EP0713977A2 - Procédé et dispositif pour régler le jeu radial des pales des compresseurs axiaux - Google Patents

Procédé et dispositif pour régler le jeu radial des pales des compresseurs axiaux Download PDF

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Publication number
EP0713977A2
EP0713977A2 EP95810704A EP95810704A EP0713977A2 EP 0713977 A2 EP0713977 A2 EP 0713977A2 EP 95810704 A EP95810704 A EP 95810704A EP 95810704 A EP95810704 A EP 95810704A EP 0713977 A2 EP0713977 A2 EP 0713977A2
Authority
EP
European Patent Office
Prior art keywords
guide
blades
blade
blade carrier
suspensions
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.)
Granted
Application number
EP95810704A
Other languages
German (de)
English (en)
Other versions
EP0713977A3 (fr
EP0713977B1 (fr
Inventor
Robert Marmilic
François Dr. Meynard
Roger Suter
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.)
ABB AG Germany
Original Assignee
ABB Management 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 ABB Management AG filed Critical ABB Management AG
Publication of EP0713977A2 publication Critical patent/EP0713977A2/fr
Publication of EP0713977A3 publication Critical patent/EP0713977A3/fr
Application granted granted Critical
Publication of EP0713977B1 publication Critical patent/EP0713977B1/fr
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
    • 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
    • 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5853—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps heat insulation or conduction

