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WO2010112421A1 - Turbomachine axiale à contrôle passif des jeux - Google Patents

Turbomachine axiale à contrôle passif des jeux Download PDF

Info

Publication number
WO2010112421A1
WO2010112421A1 PCT/EP2010/053999 EP2010053999W WO2010112421A1 WO 2010112421 A1 WO2010112421 A1 WO 2010112421A1 EP 2010053999 W EP2010053999 W EP 2010053999W WO 2010112421 A1 WO2010112421 A1 WO 2010112421A1
Authority
WO
WIPO (PCT)
Prior art keywords
annular wall
housing
axial turbomachine
wall part
main flow
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.)
Ceased
Application number
PCT/EP2010/053999
Other languages
German (de)
English (en)
Inventor
Francois Benkler
Björn Burbach
Christoph Buse
Andreas Böttcher
Martin Hartmann
Ekkehard Maldfeld
Torsten Matthias
Oliver 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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of WO2010112421A1 publication Critical patent/WO2010112421A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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 in such a way that the radial gaps are dimensioned sufficiently large for the operating case in which the radial gaps are the smallest, so that there is virtually no contact between the rotor blades and the housing.
  • unnecessarily large radial gaps must be maintained for this operating state, which results in a considerable 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 rotor blades and the housing.
  • the temporal change of the radial gap causes the centrifugal force, in particular of the blades, a transverse contraction of the rotor, a possible game 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, any ovalization of the housing due to assembly-related bias and uneven heating of the Housing.
  • Ovalizations occur in particular in stationary gas turbines, which usually have half-divided guide blade carrier and housing, which are bolted together via flange. These ovalizations are due to half of the structure, as seen over the circumference local mass accumulations in the area of the flange connections exist, which thus thermally slower react and thus have a different stretching behavior than the areas between the mass accumulations.
  • the object of the invention is to provide an axial turbomachine with a high thermal efficiency.
  • the axial turbomachine according to the invention has a rotor blade grid which is formed by rotor blades each having a radially outer, free-standing blade tip extending obliquely to the axis of the axial turbomachine, a housing in which the rotor blade grid is installed and which with its inner side forms the main flow channel of the axial turbocharger.
  • a the rotor blade sheathing and integrated in the inside of the housing ring wall comprising a plurality of annular wall parts, each with a radially inner ring inside, is continued with the (ring wall) on the inside of the housing of the main flow channel, wherein the annular wall parts immediately adjacent to the blade tips are each arranged to form a radial gap between the respective blade tip and the inner ring side, wherein the inner ring side substantially parallel to the blade tips and the annular wall parts in the housing are slidably mounted parallel to the axis of the axial turbomachine and each having a drive means which is supported on the housing and on the respective annular wall part and each having a bimetallic spring and / or a shape memory alloy body, which are thermally conductively coupled to the main flow channel or the housing, and / or a piezoelectric actuator having a thermo-transducer driving this, the thermally conductively coupled to the main flow channel or the housing, so that in dependence of the local temperature, the axial
  • the radial gap as always provided small and seen over the circumference be kept the same size, which is not to be expected with a brushing of the blade tip on the inside of the ring during operation of the axial turbomachine, even with occurring ovalizations of usually two flange bolted together halves of the housing.
  • the radial gaps can be kept constant over time with the embodiment according to the invention. As a result, 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 in a counteracting manner to the drive body, so that the annular wall part always acts on the annular wall part through 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 arranged 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. By means of the pretensioning device, the annular wall part can be brought into this position.
  • the ring inner side preferably tapers, so that the drive device is at an increase in the temperature in the main flow channel, the annular wall part in the main flow direction and at a lowering of the local temperature, the annular wall part is displaced in the direction opposite to the main flow direction.
  • 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 device 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 inner side of the ring, is formed on the annular wall part, and forms a second sliding surface corresponding to the first sliding surface and formed on the housing.
  • the annular wall part is preferably formed by a plurality of ring segments.
  • the bimetal spring and / or the shape memory alloy body and / or the piezo actuator and / or the biasing device are preferably provided.
  • net 2 shows a longitudinal section of the axial turbomachine with the annular wall part, which is arranged in a second position.
  • 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 rotor blade 5 has upstream of a front edge 6 and downstream of a trailing edge 7, wherein the blade 5 is bounded radially by a blade tip 8. In the main flow direction, the blade tip 8 is arranged inclined with respect to the axis of the axial turbomachine 1, the main flow channel widening in the area of the rotor blade 5 in the main flow direction.
  • an annular groove 9 is provided in the inner side 3 of the housing 2, in which a plurality of adjacent along the circumference ring wall parts 10 are used to form an annular wall.
  • Ringswanmaschine 10 has on their radially inner side each have a ring inner side 11, which jointly covers all Laufschaufein 5. Between each blade tip 8 and its opposite inner ring 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, the of the
  • 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 arranged at a distance from the annular groove 9, whereby between see 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 annular wall part 10 form.
  • the bimetallic spring 15 is thermally coupled to the main flow channel 4, the bimetallic spring 15 feels the temperature prevailing in the main flow channel 4 of the bimetallic spring 15 adjacent temperature. Increases this temperature, so also increases the temperature of the bimetallic spring 15. This has the consequence that the bimetallic spring 15 axially expands, whereby the bimetallic spring 15 at 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. Because of the similar Configuration of all annular wall parts 10 is thus achieved that each annular wall part 10 can assume an individual axial position in order to set over the circumference substantially identical gap dimensions for the radial gaps.
  • the local temperature of the housing for positioning the ring wall parts 10 can also be detected by the respective bimetallic spring, the respective shape memory alloy body and / or the respective thermal transducer of the piezoactuator.

