EP1664490A2 - Dispositif pour detecter une rupture d'arbre sur une turbine a gaz et turbine a gaz - Google Patents

Dispositif pour detecter une rupture d'arbre sur une turbine a gaz et turbine a gaz

Info

Publication number
EP1664490A2
EP1664490A2 EP05766945A EP05766945A EP1664490A2 EP 1664490 A2 EP1664490 A2 EP 1664490A2 EP 05766945 A EP05766945 A EP 05766945A EP 05766945 A EP05766945 A EP 05766945A EP 1664490 A2 EP1664490 A2 EP 1664490A2
Authority
EP
European Patent Office
Prior art keywords
turbine
actuating element
sensor element
gas turbine
stator
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
EP05766945A
Other languages
German (de)
English (en)
Other versions
EP1664490B1 (fr
Inventor
Christopher Bilson
Ian Fitzgerald
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1664490A2 publication Critical patent/EP1664490A2/fr
Application granted granted Critical
Publication of EP1664490B1 publication Critical patent/EP1664490B1/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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/02—Shutting-down responsive to overspeed
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor

Definitions

  • the invention relates to a device for detecting a shaft fracture on a gas turbine. Furthermore, the invention relates to a gas turbine.
  • Gas turbines designed as aircraft engines have at least one compressor, at least one combustion chamber and at least one turbine.
  • Aircraft engines are known from the prior art, on the one hand have three upstream of the combustion chamber positioned compressor and three positioned downstream of the combustion chamber turbines.
  • the three compressors are a low-pressure compressor, a medium-pressure compressor and a high-pressure compressor.
  • the three turbines are a high-pressure turbine, a medium-pressure turbine and a low-pressure turbine.
  • the rotors of high-pressure compressor and high-pressure turbine, medium-pressure compressor and medium-pressure turbine and low-pressure compressor and low-pressure turbine are connected to each other by a respective shaft, wherein the three shafts surround each other concentrically and are thus nested one inside the other.
  • the medium-pressure compressor of the medium-pressure turbine can no longer extract any work or power, whereby an overspeed at the medium-pressure turbine can then set.
  • spin-off of the medium-pressure turbine must be avoided, as this can damage the entire aircraft engine.
  • a shaft break on a gas turbine must be reliably detectable in order to interrupt a fuel supply to the combustion chamber when a shaft fracture occurs.
  • Such a detection of a wave fracture is particularly difficult if the gas turbine, as described above, has three concentrically enclosing and thus nested waves. In this case, especially the detection of a shaft breakage of the middle shaft, which couples the medium-pressure turbine to the medium-pressure compressor, presents difficulties.
  • the present invention is based on the problem to provide a novel device for detecting a shaft fracture on a Gas ⁇ turbine.
  • This problem is solved by a device for detecting a shaft break on a gas turbine in the sense of patent claim 1.
  • a device for detecting a shaft fracture on a rotor of a first turbine, in particular a medium-pressure turbine, a gas turbine, in particular an aircraft engine proposed, wherein downstream of the first turbine, a second turbine, in particular a low-pressure turbine, is positioned with an intermediate the rotor of the first turbine and a stator of the second turbine, with respect to a flow channel radially inwardly positioned actuator, and with a guided in the stator of the second turbine sensor element to convert a detected by the radially inwardly positioned actuator shaft breakage into an electrical signal and in order to transmit this electrical signal to a switching element which is positioned radially outwardly of a housing of the gas turbine with respect to the flow channel.
  • a device for detecting a shaft fracture with a mechanical actuating element which is positioned radially inwardly between a rotor and a stator of two adjacent turbines with respect to a flow channel of the gas turbine.
  • a shaft break of the upstream positioned turbine can be detected, wherein in the event of a shaft break the actuating element is pushed axially and hits the sensor element.
  • the sensor element is preferably designed as an impact sensor whose structure is changed when the actuating element strikes the sensor element and which thus generates an electrical signal representing the shaft break.
  • the sensor element is guided in the stator of the turbine positioned downstream and conducts the electrical signal representing the shaft break radially outwards to a switching element.
  • the sensor element can be pulled out of the same in the radial direction in the case of a mounted gas turbine. This ensures that, when the gas turbine is installed, all the electrical components of the device according to the invention for detecting a shaft fracture are easily accessible without the need for dismantling the gas turbine.
  • the sensor element can be easily pulled out of the assembled gas turbine in the radial direction, the switching element is positioned externally on the casing of the gas turbine.
  • the gas turbine according to the invention is defined in independent claim 9.
  • FIG. 1 shows a detail of a gas turbine according to the invention with a device according to the invention for detecting a shaft fracture on a gas turbine.
  • FIG. 1 shows a partial cross-section through a gas turbine according to the invention, namely an aircraft engine, in the radially inner region between a rotor of a medium-pressure turbine 10 and a stator of a low-pressure turbine 11.
  • the rotor of the medium-pressure turbine 10 has a rotor disk 12 in the flow direction (FIG. Arrow 15) seen last runner ring of the medium-pressure turbine 10; From the stator of the low-pressure turbine 11, a radially inner sealing structure 13 of a first vane ring of the low-pressure turbine 11, viewed in the flow direction, is shown.
