EP1249577A1 - Gasturbine mit axial verschiebbaren Gehäuseteilen - Google Patents
Gasturbine mit axial verschiebbaren Gehäuseteilen Download PDFInfo
- Publication number
- EP1249577A1 EP1249577A1 EP01109198A EP01109198A EP1249577A1 EP 1249577 A1 EP1249577 A1 EP 1249577A1 EP 01109198 A EP01109198 A EP 01109198A EP 01109198 A EP01109198 A EP 01109198A EP 1249577 A1 EP1249577 A1 EP 1249577A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- turbine according
- guide part
- rib
- guide
- 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
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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
- F01D11/20—Actively adjusting tip-clearance
- F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
Definitions
- the invention relates to a gas turbine with a guide and with a blade ring in a gas channel and with a Housing and axially secured against rotation against each other sliding funnel-shaped guide parts as a carrier of rings forming an outer jacket of the gas channel.
- Gas turbines are often not only in their starting phase, but also subject to changing loads even in continuous operation. This has especially with regard to that of individual components assume a transient temperature Operation as a result. To avoid damage to the turbine the individual components are therefore usually clamped in such a way that they are unhindered thermally induced dimensional changes can execute.
- Turbine losses due to cross currents over their blade tips to minimize as much as possible are the smallest possible radial gap between the blade tips and these opposite guide surfaces. Because both the blades and their rotor as well as guide blades and their carriers as well as an all-connecting housing expand differently in time with each load change and / or shrink, there is an optimal radial Gap over the blade tips only for very few of any number of stationary operating states. The These gas turbines are therefore often operated with a not optimized gap width and therefore with a not optimized efficiency.
- the invention is based on the object of a gas turbine system to develop further in such a way that with her over Variety of operating conditions an optimal blade tip gap is given, so that a basic requirement for Achieving good efficiency is guaranteed.
- This task is the one specified for a gas turbine kind solved according to the invention, in which at least one of the funnel-shaped guide parts controlled axially by a motor is movable. Appropriately serve as a motor Variety of hydraulic on the circumference of the guide part Press. However, every other type of drive is Content of this invention.
- the particular advantage of this arrangement lies in the possibility of the blade tip gap actively set by moving the guide part axially. at the limitation of the active adjustability to axial movements is advantageous due to the funnel-shaped shape given the conicity of the guide part, because due to this taper, any axial displacement will result the same also a change in the substantially radial looking at blade tip gap.
- An embodiment of the invention is based on a drawing explained in more detail. The only figure of this drawing shows a longitudinal section through a turbine between a propellant and exit.
- Blade rings 2 with a plurality of blades 3 wedged.
- One by vane rings 4 with a variety gas flow 6 guided by guide vanes 5 expands through a Gas channel 7 and drives the blades 3.
- the gas channel 7 has an annular cross section and is at its pressure side end with a hot gas chamber 8 connected from which compressed and heated gas Arrow direction is driven to a gas outlet opening 9.
- a radially inner boundary of the gas channel 7 is from Hubs 10 of the rotor blades wedged on the turbine shaft 1 2 and carried by the inner ends of the guide vanes 5, non-rotating hubs 11 of the guide vane rings 4 educated. Joints between the hubs 10 and the hubs 11 are sealed by labyrinth seals.
- a radially outer boundary of the gas channel 7 has one funnel-shaped, conical shape and is defined by rings 12 and 13 educated.
- the rings 12 and 13 are funnel-shaped Guide parts 14 and 15 worn, the rings 12 the free
- the ends of the blades 3 lie opposite one another and the rings 13 hold the outer ends of the guide vanes 5 and thus the wear 4 of these vane ring formed. Gaps between the rings 12 and 13 are separated by suitable Sealed sealing rings not shown.
- the guide parts 14 and 15 are thick-walled, very rigid and on in cross section preferably rectangular blocks 16 axially slidably mounted.
- the blocks 16 are in a housing 17th anchored and each of the guide parts 14 and 15 engages his both ends in a wreath from a variety of blocks 16, so that tilting for the guide parts 14 and 15 as well is excluded, like radial movements.
