EP2239423A1 - Turbomachine axiale dotée d'un contrôle passif d'étanchéité en bout d'aube - Google Patents

Turbomachine axiale dotée d'un contrôle passif d'étanchéité en bout d'aube Download PDF

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Publication number
EP2239423A1
EP2239423A1 EP09004782A EP09004782A EP2239423A1 EP 2239423 A1 EP2239423 A1 EP 2239423A1 EP 09004782 A EP09004782 A EP 09004782A EP 09004782 A EP09004782 A EP 09004782A EP 2239423 A1 EP2239423 A1 EP 2239423A1
Authority
EP
European Patent Office
Prior art keywords
wall part
annular wall
axial turbomachine
main flow
housing
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.)
Withdrawn
Application number
EP09004782A
Other languages
German (de)
English (en)
Inventor
Francois Dr. Benkler
Björn Burbach
Christoph Buse
Andreas Dr. Böttcher
Martin Hartmann
Ekkehard Dr. Maldfeld
Torsten Matthias
Oliver Dr. Schneider
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP09004782A priority Critical patent/EP2239423A1/fr
Priority to PCT/EP2010/053999 priority patent/WO2010112421A1/fr
Publication of EP2239423A1 publication Critical patent/EP2239423A1/fr
Withdrawn legal-status Critical Current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
    • F01D11/08—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
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F05D2300/505—Shape memory behaviour