  • the sealing structure 13 comprises honeycomb seals 14 of a so-called "inner air seal" seal.
  • the flow direction through the gas turbine is visualized in FIG. 1 by an arrow 15.
  • the stator of the low-pressure turbine 11 is thus positioned downstream of the rotor of the medium-pressure turbine 10.
  • the first or foremost guide vane ring of the low-pressure turbine 11, as seen in the flow direction adjoins the last or rearmost vane ring of the medium-pressure turbine 10, viewed in the flow direction.
  • a high-pressure turbine is preferably positioned upstream of the medium-pressure turbine 10.
  • an actuating element 16 between the rotor of the medium-pressure turbine 10 and the stator of the low-pressure turbine 11, the actuating element 16 in the embodiment shown between the last rotor blade ring of the medium-pressure turbine 10 and in the direction of flow seen first vane ring of the low-pressure turbine 11 is positioned.
  • the actuating element 16 is positioned radially inwardly relative to a flow channel within the gas turbine adjacent to the rotor disk 12 of the last rotor shaft of the medium-pressure turbine 10, as viewed in the flow direction.
  • the actuating element 16 is aligned axially and guided in the sealing structure 13 serving as a seal carrier.
  • a bore is introduced into the sealing structure 13 with an internal thread, wherein a nut 17 is fastened with a corresponding external thread in the bore of the sealing structure 13.
  • the nut 17 in turn has a central bore in which the actuating element 16 is displaceably guided in the axial direction.
  • the actuating element 16 which is displaceably mounted or guided in the nut 17 in the axial direction, is fixed in the axial position via a shear-off pin 18.
  • the abscherba ⁇ re pin 18 extends substantially in the radial direction of radi ⁇ al outside by the nut 17 and projects into a corresponding opening in ⁇ within the actuating element 16 in.
  • the shear-off pin 18 and the resulting axial fixation of the actuating element 16 ensure that no axial displacement of the actuating element 16 occurs during normal or regular operation of the gas turbine.
  • a washer 19 is arranged between the seal structure 13 and the nut 17. Through the thickness of this washer 19, a distance between the rotor disk 12 and one of the rotor disk 12 adjacent end 20 of the actuator 16 can be adjusted.
  • the device according to the invention for detecting a shaft fracture has a sensor element 21.
  • the sensor element 21 is designed as an impact sensor or impact sensor or impact sensor and interacts with an end 22 of the actuating element 16 opposite the end 20, that when the second end 22 of the actuating element 16 impinges on the sensor element 21 as a result of a shaft break, the sensor element 21 generates an electrical signal repeating the shaft break, in order to position this electrical signal on a radially outer side of a housing of the gas turbine Transfer switching element.
  • the sensor element 21 is guided in the stator of the low-pressure turbine 11 and can be removed in the radial direction from the stator of the low-pressure turbine 11.
  • the radially inward end of the sensor element 21 is guided in a receptacle 23, the receptacle 23 being fastened to the sealing structure 13 via a support 24.
  • the carrier 23 is fixedly connected via a rivet connection 25 with the sealing structure 13.
  • the Auf ⁇ receiving 23 held by the carrier 24 has in the region of the end 22 of the actuating element 16 via an opening so that the actuating element 16 can be moved in the direction of the sensor element 21 in the event of a shaft break.
  • FIG. 1 shows the device according to the invention for the detection of a shaft break or the corresponding gas turbine in an arrangement which corresponds to the regular or normal operation of a gas turbine.
  • the actuation element 16 is fixed in its axial displaceability by the abscher ⁇ ble pin 18. If a shaft break now occurs on the shaft, which connects the medium-pressure turbine 11 with a medium-pressure compressor (not shown), then the medium-pressure compressor of the medium-pressure turbine 10 can no longer take any work or power and spinning of the medium-pressure turbine 10 can occur , Due to the pressure conditions on the medium-pressure turbine 10, the rotor, namely the rotor disk 12 of the last or rearmost rotor blade ring of the center pressure turbine 10 shown in FIG.
  • the sensor element 21, which is in the form of an impact sensor or impact sensor, preferably has an electrical circuit which is integrated into a ceramic base body and whose structure or integrity is monitored by the switching element. If the actuating element 16 strikes the ceramic base body of the sensor element 21 due to a wave fracture, it is destroyed and the circuit integrated into the ceramic base body is interrupted.
  • the change in the signal provided by the sensor element 21 represents a break in the shaft and can be evaluated or further processed in a simple manner by the switching element in order to ultimately interrupt the fuel supply to the combustion chamber.
  • the sensor element 21 is guided in the stator of the low-pressure turbine 11 such that the sensor element 21 can be pulled out of the stator in the radial direction.
  • the extraction of the sensor element 21 in the radial direction from the stator, in particular a guide vane of a vane ring, of the low-pressure turbine 11 can be carried out with the gas engine mounted or assembled. In this way, it is possible to subject the sensor element 21 to inspection or maintenance without great expense. All electric or electronic assemblies of the device according to the invention for detecting a wave fracture are accordingly accessible without great installation effort. The remaining, only with disassembled gas turbine accessible assemblies of er ⁇ inventive device for detecting a shaft fracture, such. As the actuator 16 are purely mechanical, very robust and therefore less frequently inspected or maintained, as the electrical or electronic components thereof.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Measuring Fluid Pressure (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