- the housing 17 is as stiff as the guide parts 14 and 15 and carries on the inside, apart from the blocks 16 per guide part 14 or 15 a rigid rib 18.
- This rigid rib 18 is in each case provided axially between the rings of blocks 16, which are assigned to the same guide part 14 or 15.
- the rigid one Rib 18 is particularly practical in the axial direction not deformable.
- Each of the guide parts 14 and 15 carries one radially outward protruding, comparatively thin-walled stop rib 19, which on the hot gas chamber 8 side of the associated rigid rib 18 with one of its free end supported bead 20 supports.
- a reinforcement 21 is arranged, which is also the rigid Rib 18 is facing, but shorter in the axial direction than the bead is 20.
- the guide parts 14 and 15 are in the gas outlet opening 9 facing area radially outwards through a cross section preferably comprises trapezoidal stiffening rib 22, the one radially oriented, the associated rigid Rib 18 has opposite stop surface 23. Between the rigid ribs 18 and their opposite Stop surface 23 are even on the circumference of the associated guide part 14 or 15 distributes a large number arranged by hydraulic presses. Piston 24 of these presses are based directly on the rigid rib 18 and Associated cylinders 25 of the presses lie on the stop surface 23 of the stiffening rib 22. An annular space between the Housing 17 and the guide parts 14 and 15 is membrane-like Partitions 26 divided into chambers.
- the arrangement according to the invention now enables a targeted, active adjustment of just the width of this gap. To this For this purpose, this width is measured by sensors, not shown. If you want to reduce the gap width then by the motor represented by the presses Guide part 14 and / or 15 in the direction of the gas outlet opening 9 moved.
- the stop rib 19 resiliently clamped so that they are in the opposite direction required movement the guide member 14 or 15 carrying them pushes back towards the hot gas chamber 8.
- This task is achieved by the same guiding part 14 or 15 associated presses together have an axial force something 10 times that of gas flow 6 due to operational reasons exerted on the relevant guide member 14 or 15 axial force equivalent. Both axial forces act in the direction the gas outlet opening 9 and add up.
- Deformation energy is used when adjusting a guide part 14 or 15 in the direction of the gas outlet opening 9 saved and serves in an opposite movement to generate a restoring force.
- This restoring force is in any position of the associated guide part 14 or 15 larger than that due to the operation of the gas stream 6 on this applied axial force.
- the restoring force is preferably about 2 to 3 times as large as the operational axial force.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims (12)
- Gasturbine mit einem Leit- (4) und mit einem Laufschaufelkranz (2) in einem Gaskanal (7) und mit einem Gehäuse (17) sowie darin gegen Rotation gesicherten axial gegeneinander verschiebbaren, trichterförmigen Leitteilen (14/15) als Träger von einen äußeren Mantel des Gaskanals (7) bildenden Ringen (12/13)
dadurch gekennzeichnet , daß mindestens eines der trichterförmigen Leitteile (14/15) durch einen Motor gesteuert axial verschiebbar ist. - Gasturbine nach Anspruch 1