Definitions

  • the invention relates to a device for influencing the radial clearance of the blading in compressors of gas turbines through which there is a high flow of axial flow.
  • the radial play is caused on the one hand by inaccuracies in manufacture and assembly, but on the other hand above all by the different thermal behavior of the rotor and the blade carrier.
  • the rotor Due to the strength requirements, the rotor is usually more solid than the blade carrier. Since both the heat transfer conditions and mostly the material for both parts are similar, the rotor is thermally much slower. In addition, not only are the thermal expansions of the rotor and blade carrier different in the operating state, but also their chronological progression, especially when starting and stopping the machine. In cooperation with the centrifugal force, this results in a minimal radial play when starting in the warm state shortly after stopping and a maximum radial play when starting in the cold state.
  • cover rings are used at the same time for the storage and holding of the guide vane rings arranged between them, then the gap between the inner guide vane end (possibly cover band) which also causes loss of performance can also be and also minimize the rotor. Since the cover rings should consist of a material with the lowest possible coefficient of thermal expansion, for example an iron-nickel alloy, they are relatively expensive. Another disadvantage of this prior art is the complicated construction that results from the fastening of the centering wedges and their centering.
  • a turbomachine housing is known with an outer housing wall and an inner housing wall divided into sectors in the circumferential direction, both of which are connected to one another via releasable fasteners, in which the sectors of the inner housing wall are formed by holding rails, one at their ends
  • the sectors of the inner housing wall are formed by holding rails, one at their ends
  • a disadvantage of this prior art is the division of the blade carrier into an outer and an inner housing wall, whereby only thin guide blade feet can be accommodated due to the thin inner housing wall and the forces that occur are transmitted to the outer housing wall via the base and the inner housing wall.
  • the invention tries to avoid all these disadvantages. It is the object of the invention to provide a device for influencing the radial clearance of the blading in an axially flow-loaded compressor, with which it is possible in a simple manner to keep the radial gap between the moving blades and the blade carrier small and at an approximately constant level during different operating conditions of the machine.
  • the blade carrier has long and narrow suspensions for the guide blades, whereby at least one cavity is arranged in the guide vane feet, and that in the scooped-in state, there is a cavity in each case in the circumferential direction between the guide vane root, the two suspensions for a guide vane and the blade carrier, and that in the circumferential direction there is another cavity between the blade carrier and the suspensions for there are two successive guide vanes, which is delimited by several segments distributed over the circumference and connected to the guide vane feet, and that the cavities are filled with insulating material.
  • the segments are designed as curved plates or if they have a curved plate-shaped base on which at least one hook in each case extends in the direction of the blade carrier on the sides of the suspensions.
  • the hooks prevent a possible unwanted arching of the segments due to increased temperatures.
  • the segments are connected to the guide vane feet via springs. Press the springs Guide vanes and segments in the operating position and at the same time have a sealing function.
  • the height of the suspension is at least half the blade height and the width of the suspension corresponds to a maximum of one third of the width of the blade root of the guide blade. In this case, the heat transfer from the compressor duct to the blade carrier is reduced particularly strongly.
  • heating means for example an electric heater
  • passive radial clearance control an additional active radial clearance control can be achieved.
  • the compressor essentially consists of the rotor 1, which is equipped with moving blades 2, and the blade carrier 3, which carries the guide blades 4.
  • the blade carrier is suspended in an outer housing 5 of the compressor, which is connected, for example, via flange connections to a turbine housing, not shown here.
  • FIG. 2 shows an enlarged section of FIG. 1 in the area of the blade carrier 3 and the blades 2, 4.
  • the blade carrier 3 has a special configuration in such a way that it has long and narrow suspensions 7 with circumferential grooves, into which the guide blades 4 are vane.
  • the suspensions 7 are preferably at least as high as half the blade height h, their width is at most one third of the width b of the blade base 8 of the guide blade 4. They are poorly heat-conducting.
  • Another cavity 11 is arranged in the blade carrier 3 between the suspensions 7 of two successive guide blades 4.
  • This cavity 11 is delimited by a plurality of segments 12 distributed over the circumference and connected to the guide vane feet 8, which segments are designed as curved plates in this exemplary embodiment.
  • the segments 12 delimit the compressor flow channel 13 on their underside in the area of the blades 2. They are connected to the guide blade feet 8 by means of springs 14, which partially have a sealing function and can be, for example, C-rings, so that only contact between the segments 12 and the guide vane feet 8.
  • the springs 14 press the guide vanes 2 and the segments 12 into the operating position.
  • the cavities 9, 10, 11 are filled with solid, immovable insulation material 15, so that undesired effects, such as leakage and radiation, are prevented.
  • a means for supplying temperature 17, for example an electrical, preferably inductive heater, can be arranged within the blade carrier 3, which means is switched on when required, specifically when the machine is warm started.
  • the heat supplied to the stator increases the minimal radial play at the "pinch point" since the radius of the stator remains constant.
  • Fig. 3 makes this clear. This shows the radial play as a function of time or different operating conditions in the compressor.
  • the solid lines represent the conditions according to the prior art, the dashed line shows the dependency for the stator according to the solution according to the invention.
  • the radial play between the stator and the rotor blades is reduced, since the stator is thermally slower due to the obstruction of heat transfer from the compressor duct, which is achieved by the invention. This means that even after the machine is switched off, the stator cools down more slowly, but still faster than the rotor. If the radius of the stator is now kept constant during the warm start by switching on the already mentioned electrical heater, preferably an inductive heater, and the associated supply of heat, then the radial play that is present shortly after switching off during the warm start is no longer so small and there is no damage to the blades to fear.
  • FIG. 4 A second exemplary embodiment, which differs predominantly in the segment shape used from the exemplary embodiment described above, is shown in FIG. 4.
  • the segments 12 here have a curved plate-shaped base, on each of which a hook 16 extends in the direction of the blade carrier 3 on the sides of the suspensions 7.
  • the segment 12 thus consists of a unit of the base plate and the hook 16.
  • the hooks 16 increase the number of heat transfers compared to the above embodiment, but prevent the segments 12 from buckling, which would result in greater radial play.
  • a known solid filler which fills the cavities 9, 10 and 11, is used as the insulation material 15.
  • FIG. 5 and 6 finally show an exemplary embodiment in which segments 12 with hooks 16, which form a unit, are used analogously to the second exemplary embodiment.
  • a closed cavity for the quiescent air is created by means of additional metal sheets 18, each of which is inserted into two circumferential grooves of the segments 12 (in the area of the hooks 16) and bent at almost a right angle at the end of each segment, which encapsulates each segment 12 and prevents air circulation (see Fig. 5). Without the installation of the sheets 18, an undesired heat transfer due to free convection could take place.
  • the blade carrier 3 is axially divided by a parting plane.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP95810704A 1994-11-26 1995-11-09 Dispositif pour régler le jeu radial des pales des compresseurs axiaux Expired - Lifetime EP0713977B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4442157A DE4442157A1 (de) 1994-11-26 1994-11-26 Verfahren und Vorrichtung zur Beeinflussung des Radialspieles der Beschaufelung in axialdurchströmten Verdichtern
DE4442157 1994-11-26

