EP1716316A1 - Turbine a gaz a carter de compresseur protege du refroidissement et procede pour faire fonctionner une turbine a gaz - Google Patents

Turbine a gaz a carter de compresseur protege du refroidissement et procede pour faire fonctionner une turbine a gaz

Info

Publication number
EP1716316A1
EP1716316A1 EP05715228A EP05715228A EP1716316A1 EP 1716316 A1 EP1716316 A1 EP 1716316A1 EP 05715228 A EP05715228 A EP 05715228A EP 05715228 A EP05715228 A EP 05715228A EP 1716316 A1 EP1716316 A1 EP 1716316A1
Authority
EP
European Patent Office
Prior art keywords
compressor
gas turbine
cavity
housing
shut
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Withdrawn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
EP05715228A
Other languages
German (de)
English (en)
Inventor
Holger Bauer
Bernhard Küsters
Dieter Minninger
Marc Mittelbach
Andreas Peters
Stephan Schmidt
Steffen Skreba
Bernd STÖCKER
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 EP05715228A priority Critical patent/EP1716316A1/fr
Publication of EP1716316A1 publication Critical patent/EP1716316A1/fr
Withdrawn legal-status Critical Current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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • 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
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/105—Final actuators by passing part of the fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0223—Control schemes therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction
    • 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a gas turbine with a compressor housing which is protected against cooling, in particular against rapid cooling or cooling. Accordingly, the invention relates not only to the gas turbine in its entirety but also to the compressor with the compressor housing protected against cooling and the compressor housing itself. The invention further relates to a method for operating such a gas turbine.
  • Gas turbines are well known.
  • Various cooling devices are also known for gas turbines.
  • such cooling devices essentially relate to cooling in the area of a combustion chamber or a turbine section of the gas turbine, cf. z. B.
  • EP 0 988 441 which deals with cooling the combustion chamber wall, or EP 0 791 127 B1, EP 1 245 806 AI, WO 01/55559 AI, US 6,120,249, all of which deal with the cooling of turbine blades.
  • Extraction of compressed or partially compressed air is tapped, the tapping line having a valve for adjusting the cooling air flow.
  • US 3,736,069 discloses a gas turbine with controllable cooling of the turbine blades exposed to hot gas.
  • a ring element is opposite a valve seat, which cause a variable gap due to different thermal expansion coefficients. This adjusts the coolant flow.
  • No. 4,213,738 likewise shows a flow path for a cooling air system with a variable gap through which the cooling air can flow for adjusting the cooling.
  • Adjustable cooling for gas turbines is also known from US 2,951,340 and US 3,632,221.
  • the invention consists in specifying a possibility with which the cooling of the compressor housing is prevented or at least delayed in order to avoid the risk of contact between slower and faster cooling elements, that is to say e.g. B. to reduce the housing and the rotor.
  • Turbine and a compressor comprising a compressor housing, the compressor for cooling the turbine being tapped by means of at least one tapping line for the removal of compressed or partially compressed air, it is provided that the tapping line has a shut-off device, in particular a valve.
  • a compressor or a compressor housing with the features of claim 6.
  • the object is achieved by a method for operating such a gas turbine with the features of claim 4, in that when the gas turbine is shut down, the shut-off device, in particular the valve, is closed or partially closed.
  • the invention is based on the knowledge that certain elements in a gas turbine cool faster than others Elements.
  • the faster cooling elements are, in particular, elements that are in direct contact with the volume of the ambient air.
  • This constellation makes it necessary to set sufficient distances, for example dimensionally determined by the degree of thermal expansion of the elements involved.
  • the advantage of the invention is that the heat loss of the compressor housing can be regulated by the shut-off device.
  • the shut-off device When the gas turbine is shut down, the shut-off device is closed or partially closed in order to achieve a defined heat loss in the compressor housing. In this way it can be ensured that the compressor housing and the rotor rotating therein cool down to approximately the same extent. Uniform cooling is guaranteed at least to the extent that the risk of the rotor brushing against the inside of the compressor housing is minimized.
  • the tap line has a cavity, which is located in the flow direction of the extracted or removable air in front of the shut-off device. The volume of the cavity thus acts like a heat insulator. Air is known to be a good thermal insulator. Air is contained in the cavity at a temperature which essentially corresponds to the temperature of the rotor. The cavity therefore prevents or delays cooling or cooling of the compressor housing due to the insulating effect.
  • the cavity in the housing of the compressor is shaped in such a way that, starting from a position of an inlet of the bleed line and a stationary blade located in this area, it extends at least into the area of a next stationary blade, an enlarged effective area results cavity acting as an insulator.
  • shut-off device is assigned to the cavity, so that the volume of the cavity can be separated from the volume flow through the compressor housing.