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)

Abstract

La présente invention concerne une turbomachine axiale comportant d'une part une grille d'aubes mobiles qui est constituée d'aubes dont la pointe radialement tournée vers l'extérieure se présente en inclinaison par rapport à l'axe de la turbomachine axiale, d'autre part un carter dont al face interne définit la canal d'écoulement principal de la turbomachine axiale, et enfin une paroi annulaire qui enveloppe la grille d'aubes mobiles et qui est intégrée à la face interne du carter. Cette paroi annulaire est constituée d'une pluralité d'éléments de paroi annulaire dont la face annulaire interne, qui se prolonge par la face interne du carter du canal d'écoulement principal, jouxte directement les pointes des aubes tout en ménageant un jeu radial. En l'occurrence, la face annulaire interne est disposée parallèlement à la pointe des aubes, et l'élément de paroi annulaire est monté dans le carter de façon à pouvoir coulisser parallèlement à l'axe de la turbomachine axiale. En outre, cet élément de paroi annulaire comporte un dispositif d'entraînement qui permet à la longue de conserver un jeu sensiblement constant pendant le fonctionnement de la turbomachine axiale. Ce dispositif d'entraînement, constitué d'un ressort bimétallique et/ou d'un corps en alliage à mémoire de forme, et/ou d'un actionneur piézoélectrique sollicité par un transducteur thermique, est couplé en conductivité thermique au canal d'écoulement principal.
PCT/EP2010/053999 2009-03-31 2010-03-26 Turbomachine axiale à contrôle passif des jeux Ceased WO2010112421A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP09004782.0 2009-03-31
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
WO2010112421A1 true WO2010112421A1 (fr) 2010-10-07

Family

ID=40897623

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2010/053999 Ceased WO2010112421A1 (fr) 2009-03-31 2010-03-26 Turbomachine axiale à contrôle passif des jeux

Country Status (2)

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

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2498085C1 (ru) * 2012-04-04 2013-11-10 Николай Борисович Болотин Газотурбинный двигатель
RU2499891C1 (ru) * 2012-04-12 2013-11-27 Николай Борисович Болотин Турбина газотурбинного двигателя
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
DE102013210876A1 (de) 2013-06-11 2014-12-24 MTU Aero Engines AG Verbundbauteil zur thermischen Spaltsteuerung in einer Strömungsmaschine sowie dieses enthaltende Strömungsmaschine
RU2549922C2 (ru) * 2011-05-24 2015-05-10 Альстом Текнолоджи Лтд Турбомашина
EP3006679A1 (fr) * 2014-10-10 2016-04-13 Techspace Aero S.A. Carter externe de turbomachine axiale
CN108374694A (zh) * 2018-04-26 2018-08-07 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
CN113446069A (zh) * 2020-03-26 2021-09-28 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
CN115467855A (zh) * 2022-09-16 2022-12-13 中国联合重型燃气轮机技术有限公司 压气机、燃气轮机和使用方法
US12116896B1 (en) 2023-03-24 2024-10-15 General Electric Company Seal support assembly for a turbine engine
US12188358B2 (en) 2023-05-30 2025-01-07 General Electric Company Seal assembly for a rotary machine
US12215587B2 (en) 2023-03-24 2025-02-04 General Electric Company Seal support assembly for a turbine engine
US12215588B2 (en) 2023-03-27 2025-02-04 General Electric Company Seal assembly for a gas turbine engine
US12241375B2 (en) 2023-03-24 2025-03-04 General Electric Company Seal support assembly for a turbine engine
US12326089B2 (en) 2023-04-24 2025-06-10 General Electric Company Seal assembly for a gas turbine engine
US12372002B2 (en) 2023-03-24 2025-07-29 General Electric Company Seal support assembly for a turbine engine
US12416243B2 (en) 2023-03-24 2025-09-16 General Electric Company Seal support assembly for a turbine engine
US12421861B2 (en) 2023-03-24 2025-09-23 General Electric Company Seal support assembly for a turbine engine
US12486779B2 (en) 2023-03-08 2025-12-02 General Electric Company Seal support assembly for a turbine engine