Definitions

  • the invention relates to an axial turbomachine with a passive gap control.
  • radial gaps between blades and the housing lead to significant losses in thermal efficiency.
  • the axial turbomachine is, for example, a gas turbine.
  • the gas turbine When starting and stopping the gas turbine, the radial gaps change over time.
  • the radial gaps change when switching from part load operation to full load operation of the gas turbine.
  • the gas turbine is designed so that the radial gap for the operating case in which the radial gaps are the smallest set, are sufficiently large, so that there is virtually no contact between the blades and the housing. This has the consequence that in continuous operation of the gas turbine unnecessarily large radial gaps must be kept for this operating condition, which is associated with a significant loss of efficiency.
  • the temporal change of the radial gaps is the result of different thermal inertia behavior of the individual components of the gas turbine, in particular the rotor, the blades and the housing.
  • the temporal change of the radial gap causes the centrifugal force expansion, in particular of the blades, a transverse contraction of the rotor, a possible play in the thrust bearing of the rotor, in particular in connection with the reversal of axial thrust under appropriate operating conditions of the gas turbine, a possibly occurring ovalization of the housing due to montage charitableer Preload and uneven heating of the housing.
  • the object of the invention is to provide an axial turbomachine with a high thermal efficiency.
  • the axial turbomachine comprises a blade grid, which is formed by blades, each with a radially outer, free-standing and inclined to the axis of the axial turbomachine blade tip, a housing in which the blade grid is installed and defines the inside of the main flow channel of the axial turbomachine, and a ring wall member enveloping the blade lattice and integrated in the inside of the housing with a radially inner ring inner side with which the main flow channel continues on the inside of the housing and the ring member immediately adjacent to the blade tips forming a radial gap between the blade tip envelope and the ring inner side is arranged, wherein the inner ring side is substantially parallel to the blade tip and the annular wall part is slidably mounted in the housing parallel to the axis of the axial turbomachine sow ie has a drive device which is supported on the housing and on the annular wall part and a bimetallic spring and / or a shape memory alloy body which are thermally conductively coupled to the main
  • the annular wall part on the inside of the ring is advantageously tracked radially radially of the blade tip as a function of the temperature prevailing in the main flow channel.
  • the radial gap may be small be, since with a rubbing of the blade tip on the inside of the ring during operation of the axial turbomachine is not expected.
  • the thermal efficiency of the axial turbomachine is high.
  • the drive device preferably has a pretensioning device, which is supported on the housing and acts on the annular wall part counteracting the drive body, so that the annular wall part is always pressed against the drive body by the pretensioning device.
  • the biasing means is a coil spring.
  • the annular wall part of the drive part can always be tracked by the biasing device.
  • the drive part is preferably set up such that in the case of failure of the drive part, the drive part assumes such a position in which the annular wall part is brought into a position in which the radial gap is dimensioned sufficiently large. With the help of the biasing device, the ring wall part can be brought into this position.
  • the ring inner side preferably tapers so that the annular wall part is displaced in the main flow direction by the drive device with an increase in the temperature in the main flow channel and the ring wall part is displaced counter to the main flow direction when the temperature in the main flow channel is lowered.
  • the bimetallic spring and / or the shape memory alloy body and / or piezo actuator acts on the annular wall part upstream.
  • the prestressing device preferably engages downstream of the annular wall part.
  • annular groove is preferably provided, in which the annular wall part is housed.
  • the bimetallic spring and / or the shape memory alloy body and / or the piezoelectric actuator and / or the biasing means are preferably arranged.
  • the annular wall part is axially guided on the housing with an axial guide.
  • the axial guide is preferably formed by a first axially parallel sliding surface, which faces away from the ring inner side is formed on the annular wall part, and one of the first sliding surface corresponding formed on the housing, the second sliding surface.
  • the annular wall part is preferably formed by a plurality of ring segments.
  • the bimetallic spring and / or the shape memory alloy body and / or the piezoelectric actuator and / or the biasing device are preferably provided.
  • an axial turbomachine 1 has a housing 2 which has an inner side 3. With the inner side 3, a main flow channel 4 is defined, in which a blade ring is arranged, which is formed by a plurality of circumferentially arranged blades 5. Each blade 5 has upstream of a leading edge 6 and downstream of a trailing edge 7, wherein the blade 5 is radially bounded by a blade tip 8. In the main flow direction, the blade tip 8 is arranged inclined to the axis of the axial turbomachine 1, wherein the main flow channel widens in the region of the blade 5 in the main flow direction.
  • annular groove 9 is provided in the inner side 3 of the housing 2, in which an annular wall part 10 is inserted.
  • the annular wall part 10 has on its radially inner side a ring inner side 11, with which the annular wall part 10, the blades 5 sheathed. Between the envelope of the blade tips 8 and the ring inner side 11, a radial gap 12 is provided.
  • the ring inner side 11 is shaped such that from it the contour of the main flow channel, which is formed by the inside 3 of the housing 2, is continued.
  • the annular wall part 10 is delimited upstream of an upstream side 13 and bounded downstream of a downstream side 14.
  • the upstream side 13 and the downstream side 14 each lie in a plane which is perpendicular to the axis of the axial turbomachine 1.
  • the upstream side 13 and the downstream side 14 are each spaced from the annular groove 9, wherein between the upstream side 13 and the annular groove 9, a bimetallic spring 15 and between the downstream side 14 and the annular groove 9, a coil spring 16 are installed.
  • the bimetallic spring 15 is supported on both the upstream side 13 and the housing 2, and the coil spring 16 is supported on both the downstream side 14 and the housing 2.
  • the bimetallic spring 15 is thermally conductively connected to the main flow channel 4.
  • the annular wall part 10 has, on a radially outer side facing away from the ring inner side 11, a sliding surface running parallel to the axis of the axial turbomachine 1, which bears against a sliding surface formed on the base of the annular groove 9, so that the two sliding surfaces form an axial guide 17 of the Ring wall part 10 form.
  • axially the annular wall portion 10 in the annular groove 9 from a first position the in FIG. 1 is shown in a second position in FIG. 2 is shown and moved back.
  • Characterized in that the bimetallic spring 15 is thermally coupled to the main flow channel 4, the bimetallic spring 15 feels in the main flow channel 4 of the bimetallic spring 15 adjacent prevailing temperature. As the temperature increases, the temperature of the bimetal spring 15 also increases.
  • the bimetallic spring 15 axially expands, whereby the bimetallic spring 15 supported on the annular groove 9 on the upstream side 13 on the annular wall part 10 thrusts in the axial direction Direction of the main flow direction applies.
  • the annular wall part 10 is displaced from the first position to the second position by the bimetal spring 15, as a result of which the radial gap 12 is reduced.
  • the radial gap 12 can be adjusted as a function of the temperature in the main flow channel 4 so that the radial gap 12 during operation of the axial turbomachine 1 is substantially constant over time. Due to the provision of the coil spring 16 on the downstream side, this exerts a bias on the annular wall part 10 counter to the main flow direction, so that the annular wall part 10 is always pressed against the bimetallic spring 15.