L'invention concerne un dispositif servant à détecter une rupture d'arbre au niveau d'un rotor d'une première turbine (10), en particulier une turbine moyenne pression, d'une turbine à gaz, en particulier un groupe motopropulseur, une seconde turbine (11), en particulier une turbine basse pression, étant placée en aval de la première turbine (10). Ce dispositif comprend un élément d'actionnement (16) qui est placé entre le rotor de la première turbine (10) et un stator de la seconde turbine (11) de telle sorte qu'il soit situé à l'intérieur radialement vis-à-vis d'un canal d'écoulement, ainsi qu'un élément de détection (21) logé dans le stator de la seconde turbine (11) pour convertir une rupture d'arbre détectée par l'élément d'actionnement (16) situé à l'intérieur radialement en un signal électrique et transmettre ce signal électrique à un élément de commutation qui est placé sur un carter de la turbine à gaz de façon à se trouver à l'extérieur radialement vis-à-vis du canal d'écoulement.
EP05766945A 2004-07-14 2005-07-07 Dispositif pour detecter une rupture d'arbre sur une turbine a gaz et turbine a gaz Ceased EP1664490B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004033924A DE102004033924A1 (de) 2004-07-14 2004-07-14 Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine
PCT/DE2005/001206 WO2006005319A2 (fr) 2004-07-14 2005-07-07 Dispositif pour detecter une rupture d'arbre sur une turbine a gaz et turbine a gaz