  • the advantage of the invention and its configurations is that the or each cavity can also be used to cool the housing of the rear compressor stages. As a result, the thermal expansion The flow channel in the compressor is reduced. The bleed air can be discharged from the housing further "behind” accordingly.
  • FIG. 2 shows the detail according to FIG. 1 with a tap line which can be locked by a shut-off device
  • FIG. 3 shows a bleed line with a cavity designed and enlarged with a view to a desired thermal influence on the compressor housing
  • FIG. 4 shows the cavity lockable by a shut-off device.
  • both the compressor and the turbine comprise a number of stationary guide vanes, which are also attached to an inner wall of the housing of the compressor or turbine to form rows of guide vanes.
  • the rotor blades serve to drive the turbine shaft by transmitting impulses from the working medium flowing through the turbine.
  • the guide vanes serve to guide the flow of the working medium between two successive rows of moving blades or rotating vane rings when viewed in the flow direction of the working medium. A successive pair of one
  • a ring of guide blades or a row of guide blades and a ring of rotor blades or a row of rotor blades is also referred to as a turbine stage or a compressor stage.
  • FIG. 1 shows in a vertical section along the longitudinal axis of a gas turbine a section from the compressor, designated overall by 10, of such a gas turbine.
  • the alternating sequence of stationary blades 11 and rotating blades is shown, which are attached to a turbine shaft 13 for this purpose.
  • a radial gap 15 remains between the rotating blades 12 and the stationary blades 11 as part of a housing 14 of the gas turbine or of the compressor 10 of the gas turbine.
  • bleed line 16 modified in accordance with the invention.
  • the bleed line 16 can be locked or at least partially locked in order to prevent or prevent the outflow of air through the bleed line 16 reduce.
  • a shut-off device shown as valve 19 is provided in the bleed line 16.
  • the tap line 16 can be partially or completely locked. Ambient air then no longer flows through tap line 16, or only to a reduced extent. The heat loss otherwise associated with the outflow of the ambient air is correspondingly prevented or reduced.
  • FIG. 3 shows essentially the same representation as FIG. 2.
  • the cavity 17 is designed with a view to a desired thermal influence on the compressor housing 14.
  • the cavity 17 is on the one hand enlarged and on the other hand shaped in such a way that it covers at least the area of two successive rotating blades 12 along its longitudinal extent. With a cavity 17 designed in this way, a particularly favorable shape results for its function as an insulator.
  • the cavity can also be made longer than shown. The size and shape of the cavity are essentially limited only by the demands on the strength of the compressor housing 14.
  • FIG. 4 shows a representation compared to FIG. 3 with a shut-off device 20.
  • the cavity 17 is fluidically flowed from the compressor duct by means of the shut-off element 20 in the form of a bulkhead or the like, the mobility of which is illustrated by the vertical arrow is decoupled.
  • the shut-off device 20 is arranged in the area of an inlet of the cavity 17, so that the shut-off device allows the essential part of the volume of the cavity to be separated from the compressor channel Compressor housing 14 in
  • the cavity 17 is selectively pressurized with compressor air, so that the compressor stages which are at the rear (and thus warmer) are cooled in order to achieve delayed heating of the compressor housing 14 in this way.
  • the compressor housing 14 is then heated to the same extent as the rotor.
  • a gas turbine with a shut-off device is specified in a bleed line 18 provided for removing cooling air from the compressor 10, so that the compressor housing 14 can be partitioned off to reduce cooling.
  • the housing and rotor cool down to approximately the same extent, so that there is an even heat contraction.
  • a stronger cooling of the housing 14 and thus a constriction around the slower cooling rotor can be prevented in this way. This makes warm starts easier because rubbing against the rotor on the inside wall of the housing, which cools down in the same way as the rotor, is largely ruled out.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une turbine à gaz comportant une turbine et un compresseur (10) doté d'un carter (14), ainsi qu'un procédé de fonctionnement associé. Selon l'invention, le carter (10) est purgé pour refroidir la turbine au moyen d'au moins un conduit de vidange (16) servant à l'évacuation de l'air comprimé ou partiellement comprimé. Ce conduit de vidange (16) est doté d'un dispositif d'arrêt, notamment d'un clapet (19), pour réguler le flux de l'air de vidange et, par conséquent, le refroidissement du carter (14).
EP05715228A 2004-02-19 2005-01-31 Turbine a gaz a carter de compresseur protege du refroidissement et procede pour faire fonctionner une turbine a gaz Withdrawn EP1716316A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05715228A EP1716316A1 (fr) 2004-02-19 2005-01-31 Turbine a gaz a carter de compresseur protege du refroidissement et procede pour faire fonctionner une turbine a gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04003669A EP1566531A1 (fr) 2004-02-19 2004-02-19 Turbine à gas avec carter protégé contre le refroidessement et Méthode de fonctionnement d'une turbine à gas
EP05715228A EP1716316A1 (fr) 2004-02-19 2005-01-31 Turbine a gaz a carter de compresseur protege du refroidissement et procede pour faire fonctionner une turbine a gaz
PCT/EP2005/000925 WO2005090755A1 (fr) 2004-02-18 2005-01-31 Turbine a gaz a carter de compresseur protege du refroidissement et procede pour faire fonctionner une turbine a gaz