Publications (3)

Publication Number Publication Date
EP0713977A2 true EP0713977A2 (fr) 1996-05-29
EP0713977A3 EP0713977A3 (fr) 1998-01-07
EP0713977B1 EP0713977B1 (fr) 2002-07-10

Family

ID=6534246

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810704A Expired - Lifetime EP0713977B1 (fr) 1994-11-26 1995-11-09 Dispositif pour régler le jeu radial des pales des compresseurs axiaux

Country Status (5)

Country Link
US (1) US5630702A (fr)
EP (1) EP0713977B1 (fr)
JP (1) JPH08210106A (fr)
CN (1) CN1133946A (fr)
DE (2) DE4442157A1 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2761119A1 (fr) * 1997-03-20 1998-09-25 Snecma Stator de compresseur de turbomachine
FR2933131A1 (fr) * 2008-06-25 2010-01-01 Snecma Support pour fixer un anneau entourant les aubes mobiles d'une turbine
CH704001A1 (de) * 2010-10-26 2012-04-30 Alstom Technology Ltd Leitschaufelanordnung einer Strömungsmaschine, insbesondere eines Axialkompressors.
CH704000A1 (de) * 2010-10-26 2012-04-30 Alstom Technology Ltd Leitschaufelanordnung einer Strömungsmaschine, insbesondere eines Axialkompressors.
RU2500894C1 (ru) * 2012-04-27 2013-12-10 Николай Борисович Болотин Турбина газотурбинного двигателя
CN103867493A (zh) * 2014-02-26 2014-06-18 江苏永一泵业有限公司 一种高温泵的冷却装置
EP2754860A1 (fr) * 2013-01-10 2014-07-16 Alstom Technology Ltd Turbomachine avec pilotage électrique actif de jeu et procédé associé
ITFI20130118A1 (it) * 2013-05-21 2014-11-22 Nuovo Pignone Srl "compressor with a thermal shield and methods of operation"
EP2896796A1 (fr) * 2014-01-20 2015-07-22 Techspace Aero S.A. Stator de turbomachine axiale et turbomachine associée
CN111536074B (zh) * 2020-05-15 2021-03-16 杭州余杭特种风机有限公司 一种高效散热风机叶轮
US11225883B2 (en) 2017-01-23 2022-01-18 MTU Aero Engines AG Turbomachine housing element