dadurch gekennzeichnet, daß als Motor mehrere auf den Umfang des Leitteiles (14/15) verteilte hydraulische oder pneumatische Pressen dienen. - Gasturbine nach Anspruch 1 oder 2
dadurch gekennzeichnet, daß sich Kolben (24) der Pressen mit ihrem freien Ende an einer gehäusefesten, starren Rippe (18) abstützen. - Gasturbine nach einem der Ansprüche 1 bis 3
dadurch gekennzeichnet, daß auf den Kolben (24) der Pressen gleitende Zylinder (25) von dem Leitteil (14/15) getragen sind. - Gasturbine nach einem der Ansprüche 1 bis 4
dadurch gekennzeichnet, daß das Leitteil (14/15) außer den Gaskanal (7) begrenzenden Ringen (12/13) mindestens einen Leitschaufelkranz (4) trägt. - Gasturbine nach einem der Ansprüche 1 bis 5
dadurch gekennzeichnet, daß sich eine flanschartig vom Leitteil (14/15) radial nach außen vorstehende Anschlagrippe (19) mit ihrem freien Ende an der steifen gehäusefesten Rippe (18) abstützt und durch die Pressen elastisch verformbar ist. - Gasturbine nach einem der Ansprüche 1 bis 6
dadurch gekennzeichnet, daß eine von den denselben Leitteil (14/15) beaufschlagenden Pressen gemeinsam erzeugbare Kraft mindestens um den Faktor 10 größer ist, als eine betriebsbedingt auf die Anschlagrippe (19) wirkende Axialkraft. - Gasturbine nach einem der Ansprüche 1 bis 7
dadurch gekennzeichnet, daß eine Rückstellkraft der elastisch verformten Anschlagrippe (19) größer ist, als die betriebsbedingt auf die Anschlagrippe (19) wirkende Axialkraft. - Gasturbine nach einem der Ansprüche 1 bis 8
dadurch gekennzeichnet, daß die Rückstellkraft durch Verschieben des trichterförmigen Leitteils (14/15) einen Laufschaufelspitzenspalt vergrößert. - Gasturbine nach einem der Ansprüche 1 bis 9
dadurch gekennzeichnet, daß die flanschartige, elastisch verformbare Anschlagrippe (19) an ihrer Wurzel einen Endanschlag (Verstärkung 21) aufweist, der die elastische Verformung begrenzt. - Gasturbine nach einem der Ansprüche 1 bis 10
dadurch gekennzeichnet, daß das Leitteil (14/15) sowohl axial vor, als auch axial hinter der Anschlagrippe (19) und der gehäusefesten Rippe (18) durch mehrere, über den Umfang des Leitteils (14) verteilte Axialführungen (Klotz 16) gegen Verkanten gesichert ist. - Gasturbine nach einem der Ansprüche 1 bis 11
dadurch gekennzeichnet, daß die Axialführungen (Klotz 16) vom Gehäuse (17) getragen sind.
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE50112597T DE50112597D1 (de) | 2001-04-12 | 2001-04-12 | Gasturbine mit axial verschiebbaren Gehäuseteilen |
ES01109198T ES2286054T3 (es) | 2001-04-12 | 2001-04-12 | Turbina de gas con piezas de la carcasa axialmente desplazables. |
EP01109198A EP1249577B1 (de) | 2001-04-12 | 2001-04-12 | Gasturbine mit axial verschiebbaren Gehäuseteilen |
JP2002106196A JP4283488B2 (ja) | 2001-04-12 | 2002-04-09 | ガスタービン |
US10/120,808 US6676372B2 (en) | 2001-04-12 | 2002-04-11 | Gas turbine with axially mutually displaceable guide parts |
CNB02119078XA CN100400797C (zh) | 2001-04-12 | 2002-04-12 | 具有可轴向相对移动的引导部件的燃气轮机 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP01109198A EP1249577B1 (de) | 2001-04-12 | 2001-04-12 | Gasturbine mit axial verschiebbaren Gehäuseteilen |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1249577A1 true EP1249577A1 (de) | 2002-10-16 |
EP1249577B1 EP1249577B1 (de) | 2007-06-06 |
Family
ID=8177137
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01109198A Expired - Lifetime EP1249577B1 (de) | 2001-04-12 | 2001-04-12 | Gasturbine mit axial verschiebbaren Gehäuseteilen |