Publications (2)

Publication Number Publication Date
EP1664490A2 true EP1664490A2 (fr) 2006-06-07
EP1664490B1 EP1664490B1 (fr) 2007-10-24

Family

ID=35458000

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05766945A Ceased EP1664490B1 (fr) 2004-07-14 2005-07-07 Dispositif pour detecter une rupture d'arbre sur une turbine a gaz et turbine a gaz

Country Status (5)

Country Link
US (1) US7758301B2 (fr)
EP (1) EP1664490B1 (fr)
DE (2) DE102004033924A1 (fr)
RU (1) RU2377420C2 (fr)
WO (1) WO2006005319A2 (fr)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004026366A1 (de) * 2004-05-29 2005-12-15 Mtu Aero Engines Gmbh Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine
DE102005042271A1 (de) * 2005-09-06 2007-03-08 Mtu Aero Engines Gmbh Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine
DE102006017790B3 (de) * 2006-04-15 2007-07-26 Mtu Aero Engines Gmbh Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine
US9355571B2 (en) * 2008-01-23 2016-05-31 Sikorsky Aircraft Corporation Modules and methods for biasing power to a multi-engine power plant suitable for one engine inoperative flight procedure training
GB2468686A (en) * 2009-03-18 2010-09-22 Weston Aerospace Ltd System and method for detecting abnormal movement in a gas turbine shaft
US9169742B2 (en) * 2010-02-26 2015-10-27 Pratt & Whitney Canada Corp. Electronic shaft shear detection conditioning circuit
GB2488805A (en) * 2011-03-09 2012-09-12 Rolls Royce Plc Shaft break detection
FR2974841B1 (fr) * 2011-05-04 2013-06-07 Snecma Dispositif d'etancheite pour distributeur de turbine de turbomachine
US8864446B2 (en) * 2011-05-23 2014-10-21 Siemens Energy, Inc. Wear pin gap closure detection system for gas turbine engine
US8505364B2 (en) 2011-11-04 2013-08-13 General Electric Company Systems and methods for use in monitoring operation of a rotating component
US10167784B2 (en) 2012-10-26 2019-01-01 Pratt & Whitney Canada Corp. System for detecting shaft shear event
DE102013213386B3 (de) 2013-07-09 2014-08-14 MTU Aero Engines AG Strömungsmaschinen-Keramikbauteil
GB2540784A (en) * 2015-07-27 2017-02-01 Weston Aerospace Ltd Magnetic sensor system for detecting abnormal movement in a gas turbine shaft
US10113937B2 (en) 2017-03-03 2018-10-30 Siemens Energy, Inc. System and method for monitoring hook wear in a gas turbine engine
GB2583078B (en) * 2019-04-09 2022-10-05 Weston Aerospace Ltd System for detecting abnormal movement of a shaft in a gas turbine engine
US11504813B2 (en) 2020-05-18 2022-11-22 Rolls-Royce Plc Methods for health monitoring of ceramic matrix composite components in gas turbine engines
US11618580B2 (en) 2020-08-31 2023-04-04 General Electric Company Hybrid electric aircraft engine
CN121576345A (zh) * 2026-01-23 2026-02-27 中国航发商用航空发动机有限责任公司 航空发动机、轴及针对轴断裂的超转保护装置

