11 United Technologies Corporation Turbine case cooling system
DE2745130A1 (de) * 1977-10-07 1979-04-12 Motoren Turbinen Union Einrichtung zur einhaltung bestimmter ausmasse von dichtspalten zwischen laufschaufel- und/oder leitschaufelspitzen und der damit zusammenwirkenden dichtungen fuer gasturbinentriebwerke
US4925365A (en) * 1988-08-18 1990-05-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine stator ring assembly
GB2226365A (en) * 1988-12-22 1990-06-27 Rolls Royce Plc Turbomachine clearance control
EP0937864A2 (fr) * 1998-02-20 1999-08-25 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Configuration des aubes de guidage pour une turbomachine axiale
EP0940562A2 (fr) * 1998-03-03 1999-09-08 Mitsubishi Heavy Industries, Ltd. Turbine à gaz
EP1106785A1 (fr) * 1999-12-07 2001-06-13 Rolls-Royce Deutschland Ltd & Co KG Conduit pour fluide de fuite dans le rotor d'une turbomachine
US20050232752A1 (en) * 2004-04-15 2005-10-20 David Meisels Turbine shroud cooling system
US8011879B2 (en) * 2006-10-06 2011-09-06 Snecma Transition channel between two turbine stages

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2725203B1 (fr) * 2012-10-23 2019-04-03 MTU Aero Engines AG Conduite d'air froid dans une structure de boîtier d'une turbomachine
EP3000990B1 (fr) 2014-09-26 2019-05-29 Rolls-Royce plc Dispositif de retenue de virole d'une turbine
EP3179053A1 (fr) * 2015-12-07 2017-06-14 MTU Aero Engines GmbH Structure de carter de turbomachine avec écran de protection thermique
US10422247B2 (en) 2015-12-07 2019-09-24 MTU Aero Engines AG Housing structure of a turbomachine with heat protection shield

Also Published As

Publication number Publication date
US20140105731A1 (en) 2014-04-17
US9605551B2 (en) 2017-03-28

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