Publications (1)

Publication Number Publication Date
EP1716316A1 true EP1716316A1 (fr) 2006-11-02

Family

ID=34707315

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04003669A Withdrawn EP1566531A1 (fr) 2004-02-18 2004-02-19 Turbine à gas avec carter protégé contre le refroidessement et Méthode de fonctionnement d'une turbine à gas
EP05715228A Withdrawn EP1716316A1 (fr) 2004-02-19 2005-01-31 Turbine a gaz a carter de compresseur protege du refroidissement et procede pour faire fonctionner une turbine a gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP04003669A Withdrawn EP1566531A1 (fr) 2004-02-18 2004-02-19 Turbine à gas avec carter protégé contre le refroidessement et Méthode de fonctionnement d'une turbine à gas

Country Status (5)

Country Link
US (1) US8336315B2 (fr)
EP (2) EP1566531A1 (fr)
JP (1) JP4584939B2 (fr)
CN (1) CN1942656B (fr)
WO (1) WO2005090755A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5747403B2 (ja) * 2010-12-08 2015-07-15 三菱重工業株式会社 ターボ回転機械及びその運転方法
US20120183398A1 (en) * 2011-01-13 2012-07-19 General Electric Company System and method for controlling flow through a rotor
EP2532898A1 (fr) * 2011-06-08 2012-12-12 Siemens Aktiengesellschaft Turbocompresseur axial
EP2977590B1 (fr) * 2014-07-25 2018-01-31 Ansaldo Energia Switzerland AG Ensemble compresseur pour turbine à gaz
CN107850082B (zh) * 2015-10-27 2019-11-05 三菱重工业株式会社 旋转机械
US10247029B2 (en) * 2016-02-04 2019-04-02 United Technologies Corporation Method for clearance control in a gas turbine engine
KR101993049B1 (ko) * 2017-09-21 2019-06-25 두산중공업 주식회사 압축기 및 이를 포함하는 가스 터빈

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2837270A (en) * 1952-07-24 1958-06-03 Gen Motors Corp Axial flow compressor
US2951340A (en) * 1956-01-03 1960-09-06 Curtiss Wright Corp Gas turbine with control mechanism for turbine cooling air
US3736069A (en) * 1968-10-28 1973-05-29 Gen Motors Corp Turbine stator cooling control
DE1938132A1 (de) * 1969-07-26 1971-01-28 Daimler Benz Ag Leitschaufeln von Axialverdichtern
US3632221A (en) * 1970-08-03 1972-01-04 Gen Electric Gas turbine engine cooling system incorporating a vortex shaft valve
US4213738A (en) * 1978-02-21 1980-07-22 General Motors Corporation Cooling air control valve
US4332133A (en) * 1979-11-14 1982-06-01 United Technologies Corporation Compressor bleed system for cooling and clearance control
JPS611809A (ja) 1984-06-13 1986-01-07 Hitachi Ltd 蒸気タ−ビンのケ−シング
GB2172053B (en) * 1985-03-05 1988-10-05 Rolls Royce Gas turbine engine valve control system
US4815272A (en) * 1987-05-05 1989-03-28 United Technologies Corporation Turbine cooling and thermal control
FR2653171B1 (fr) * 1989-10-18 1991-12-27 Snecma Carter de compresseur de turbomachine muni d'un dispositif de pilotage de son diametre interne.
US5203162A (en) * 1990-09-12 1993-04-20 United Technologies Corporation Compressor bleed manifold for a gas turbine engine
FR2695161B1 (fr) * 1992-08-26 1994-11-04 Snecma Système de refroidissement d'un compresseur de turbomachine et de contrôle des jeux.
US5488823A (en) * 1993-05-12 1996-02-06 Gas Research Institute Turbocharger-based bleed-air driven fuel gas booster system and method
DE4327376A1 (de) * 1993-08-14 1995-02-16 Abb Management Ag Verdichter sowie Verfahren zu dessen Betrieb
DE4411616C2 (de) * 1994-04-02 2003-04-17 Alstom Verfahren zum Betreiben einer Strömungsmaschine
JP3824324B2 (ja) * 1994-10-31 2006-09-20 ウエスチングハウス・エレクトリック・コーポレイション 冷却式プラットホームを備えたガスタービン翼
ES2144147T3 (es) 1994-11-10 2000-06-01 Siemens Westinghouse Power Alabe de turbina de gas con mortaja interna refrigerada.
US6004095A (en) * 1996-06-10 1999-12-21 Massachusetts Institute Of Technology Reduction of turbomachinery noise
US6018950A (en) 1997-06-13 2000-02-01 Siemens Westinghouse Power Corporation Combustion turbine modular cooling panel
US6574965B1 (en) * 1998-12-23 2003-06-10 United Technologies Corporation Rotor tip bleed in gas turbine engines
WO2001055559A1 (fr) 2000-01-27 2001-08-02 Siemens Aktiengesellschaft Aube de turbine poreuse et turbine equipee de telles aubes
JP2002295291A (ja) 2001-03-29 2002-10-09 Denso Corp 内燃機関のアイドル回転速度制御方法
DE10233032A1 (de) * 2002-07-20 2004-01-29 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit integriertem Fluidzirkulationssystem
FR2875866B1 (fr) * 2004-09-30 2006-12-08 Snecma Moteurs Sa Procede de circulation d'air dans un compresseur de turbomachine, agencement de compresseur le mettant en oeuvre , etage de compression et compresseur comportant un tel agencement, et moteur d'aeronef equipe d'un tel compresseur