Country Status (6)
Country | Link |
---|---|
US (1) | US6676372B2 (de) |
EP (1) | EP1249577B1 (de) |
JP (1) | JP4283488B2 (de) |
CN (1) | CN100400797C (de) |
DE (1) | DE50112597D1 (de) |
ES (1) | ES2286054T3 (de) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1520958A2 (de) * | 2003-09-30 | 2005-04-06 | General Electric Company | Methode und Einrichtung zur aktiven Spaltregelung bei Turbomaschinen |
EP1900907A2 (de) * | 2006-09-08 | 2008-03-19 | Siemens Power Generation, Inc. | System zur Turbinenschaufelspitzen-Abstandsreduktion für einen Turbinenmotor |
EP1965035A1 (de) | 2007-03-02 | 2008-09-03 | Siemens Aktiengesellschaft | Minimierung der axialen Spalte an verstellbaren Leitgittern und am Konturring für Heissgasexpander |
WO2009074355A1 (de) * | 2007-12-10 | 2009-06-18 | Siemens Aktiengesellschaft | Axialturbomaschine mit reduzierten spaltverlusten |
WO2010108876A1 (de) | 2009-03-26 | 2010-09-30 | Siemens Aktiengesellschaft | Axialturbomaschine mit axial verschiebbarem leitschaufelträger |
DE102009023062A1 (de) * | 2009-05-28 | 2010-12-02 | Mtu Aero Engines Gmbh | Spaltkontrollsystem, Strömungsmaschine und Verfahren zum Einstellen eines Laufspalts zwischen einem Rotor und einer Ummantelung einer Strömungsmaschine |
DE102009037620A1 (de) * | 2009-08-14 | 2011-02-17 | Mtu Aero Engines Gmbh | Strömungsmaschine |
EP2339122A1 (de) * | 2009-12-23 | 2011-06-29 | Siemens Aktiengesellschaft | Turbine mit Einlasskammer mit einstellbarem Volumen |
DE102010045851A1 (de) * | 2010-09-17 | 2012-03-22 | Mtu Aero Engines Gmbh | Kompensation unterschiedlicher Längsdehnungen von Gehäuse und Rotorwelle einer Turbomaschine |
EP3078815A1 (de) * | 2015-04-09 | 2016-10-12 | United Technologies Corporation | Aktive spaltregelung für axialrotorsysteme |
Families Citing this family (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7222488B2 (en) * | 2002-09-10 | 2007-05-29 | General Electric Company | Fabricated cowl for double annular combustor of a gas turbine engine |
GB0411850D0 (en) * | 2004-05-27 | 2004-06-30 | Rolls Royce Plc | Spacing arrangement |
US7234918B2 (en) * | 2004-12-16 | 2007-06-26 | Siemens Power Generation, Inc. | Gap control system for turbine engines |
DE102005018716A1 (de) * | 2005-04-21 | 2006-10-26 | Priebe, Klaus-Peter, Dipl.-Ing. | Dichtspaltregelung |
EP1746256A1 (de) * | 2005-07-20 | 2007-01-24 | Siemens Aktiengesellschaft | Reduzierung von Spaltverlust in Strömungsmaschinen |
DE102005048982A1 (de) * | 2005-10-13 | 2007-04-19 | Mtu Aero Engines Gmbh | Vorrichtung und Verfahren zum axialen Verschieben eines Turbinenrotors |
US7909566B1 (en) | 2006-04-20 | 2011-03-22 | Florida Turbine Technologies, Inc. | Rotor thrust balance activated tip clearance control system |
US7549835B2 (en) * | 2006-07-07 | 2009-06-23 | Siemens Energy, Inc. | Leakage flow control and seal wear minimization system for a turbine engine |
FR2920469A1 (fr) * | 2007-08-30 | 2009-03-06 | Snecma Sa | Aube a calage variable de turbomachine |
US8277177B2 (en) * | 2009-01-19 | 2012-10-02 | Siemens Energy, Inc. | Fluidic rim seal system for turbine engines |
US20100196139A1 (en) * | 2009-02-02 | 2010-08-05 | Beeck Alexander R | Leakage flow minimization system for a turbine engine |
US8177476B2 (en) * | 2009-03-25 | 2012-05-15 | General Electric Company | Method and apparatus for clearance control |