Family Cites Families (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2815818A (en) * 1957-12-10 Certificate of correction
US1326867A (en) * 1918-12-06 1919-12-30 Gen Electric Elastic-fluid turbine.
US2977758A (en) * 1955-02-18 1961-04-04 Rolls Royce Propeller driving gas-turbine engines
GB903945A (en) 1957-10-29 1962-08-22 Rolls Royce Improvements in or relating to gas-turbine engines
GB982292A (en) 1960-06-30 1965-02-03 Fairfield Shipbuilding & Engin Trip gear for turbines
US3159166A (en) * 1961-10-16 1964-12-01 Gen Motors Corp Engine safety control
DE2062047A1 (de) 1970-12-16 1972-07-06 Motoren Turbinen Union Warnvorrichtung
DE1915930B2 (de) 1968-04-03 1971-06-09 Motoren und Turbinen Union München GmbH, 8000 München Vorrichtung an tirbomaschinen zum fruehzeitigen erkennen von schaufelschaeden
US3696612A (en) * 1970-12-30 1972-10-10 Westinghouse Electric Corp Fuel pump system for gas turbines
GB1443333A (en) * 1972-08-12 1976-07-21 Mtu Muenchen Gmbh Aircraft having apparatus for augmenting the lift of the aircraft
US3989408A (en) * 1974-05-20 1976-11-02 Westinghouse Electric Corporation Positioning device for a turbine rotor position sensor
JPS5274737A (en) * 1975-12-19 1977-06-23 Hitachi Ltd Operation stopper of hydraulical machinery
GB2002857A (en) 1977-08-16 1979-02-28 Rolls Royce Means for detecting relative movement between parts of machines
US4406117A (en) * 1979-10-26 1983-09-27 General Electric Company Cyclic load duty control for gas turbine
GB2124788B (en) * 1982-06-30 1986-05-21 Rolls Royce Torque-sensitive control of gas turbines
US4498291A (en) * 1982-10-06 1985-02-12 Rolls-Royce Limited Turbine overspeed limiter for turbomachines
JPH03121219A (ja) 1989-10-03 1991-05-23 Mitsubishi Heavy Ind Ltd エンジンの緊急停止装置
US5301499A (en) * 1990-06-28 1994-04-12 General Electric Company Overspeed anticipation and control system for single shaft combined cycle gas and steam turbine unit
US5363317A (en) * 1992-10-29 1994-11-08 United Technologies Corporation Engine failure monitor for a multi-engine aircraft having partial engine failure and driveshaft failure detection
RU2086779C1 (ru) * 1993-10-21 1997-08-10 Омское моторостроительное конструкторское бюро Устройство защиты газотурбинного двигателя
US5411364A (en) * 1993-12-22 1995-05-02 Allied-Signal Inc. Gas turbine engine failure detection system
DE19524992C1 (de) 1995-07-08 1996-08-08 Mtu Muenchen Gmbh Regelung eines Wellentriebwerks mit einem Mikrosteuergerät
DE19727296A1 (de) * 1997-06-27 1999-01-07 Mtu Muenchen Gmbh Einrichtung zur Notabschaltung einer Gasturbine
DE19857552A1 (de) * 1998-12-14 2000-06-15 Rolls Royce Deutschland Verfahren zum Erkennen eines Wellenbruches in einer Strömungskraftmaschine
US6546735B1 (en) * 2001-03-07 2003-04-15 General Electric Company Methods and apparatus for operating turbine engines using rotor temperature sensors
RU2187008C1 (ru) * 2001-05-16 2002-08-10 Общевойсковая Академия Вооруженных Сил Российской Федерации Устройство для предохранения от поломок силовой турбины газотурбинного двигателя
US6607349B2 (en) * 2001-11-14 2003-08-19 Honeywell International, Inc. Gas turbine engine broken shaft detection system
DE10310900A1 (de) * 2003-03-13 2004-09-23 Rolls-Royce Deutschland Ltd & Co Kg Elekronisches Sicherheitssystem zur Vermeidung eines Überdrehzahlzustandes bei einem Wellenbruch
US7043896B2 (en) * 2003-11-21 2006-05-16 Pratt & Whitney Canada Corp. Method and apparatus for controlling fuel flow to an engine
DE102004026366A1 (de) * 2004-05-29 2005-12-15 Mtu Aero Engines Gmbh Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine
DE102004047892A1 (de) * 2004-10-01 2006-04-06 Mtu Aero Engines Gmbh Gasturbine und Verfahren zum Abschalten einer Gasturbine bei Identifikation eines Wellenbruchs
US7207768B2 (en) * 2005-01-15 2007-04-24 Siemens Power Generation, Inc. Warning system for turbine component contact