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2005090755A1 *

Also Published As

Publication number Publication date
EP1566531A1 (fr) 2005-08-24
US8336315B2 (en) 2012-12-25
CN1942656B (zh) 2010-11-03
JP4584939B2 (ja) 2010-11-24
CN1942656A (zh) 2007-04-04
JP2007523287A (ja) 2007-08-16
WO2005090755A1 (fr) 2005-09-29
US20070289286A1 (en) 2007-12-20

Similar Documents

Publication Publication Date Title
DE602004000527T2 (de) Verfahren zur Kühlung von heissen Turbinenbauteilen mittels eines teilweise in einem externen Wärmetauscher gekühlten Luftstromes und so gekühltes Turbinentriebwerk
DE2532415C2 (de) Vorrichtung zum selbsttätigen Regeln des Spiels zwischen den Spitzen der Rotorschaufeln einer Gasturbine und der gegenüberliegenden Wand eines Turbinengehäuses
DE3909606C2 (de) Spaltsteueranordnung
DE60015233T2 (de) Turbinenschaufel mit interner Kühlung
DE69827555T2 (de) Gasturbine
EP0929736B1 (fr) Turbine a vapeur et procede pour le refroidissement d'une turbine a vapeur fonctionnant en mode ventilation
EP1389690B1 (fr) Vis intérieurement refroidissable
EP1716316A1 (fr) Turbine a gaz a carter de compresseur protege du refroidissement et procede pour faire fonctionner une turbine a gaz
DE112014004335T5 (de) Gasturbine, Gasturbinen-Steuergerät und Gasturbinen-Betriebsverfahren
EP2136052A1 (fr) Turbine à turbopropulseur dotée d'un dispositif de production d'un flux d'air de refroidissement
EP1000224B1 (fr) Repartition de l'air de refroidissement dans l'etage de turbine d'une turbine a gaz
EP1173664A1 (fr) Systeme d'air de refroidissement
DE1601555A1 (de) Gekuehlter Turbinenleitkranz fuer bei hohen Temperaturen arbeitende Turbinen
WO2006021520A1 (fr) Injection de fluide dans une turbine a gaz pendant une phase de refroidissement
EP2084368A1 (fr) Aube de turbine
DE2451500A1 (de) Gasturbinentriebwerk
CH710576A2 (de) Turbinenschaufel mit mehreren Kühlkanälen.
EP1165942B1 (fr) Turbomachine avec un systeme d'elements de paroi pouvant etre refroidi et procede de refroidissement d'un systeme d'elements de paroi
CH706962B1 (de) Serpentinenkühlung der Leitschaufelendwand.
EP1167721B1 (fr) Procédé et dispositif de refroidissement d'une turbine a gaz
DE4336143C2 (de) Kühlverfahren für Turbomaschinen
DE102010035393B4 (de) Turbine und Verfahren zum Betrieb einer Turbine für ein CAES-System
WO2013182381A1 (fr) Conduit de pontage pour agent de refroidissement pour turbine à gaz installable dans une aube de turbine creuse refroidie
WO2017133873A1 (fr) Turbine à gaz équipée d'un piston à poussée axiale et d'un palier radial
DE102016102049A1 (de) Gasturbine und Verfahren zum Konditionieren der Temperatur einer Turbinenscheibe einer Gasturbine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20060726

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH DE ES FR GB IT LI

DAX Request for extension of the european patent (deleted)
RBV Designated contracting states (corrected)

Designated state(s): CH DE ES FR GB IT LI

17Q First examination report despatched

Effective date: 20071012

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20131119

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20140401