US8177483B2 (en) * | 2009-05-22 | 2012-05-15 | General Electric Company | Active casing alignment control system and method |
US8939715B2 (en) * | 2010-03-22 | 2015-01-27 | General Electric Company | Active tip clearance control for shrouded gas turbine blades and related method |
US9109608B2 (en) * | 2011-12-15 | 2015-08-18 | Siemens Energy, Inc. | Compressor airfoil tip clearance optimization system |
US9488062B2 (en) | 2012-05-10 | 2016-11-08 | General Electric Company | Inner turbine shell axial movement |
DE102012213016A1 (de) * | 2012-07-25 | 2014-01-30 | Siemens Aktiengesellschaft | Verfahren zur Minimierung des Spalts zwischen einem Läufer und einem Gehäuse |
WO2015044266A1 (de) * | 2013-09-27 | 2015-04-02 | Siemens Aktiengesellschaft | Innengehäusenabe für eine gasturbine |
JP6223774B2 (ja) * | 2013-10-15 | 2017-11-01 | 三菱日立パワーシステムズ株式会社 | ガスタービン |
US9840932B2 (en) | 2014-10-06 | 2017-12-12 | General Electric Company | System and method for blade tip clearance control |
CN104389645A (zh) * | 2014-11-15 | 2015-03-04 | 哈尔滨广瀚燃气轮机有限公司 | 一种新型涡轮机高温热膨胀补偿静子密封结构 |
CN106837432B (zh) * | 2015-12-03 | 2019-10-11 | 上海电气电站设备有限公司 | 汽轮机胀差控制结构及控制方法 |
WO2018093429A1 (en) * | 2016-08-10 | 2018-05-24 | In2Rbo, Inc. | Multistage radial compressor and turbine |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
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DE1426818A1 (de) * | 1963-07-26 | 1969-03-13 | Licentia Gmbh | Einrichtung zur Radialverstellung von Segmenten eines Ringes einer Axialturbomaschine,insbesondere -gasturbine,der Leitschaufeln traegt und/oder Laufschaufeln umgibt |
DE2165528A1 (de) * | 1971-12-30 | 1973-07-12 | Kloeckner Humboldt Deutz Ag | Einrichtung zum herstellen eines geringen spaltes zwischen den umlaufenden schaufeln und der wandung einer stroemungsmaschine |
US4177004A (en) | 1977-10-31 | 1979-12-04 | General Electric Company | Combined turbine shroud and vane support structure |
US5203673A (en) * | 1992-01-21 | 1993-04-20 | Westinghouse Electric Corp. | Tip clearance control apparatus for a turbo-machine blade |
Family Cites Families (6)
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US3227418A (en) * | 1963-11-04 | 1966-01-04 | Gen Electric | Variable clearance seal |
US3520635A (en) * | 1968-11-04 | 1970-07-14 | Avco Corp | Turbomachine shroud assembly |
CH538046A (de) * | 1971-11-10 | 1973-06-15 | Bbc Brown Boveri & Cie | Einrichtung zum Einstellen des Spitzenspiels an Strömungsmaschinen |
GB2042646B (en) * | 1979-02-20 | 1982-09-22 | Rolls Royce | Rotor blade tip clearance control for gas turbine engine |
EP0103260A3 (de) * | 1982-09-06 | 1984-09-26 | Hitachi, Ltd. | Einstellung des Spiels zwischen Turbinenschaufelspitzen und Gehäuse |
EP1243756A1 (de) * | 2001-03-23 | 2002-09-25 | Siemens Aktiengesellschaft | Turbine |
-
2001
- 2001-04-12 EP EP01109198A patent/EP1249577B1/de not_active Expired - Lifetime
- 2001-04-12 ES ES01109198T patent/ES2286054T3/es not_active Expired - Lifetime
- 2001-04-12 DE DE50112597T patent/DE50112597D1/de not_active Expired - Lifetime
-
2002
- 2002-04-09 JP JP2002106196A patent/JP4283488B2/ja not_active Expired - Fee Related
- 2002-04-11 US US10/120,808 patent/US6676372B2/en not_active Expired - Lifetime