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US7794729B2 (en) * 1994-11-08 2010-09-14 The Trustees Of The University Of Pennsylvania Methods and compositions for immunotherapy of cancer
DE19615549B8 (de) * 1996-04-19 2005-07-07 Alstom Vorrichtung zum thermischen Schutz eines Rotors eines Hochdruckverdichters
US6155780A (en) * 1999-08-13 2000-12-05 Capstone Turbine Corporation Ceramic radial flow turbine heat shield with turbine tip seal
RU2272151C2 (ru) * 2000-12-28 2006-03-20 Альстом Текнолоджи Лтд Лопатка статора осевой турбины
US6896483B2 (en) * 2001-07-02 2005-05-24 Allison Advanced Development Company Blade track assembly
FR2829176B1 (fr) * 2001-08-30 2005-06-24 Snecma Moteurs Carter de stator de turbomachine
DE10356586A1 (de) * 2003-12-04 2005-07-07 Alstom Technology Ltd Verdichterrotor
DE102005013798A1 (de) * 2005-03-24 2006-09-28 Alstom Technology Ltd. Wärmestausegment zum Abdichten eines Strömungskanals einer Strömungsrotationsmaschine
DE502005010381D1 (de) * 2005-04-28 2010-11-25 Siemens Ag Verfahren und Vorrichtung zur Einstellung eines Radialspaltes eines axial durchströmten Verdichters einer Strömungsmaschine
FR2887939B1 (fr) * 2005-06-29 2016-09-30 Soc Nat D'etude Et De Construction De Moteurs D'aviation Snecma Compresseur multi-etages de turbomachine
EP1744015A1 (fr) 2005-07-14 2007-01-17 Siemens Aktiengesellschaft Montage d'un segment d'étanchéité dans le pied d'une aube statorique
FR2890685B1 (fr) * 2005-09-14 2007-12-14 Snecma Pilotage de jeu au sommet d'aubes de rotor de turbine haute pression dans une turbomachine
US8292571B2 (en) * 2007-10-12 2012-10-23 General Electric Company Apparatus and method for clearance control of turbine blade tip
FR2943717B1 (fr) * 2009-03-27 2016-02-19 Snecma Stator de compresseur ou turbine de turbomachine permettant un controle du jeu en sommet d'aubes d'un rotor en regard
DE102011005122A1 (de) * 2011-03-04 2012-09-06 Siemens Aktiengesellschaft Dampfturbine insbesondere für solarthermische Kraftwerke
DE102011005126A1 (de) * 2011-03-04 2012-09-06 Siemens Aktiengesellschaft Dampfturbine mit induktiver Beheizung
US9057282B2 (en) * 2011-11-22 2015-06-16 General Electric Company Systems and methods for adjusting clearances in turbines
US20130251500A1 (en) * 2012-03-23 2013-09-26 Kin-Leung Cheung Gas turbine engine case with heating layer and method
US20130305728A1 (en) * 2012-05-15 2013-11-21 General Electric Company Systems and Methods for Minimizing Coking in Gas Turbine Engines
EP2762681B1 (fr) * 2013-02-04 2017-09-06 Safran Aero Boosters SA Tambour de rotor de turbomachine axiale et turbomachine associée
RU2556297C2 (ru) * 2013-10-23 2015-07-10 Федеральное государственное бюджетное учреждение науки Институт проблем управления сложными системами Российской академии наук (ИПУСС РАН) Способ измерения радиальных зазоров и осевых смещений торцов рабочих лопаток турбины
CN103696981A (zh) * 2013-12-25 2014-04-02 绍兴协亨机械设备有限公司 一种汽车的喷泵装置
EP2930308B1 (fr) * 2014-04-11 2021-07-28 Safran Aero Boosters SA Carter à facettes de turbomachine axiale
CN105466689B (zh) * 2014-09-09 2019-11-08 中国航空工业集团公司沈阳发动机设计研究所 一种压气机叶片表面动态压力测量装置的安装方法
RU2651622C1 (ru) * 2016-12-09 2018-04-23 Федеральное государственное бюджетное учреждение науки Институт проблем управления сложными системами Российской академии наук (ИПУСС РАН) Способ измерения радиальных зазоров между торцами лопаток рабочего колеса и статорной оболочкой турбомашины
US10815824B2 (en) * 2017-04-04 2020-10-27 General Electric Method and system for rotor overspeed protection
WO2019099009A1 (fr) * 2017-11-16 2019-05-23 Siemens Aktiengesellschaft Système de commande de jeu de turbine à gaz comprenant un circuit de chauffage électrique intégré
CN111542682B (zh) * 2018-01-05 2022-08-23 西门子能源全球两合公司 燃气涡轮感应系统、对应感应加热器以及用于感应加热部件的方法
CN109458232B (zh) * 2018-10-16 2021-02-12 中广核核电运营有限公司 一种测量汽缸隔板洼窝及其叶顶阻汽片同心的方法
CN115013079A (zh) * 2022-07-08 2022-09-06 泰安凯顺机电工程有限公司 一种使用寿命高的汽轮机

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GB716391A (en) * 1952-02-11 1954-10-06 English Electric Co Ltd Improvements in and relating to gas turbines
FR2482662A1 (fr) * 1980-05-16 1981-11-20 Mtu Muenchen Gmbh Carter exterieur pour compresseur axial ou turbine axiale d'une machine fluidique
DE3305170A1 (de) * 1982-02-19 1983-08-25 General Electric Co., Schenectady, N.Y. Verdichtergehaeuse
CH639171A5 (en) * 1979-07-20 1983-10-31 Sulzer Ag Stator for at least one part of a multi-stage axial flow turbo-engine
FR2557634A2 (fr) * 1983-02-03 1985-07-05 Snecma Dispositif d'etancheite d'aubages mobiles de turbomachine
FR2589520A1 (fr) * 1985-10-30 1987-05-07 Snecma Carter de turbomachine muni d'un accumulateur de chaleur