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GB201021327D0 (en) * 2010-12-16 2011-01-26 Rolls Royce Plc Clearance control arrangement
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

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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
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* Cited by examiner, † Cited by third party
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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
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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 (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2549922C2 (ru) * 2011-05-24 2015-05-10 Альстом Текнолоджи Лтд Турбомашина
US9169741B2 (en) 2011-05-24 2015-10-27 Alstom Technology Ltd Turbomachine clearance control configuration using a shape memory alloy or a bimetal
RU2506433C2 (ru) * 2012-04-04 2014-02-10 Николай Борисович Болотин Газотурбинный двигатель
RU2506434C2 (ru) * 2012-04-04 2014-02-10 Николай Борисович Болотин Газотурбинный двигатель
RU2498085C1 (ru) * 2012-04-04 2013-11-10 Николай Борисович Болотин Газотурбинный двигатель
RU2499891C1 (ru) * 2012-04-12 2013-11-27 Николай Борисович Болотин Турбина газотурбинного двигателя
DE102013210876A1 (de) 2013-06-11 2014-12-24 MTU Aero Engines AG Verbundbauteil zur thermischen Spaltsteuerung in einer Strömungsmaschine sowie dieses enthaltende Strömungsmaschine
DE102013210876B4 (de) * 2013-06-11 2015-02-26 MTU Aero Engines AG Verbundbauteil zur thermischen Spaltsteuerung in einer Strömungsmaschine sowie dieses enthaltende Strömungsmaschine
EP3006679A1 (fr) * 2014-10-10 2016-04-13 Techspace Aero S.A. Carter externe de turbomachine axiale
BE1022471B1 (fr) * 2014-10-10 2016-04-15 Techspace Aero S.A. Carter externe de compresseur de turbomachine axiale avec joint d'etancheite
US10082038B2 (en) 2014-10-10 2018-09-25 Safran Aero Boosters S.A. Axial turbomachine compressor outer casing with seal
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
CN108374694A (zh) * 2018-04-26 2018-08-07 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
CN113446069A (zh) * 2020-03-26 2021-09-28 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
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
CN115467855A (zh) * 2022-09-16 2022-12-13 中国联合重型燃气轮机技术有限公司 压气机、燃气轮机和使用方法
US12486779B2 (en) 2023-03-08 2025-12-02 General Electric Company Seal support assembly for a turbine engine
US12116896B1 (en) 2023-03-24 2024-10-15 General Electric Company Seal support assembly for a turbine engine
US12215587B2 (en) 2023-03-24 2025-02-04 General Electric Company Seal support assembly for a turbine engine
US12241375B2 (en) 2023-03-24 2025-03-04 General Electric Company Seal support assembly for a turbine engine
US12372002B2 (en) 2023-03-24 2025-07-29 General Electric Company Seal support assembly for a turbine engine
US12416243B2 (en) 2023-03-24 2025-09-16 General Electric Company Seal support assembly for a turbine engine
US12421861B2 (en) 2023-03-24 2025-09-23 General Electric Company Seal support assembly for a turbine engine
US12215588B2 (en) 2023-03-27 2025-02-04 General Electric Company Seal assembly for a gas turbine engine
US12326089B2 (en) 2023-04-24 2025-06-10 General Electric Company Seal assembly for a gas turbine engine
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