- 2002-04-12 CN CNB02119078XA patent/CN100400797C/zh not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1426818A1 (de) * | 1963-07-26 | 1969-03-13 | Licentia Gmbh | Einrichtung zur Radialverstellung von Segmenten eines Ringes einer Axialturbomaschine,insbesondere -gasturbine,der Leitschaufeln traegt und/oder Laufschaufeln umgibt |
DE2165528A1 (de) * | 1971-12-30 | 1973-07-12 | Kloeckner Humboldt Deutz Ag | Einrichtung zum herstellen eines geringen spaltes zwischen den umlaufenden schaufeln und der wandung einer stroemungsmaschine |
US4177004A (en) | 1977-10-31 | 1979-12-04 | General Electric Company | Combined turbine shroud and vane support structure |
US5203673A (en) * | 1992-01-21 | 1993-04-20 | Westinghouse Electric Corp. | Tip clearance control apparatus for a turbo-machine blade |
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1520958A3 (de) * | 2003-09-30 | 2012-10-17 | General Electric Company | Methode und Einrichtung zur aktiven Spaltregelung bei Turbomaschinen |
EP1520958A2 (de) * | 2003-09-30 | 2005-04-06 | General Electric Company | Methode und Einrichtung zur aktiven Spaltregelung bei Turbomaschinen |
EP1900907A2 (de) * | 2006-09-08 | 2008-03-19 | Siemens Power Generation, Inc. | System zur Turbinenschaufelspitzen-Abstandsreduktion für einen Turbinenmotor |
EP1900907A3 (de) * | 2006-09-08 | 2009-12-16 | Siemens Energy, Inc. | System zur Turbinenschaufelspitzen-Abstandsreduktion für einen Turbinenmotor |
EP1965035A1 (de) | 2007-03-02 | 2008-09-03 | Siemens Aktiengesellschaft | Minimierung der axialen Spalte an verstellbaren Leitgittern und am Konturring für Heissgasexpander |
CN101255804B (zh) * | 2007-03-02 | 2016-03-30 | 西门子公司 | 流体机,尤其是热气膨胀机 |
WO2009074355A1 (de) * | 2007-12-10 | 2009-06-18 | Siemens Aktiengesellschaft | Axialturbomaschine mit reduzierten spaltverlusten |
WO2010108876A1 (de) | 2009-03-26 | 2010-09-30 | Siemens Aktiengesellschaft | Axialturbomaschine mit axial verschiebbarem leitschaufelträger |
DE102009023062A1 (de) * | 2009-05-28 | 2010-12-02 | Mtu Aero Engines Gmbh | Spaltkontrollsystem, Strömungsmaschine und Verfahren zum Einstellen eines Laufspalts zwischen einem Rotor und einer Ummantelung einer Strömungsmaschine |
US9068471B2 (en) | 2009-05-28 | 2015-06-30 | Mtu Aero Engines Gmbh | Clearance control system, turbomachine and method for adjusting a running clearance between a rotor and a casing of a turbomachine |
DE102009037620A1 (de) * | 2009-08-14 | 2011-02-17 | Mtu Aero Engines Gmbh | Strömungsmaschine |
EP2339122A1 (de) * | 2009-12-23 | 2011-06-29 | Siemens Aktiengesellschaft | Turbine mit Einlasskammer mit einstellbarem Volumen |
DE102010045851A1 (de) * | 2010-09-17 | 2012-03-22 | Mtu Aero Engines Gmbh | Kompensation unterschiedlicher Längsdehnungen von Gehäuse und Rotorwelle einer Turbomaschine |
EP3078815A1 (de) * | 2015-04-09 | 2016-10-12 | United Technologies Corporation | Aktive spaltregelung für axialrotorsysteme |
US10323536B2 (en) | 2015-04-09 | 2019-06-18 | United Technologies Corporation | Active clearance control for axial rotor systems |
Also Published As
Publication number | Publication date |
---|---|
ES2286054T3 (es) | 2007-12-01 |
US20020164246A1 (en) | 2002-11-07 |
US6676372B2 (en) | 2004-01-13 |
EP1249577B1 (de) | 2007-06-06 |
DE50112597D1 (de) | 2007-07-19 |
CN1381670A (zh) | 2002-11-27 |
JP2002327603A (ja) | 2002-11-15 |
CN100400797C (zh) | 2008-07-09 |
JP4283488B2 (ja) | 2009-06-24 |
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