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CH421142A (de) * 1965-01-12 1966-09-30 Escher Wyss Ag Gehäuse für eine Gas- oder Dampfturbine
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FR2607198B1 (fr) * 1986-11-26 1990-05-04 Snecma Carter de compresseur adapte pour le pilotage actif de ses dilatations et son procede de fabrication
FR2685936A1 (fr) * 1992-01-08 1993-07-09 Snecma Dispositif de controle des jeux d'un carter de compresseur de turbomachine.
DE4331060C1 (de) * 1993-09-13 1994-06-30 Gruenzweig & Hartmann Montage Wärmedämmanordnung

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Publication number Priority date Publication date Assignee Title
GB716391A (en) * 1952-02-11 1954-10-06 English Electric Co Ltd Improvements in and relating to gas turbines
CH639171A5 (en) * 1979-07-20 1983-10-31 Sulzer Ag Stator for at least one part of a multi-stage axial flow turbo-engine
FR2482662A1 (fr) * 1980-05-16 1981-11-20 Mtu Muenchen Gmbh Carter exterieur pour compresseur axial ou turbine axiale d'une machine fluidique
DE3305170A1 (de) * 1982-02-19 1983-08-25 General Electric Co., Schenectady, N.Y. Verdichtergehaeuse
FR2557634A2 (fr) * 1983-02-03 1985-07-05 Snecma Dispositif d'etancheite d'aubages mobiles de turbomachine
FR2589520A1 (fr) * 1985-10-30 1987-05-07 Snecma Carter de turbomachine muni d'un accumulateur de chaleur

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2761119A1 (fr) * 1997-03-20 1998-09-25 Snecma Stator de compresseur de turbomachine
FR2933131A1 (fr) * 2008-06-25 2010-01-01 Snecma Support pour fixer un anneau entourant les aubes mobiles d'une turbine
CH704001A1 (de) * 2010-10-26 2012-04-30 Alstom Technology Ltd Leitschaufelanordnung einer Strömungsmaschine, insbesondere eines Axialkompressors.
CH704000A1 (de) * 2010-10-26 2012-04-30 Alstom Technology Ltd Leitschaufelanordnung einer Strömungsmaschine, insbesondere eines Axialkompressors.
RU2500894C1 (ru) * 2012-04-27 2013-12-10 Николай Борисович Болотин Турбина газотурбинного двигателя
EP2754860A1 (fr) * 2013-01-10 2014-07-16 Alstom Technology Ltd Turbomachine avec pilotage électrique actif de jeu et procédé associé
EP2754859A1 (fr) * 2013-01-10 2014-07-16 Alstom Technology Ltd Turbomachine avec pilotage électrique actif de jeu et procédé associé
ITFI20130118A1 (it) * 2013-05-21 2014-11-22 Nuovo Pignone Srl "compressor with a thermal shield and methods of operation"
WO2014187786A3 (fr) * 2013-05-21 2015-04-16 Nuovo Pignone Srl Compresseur à bouclier thermique et procédés de fonctionnement
CN105705799A (zh) * 2013-05-21 2016-06-22 诺沃皮尼奥内股份有限公司 具有热屏蔽的压缩机及其操作方法
US10711641B2 (en) 2013-05-21 2020-07-14 Nuovo Pignone Srl Compressor with a thermal shield and methods of operation
EP2896796A1 (fr) * 2014-01-20 2015-07-22 Techspace Aero S.A. Stator de turbomachine axiale et turbomachine associée
CN103867493A (zh) * 2014-02-26 2014-06-18 江苏永一泵业有限公司 一种高温泵的冷却装置
US11225883B2 (en) 2017-01-23 2022-01-18 MTU Aero Engines AG Turbomachine housing element
CN111536074B (zh) * 2020-05-15 2021-03-16 杭州余杭特种风机有限公司 一种高效散热风机叶轮

Also Published As

Publication number Publication date
EP0713977A3 (fr) 1998-01-07
JPH08210106A (ja) 1996-08-20
EP0713977B1 (fr) 2002-07-10
DE4442157A1 (de) 1996-05-30
DE59510267D1 (de) 2002-08-14
US5630702A (en) 1997-05-20
CN1133946A (zh) 1996-10-23

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