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)
EP09004782A 2009-03-31 2009-03-31 Turbomachine axiale dotée d'un contrôle passif d'étanchéité en bout d'aube Withdrawn EP2239423A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP09004782A EP2239423A1 (fr) 2009-03-31 2009-03-31 Turbomachine axiale dotée d'un contrôle passif d'étanchéité en bout d'aube
PCT/EP2010/053999 WO2010112421A1 (fr) 2009-03-31 2010-03-26 Turbomachine axiale à contrôle passif des jeux

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09004782A EP2239423A1 (fr) 2009-03-31 2009-03-31 Turbomachine axiale dotée d'un contrôle passif d'étanchéité en bout d'aube

Publications (1)

Publication Number Publication Date
EP2239423A1 true EP2239423A1 (fr) 2010-10-13

Family

ID=40897623

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09004782A Withdrawn EP2239423A1 (fr) 2009-03-31 2009-03-31 Turbomachine axiale dotée d'un contrôle passif d'étanchéité en bout d'aube

Country Status (2)

Country Link
EP (1) EP2239423A1 (fr)
WO (1) WO2010112421A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2549065A1 (fr) * 2011-07-18 2013-01-23 General Electric Company Système et procédé d'exploitation d'une turbine
EP2466075A3 (fr) * 2010-12-16 2013-06-26 Rolls-Royce plc Dispositif de réglage du jeu pour turbine à gaz
EP2851515A1 (fr) * 2013-09-24 2015-03-25 Siemens Aktiengesellschaft Agencement de fixation d'aubes de turbine
US12049828B2 (en) 2022-07-12 2024-07-30 General Electric Company Active clearance control of fan blade tip closure using a variable sleeve system

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH704995A1 (de) 2011-05-24 2012-11-30 Alstom Technology Ltd Turbomaschine.
RU2498085C1 (ru) * 2012-04-04 2013-11-10 Николай Борисович Болотин Газотурбинный двигатель
RU2506434C2 (ru) * 2012-04-04 2014-02-10 Николай Борисович Болотин Газотурбинный двигатель
RU2506433C2 (ru) * 2012-04-04 2014-02-10 Николай Борисович Болотин Газотурбинный двигатель
RU2499891C1 (ru) * 2012-04-12 2013-11-27 Николай Борисович Болотин Турбина газотурбинного двигателя
DE102013210876B4 (de) 2013-06-11 2015-02-26 MTU Aero Engines AG Verbundbauteil zur thermischen Spaltsteuerung in einer Strömungsmaschine sowie dieses enthaltende Strömungsmaschine
BE1022471B1 (fr) 2014-10-10 2016-04-15 Techspace Aero S.A. Carter externe de compresseur de turbomachine axiale avec joint d'etancheite
CN108374694B (zh) * 2018-04-26 2023-11-17 贵州智慧能源科技有限公司 一种压气机间隙主动控制装置及方法
RU192393U1 (ru) * 2019-06-20 2019-09-16 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Устройство для регулирования радиального зазора
RU2716648C1 (ru) * 2019-07-16 2020-03-13 ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ БЮДЖЕТНОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Брянский государственный технический университет" Охлаждаемая лопатка газовой турбины
CN113446069B (zh) * 2020-03-26 2023-06-20 中国航发商用航空发动机有限责任公司 航空发动机叶尖间隙被动控制装置和航空发动机