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2006005319A3 *

Also Published As

Publication number Publication date
RU2006116454A (ru) 2008-09-27
DE102004033924A1 (de) 2006-02-09
WO2006005319A2 (fr) 2006-01-19
EP1664490B1 (fr) 2007-10-24
US20070160457A1 (en) 2007-07-12
US7758301B2 (en) 2010-07-20
DE502005001773D1 (de) 2007-12-06
RU2377420C2 (ru) 2009-12-27
WO2006005319A3 (fr) 2006-02-23

Similar Documents

Publication Publication Date Title
EP1664490B1 (fr) Dispositif pour detecter une rupture d'arbre sur une turbine a gaz et turbine a gaz
DE602004002049T2 (de) Niederdruck-Turbine einer Turbomaschine
EP1483482A1 (fr) Fixation d'une aube directrice dans le canal d'ecoulement d'une turbine a gaz d'avion
EP3184754B1 (fr) Système de détection et procédé de mesure d'une turbomachine
DE102005048814A1 (de) Verfahren und Vorrichtung zur Montage von Gasturbinen
EP1759092B1 (fr) Dispositif de detection d'une rupture d'arbre sur une turbine a gaz et turbine a gaz
DE69913625T2 (de) Gasturbine
DE102007050916A1 (de) Verfahren und Vorrichtung zum Zusammenbau von Gasturbinen-Triebwerken
CH698497B1 (de) Strömungsmaschine mit radial durchströmtem Verdichterrad und mit Halteeinrichtung.
EP0806547A1 (fr) Turbine axiale pour turbocompresseurs
EP0999349A2 (fr) Turbine axiale
EP2129875B1 (fr) Turbomachine avec controle de jeu actif
EP2526263B1 (fr) Système de boîtier pour une turbomachine axiale
EP2611992B1 (fr) Structure de carter d'une turbomachine
EP3176386B1 (fr) Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés
EP1001139A1 (fr) Dispositif d'étanchéité pour les extrémités des aubes de turbine
EP1922472B1 (fr) Turbine a gaz pourvue d'un dispositif de detection d'une rupture de l'arbre
EP2770191A2 (fr) Turbine à gaz d'aéronef dotée d'un premier arbre rotatif
EP1794417B1 (fr) Turbine a gaz et procede pour interrompre le fonctionnement d'une turbine a gaz lors de l'identification de la rupture d'un arbre
DE102019204507A1 (de) Gleitlagervorrichtung, ein Verfahren zum Betrieb einer Gleitlagervorrichtung und ein Gasturbinentriebwerk
DE102009009079B4 (de) Axialströmungsmaschine
DE102006017790B3 (de) Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine
DE102016015296A1 (de) Turbine für einen Abgasturbolader
EP1657404A1 (fr) Rotor d'une turbomachine, notamment rotor d'une turbine à gaz
DE102023118123B4 (de) Turbine und Turbolader mit einer Turbine

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: 20060126

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): DE FR GB

R17D Deferred search report published (corrected)

Effective date: 20060223

17Q First examination report despatched

Effective date: 20060929

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

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

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 502005001773

Country of ref document: DE

Date of ref document: 20071206

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20071115

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20080725

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20190724

Year of fee payment: 15

Ref country code: DE

Payment date: 20190723

Year of fee payment: 15

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20190725

Year of fee payment: 15

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502005001773

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20200707

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200707

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210202