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure
US4023919A (en) * 1974-12-19 1977-05-17 General Electric Company Thermal actuated valve for clearance control
DE2728190A1 (de) * 1976-07-05 1978-01-19 Stal Laval Turbin Ab Gasturbine
JPS57195803A (en) * 1981-05-27 1982-12-01 Hitachi Ltd Adjusting device of tip clearance in turbo fluidic machine
JPS58206807A (ja) * 1982-05-28 1983-12-02 Hitachi Ltd 軸流タ−ビンの動翼先端すき間制御装置
JPS5915605A (ja) * 1982-07-15 1984-01-26 Toshiba Corp ガスタ−ビン
JPS60111004A (ja) * 1983-11-21 1985-06-17 Hitachi Ltd 軸流形流体機械のケ−シング
JPS60187302U (ja) * 1984-05-22 1985-12-12 株式会社東芝 蒸気タ−ビン
EP0924388A2 (fr) * 1997-12-19 1999-06-23 BMW Rolls-Royce GmbH Système pour maintenir le jeu des extrémités des aubes d'une turbine à gaz à constant
EP1686243A2 (fr) * 2005-01-26 2006-08-02 General Electric Company Stator de turbine avec des alliages à mémoire de forme et pilotage de jeu des aubes
DE102005048982A1 (de) * 2005-10-13 2007-04-19 Mtu Aero Engines Gmbh Vorrichtung und Verfahren zum axialen Verschieben eines Turbinenrotors
US20080131270A1 (en) * 2006-12-04 2008-06-05 Siemens Power Generation, Inc. Blade clearance system for a turbine engine

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure
US4023919A (en) * 1974-12-19 1977-05-17 General Electric Company Thermal actuated valve for clearance control
DE2728190A1 (de) * 1976-07-05 1978-01-19 Stal Laval Turbin Ab Gasturbine
JPS57195803A (en) * 1981-05-27 1982-12-01 Hitachi Ltd Adjusting device of tip clearance in turbo fluidic machine
JPS58206807A (ja) * 1982-05-28 1983-12-02 Hitachi Ltd 軸流タ−ビンの動翼先端すき間制御装置
JPS5915605A (ja) * 1982-07-15 1984-01-26 Toshiba Corp ガスタ−ビン
JPS60111004A (ja) * 1983-11-21 1985-06-17 Hitachi Ltd 軸流形流体機械のケ−シング
JPS60187302U (ja) * 1984-05-22 1985-12-12 株式会社東芝 蒸気タ−ビン
EP0924388A2 (fr) * 1997-12-19 1999-06-23 BMW Rolls-Royce GmbH Système pour maintenir le jeu des extrémités des aubes d'une turbine à gaz à constant
EP1686243A2 (fr) * 2005-01-26 2006-08-02 General Electric Company Stator de turbine avec des alliages à mémoire de forme et pilotage de jeu des aubes
DE102005048982A1 (de) * 2005-10-13 2007-04-19 Mtu Aero Engines Gmbh Vorrichtung und Verfahren zum axialen Verschieben eines Turbinenrotors
US20080131270A1 (en) * 2006-12-04 2008-06-05 Siemens Power Generation, Inc. Blade clearance system for a turbine engine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2466075A3 (fr) * 2010-12-16 2013-06-26 Rolls-Royce plc Dispositif de réglage du jeu pour turbine à gaz
US8894358B2 (en) 2010-12-16 2014-11-25 Rolls-Royce Plc Clearance control arrangement
EP2549065A1 (fr) * 2011-07-18 2013-01-23 General Electric Company Système et procédé d'exploitation d'une turbine
US8939709B2 (en) 2011-07-18 2015-01-27 General Electric Company Clearance control for a turbine
EP2851515A1 (fr) * 2013-09-24 2015-03-25 Siemens Aktiengesellschaft Agencement de fixation d'aubes de turbine
US12049828B2 (en) 2022-07-12 2024-07-30 General Electric Company Active clearance control of fan blade tip closure using a variable sleeve system

Also Published As

Publication number Publication date
WO2010112421A1 (fr) 2010-10-07

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