EP2007971A1 - Dispositif de détection de rupture d'arbre d'une turbine à gaz et turbine à gaz - Google Patents

Dispositif de détection de rupture d'arbre d'une turbine à gaz et turbine à gaz

Info

Publication number
EP2007971A1
EP2007971A1 EP07722167A EP07722167A EP2007971A1 EP 2007971 A1 EP2007971 A1 EP 2007971A1 EP 07722167 A EP07722167 A EP 07722167A EP 07722167 A EP07722167 A EP 07722167A EP 2007971 A1 EP2007971 A1 EP 2007971A1
Authority
EP
European Patent Office
Prior art keywords
turbine
rotor
sensor element
stator
flow direction
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Withdrawn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
EP07722167A
Other languages
German (de)
English (en)
Inventor
Alastair Mcintosh
Christopher Bilson
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.)
Rolls Royce Deutschland Ltd and Co KG
MTU Aero Engines AG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG, MTU Aero Engines GmbH filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2007971A1 publication Critical patent/EP2007971A1/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Withdrawn legal-status Critical Current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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/90—Braking

Definitions

  • the invention relates to a device for detecting a shaft fracture on a gas turbine, in particular on a gas turbine aircraft engine. 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 by a respective shaft, wherein the three shafts surround each other concentrically and are thus interleaved.
  • the intermediate-pressure compressor of the medium-pressure turbine can no longer extract any work or power, which can then lead to an overspeed at the medium-pressure turbine.
  • Such 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, prepare especially the detection of a shaft break of the middle wave, which couples the medium-pressure turbine with the medium-pressure compressor, difficulties.
  • a similar problem also arises with stationary gas turbines.
  • a device for detecting a shaft fracture on a gas turbine in which between the last seen in the flow direction, rotor side blade ring of a first turbine and a flow direction in the first, stator side vane ring of a second turbine radially inside an actuating element is arranged, which cooperates with a transmission element which extends in the radial direction through the flow direction in the first stator-side vane ring of the second turbine.
  • 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 fracture on a gas turbine in the sense of claim 1.
  • a device for detecting a shaft fracture on a rotor of a turbine of a gas turbine is proposed, wherein downstream of the turbine at least one stator-side sensor element is positioned, and wherein at a shaft break of the rotor of the turbine, a radially inner portion of a last seen in the flow direction, Rotor-side blade ring of the turbine with the or each sensor element directly or directly cooperates to generate a wave breaking, corresponding electrical signal.
  • the gas turbine according to the invention is defined in 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 according to a preferred embodiment of the invention.
  • FIG. 1 shows a section of a gas turbine according to the invention, namely an aircraft engine, 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 downstream section of a rotor blade 12 of the last rotor blade ring viewed in the flow direction (arrow 13) the medium-pressure turbine 10 shown.
  • a guide vane 14 of the first vane ring of the low-pressure turbine 11 and a housing section 15 seen in the flow direction (arrow 13) is shown.
  • the first or leading vane ring of the low-pressure turbine 11 seen in the flow direction accordingly adjoins the last or rearmost blade ring of the medium-pressure turbine 10, as seen in the flow direction.
  • a high pressure turbine is positioned upstream of the medium pressure turbine 10.
  • the rotors of high-pressure turbine and high-pressure compressor, medium-pressure turbine and medium-pressure compressor and low-pressure turbine and low-pressure compressor connected by one shaft these three shafts surround each other concentrically and thus interleaved are.
  • At least one sensor element 16 is positioned in the area of the first stator-side vane ring of the low-pressure turbine 11, as seen in the flow direction.
  • the or each sensor element 16 acts to detect a shaft fracture with a radially inner portion 17 of seen in the flow direction (arrow 13), the last rotor side blade ring of the intermediate-pressure turbine 10 such that at a shaft break seen in the flow direction rearmost or last blade ring of the medium-pressure turbine 10th with the radially inner portion 17, the sensor element 16 directly or directly contacted.
  • the or each sensor element 16 is preferably formed as an electrical conductor, which is severed at a shaft break from the radially inner portion 17 of the last seen in the flow direction of the rotor blade ring of the intermediate-pressure turbine 10 so as to generate a corresponding to the shaft breakage electrical signal and to a non-illustrated Transfer switching element.
  • the or each trained as a conductor sensor element 16 is thereby severed by the radially inner portion 17 of the last seen in the flow direction of the rotor blade ring of the central pressure turbine 10.
  • the section 17 is designed as a flow-projecting projection of a blade platform 18 of the rotor blades 12 of the last rotor blade ring of the medium-pressure turbine 10, viewed in the direction of flow.
  • the sensor element 16 shown in Fig. 1 is guided in a recess formed as a bore 19 of a stator vane 14 of the flow direction forermost guide vane ring of the low-pressure turbine 11, wherein the bore 19 extends substantially in the radial direction of the vane 14 and the guide vane 14 in a straight line penetrates.
  • the sensor 16 can be inserted from the outside into the bore 19 of the guide blade 14 and can be brought out of the bore 19 for maintenance purposes or cleaning purposes.
  • the sensor element 16 thus forms a line replaceable unit, which can be uninstalled for maintenance of the gas turbine and then reinstalled without disassembly of the gas turbine.
  • the sensor element 16 extends into a radially inner region of a flow channel, which is formed between the last rotor-side blade ring of the medium-pressure turbine 10 and the first guide blade ring of the low-pressure turbine 11 viewed in the flow direction.
  • a section 21 radially adjoining this section 20 of the sensor element 16 and a section 22 radially adjoining this section 20 of the sensor element 16 are guided in the bore 19 of the guide blade 14 and accordingly sheathed by the vane 14 and thus protected. This ensures that when, in the event of a shaft break, the section 17 of the rotor blade 12 strikes the section 20 of the sensor element 16, this section 20 of the sensor element 16 is not merely bent but severed by the section 17 of the rotor blade 12.
  • the or each sensor element 16 is preferably designed as an electrical conductor, wherein, according to a particularly preferred development of the present invention, the or each sensor element 16 is designed as a thermocouple.
  • thermocouples are resistant to oxidation, which is advantageous in particular with regard to the section 20 of the sensor element 16, which is uncoated or unprotected in the flow channel.
  • a shaft break in particular of a low-pressure turbine, can be detected by the fact that, if such a shaft break occurs, the last rotor-side rotor blade of the medium-pressure turbine 10, viewed in the direction of flow, projects the section through the section 17 projecting in the direction of flow 20 of the sensor element 16 is severed.
  • a corresponding signal indicative of a shaft break is transmitted from the sensor element 16 to a control device, not shown, which, depending on this, interrupts a fuel supply to a combustion chamber of the gas turbine.
  • a device for detecting a shaft fracture on a rotor of a gas turbine wherein a radially inner portion of a seen in the flow direction last blade ring of the turbine, which is connected to the shaft to be monitored with respect to shaft shaft, cooperating with at least one sensor element which is assigned to a stator, in particular a first vane ring of a turbine positioned downstream in the flow direction.
  • the or each sensor element is at a shaft break from the protruding in the flow direction portion of the last seen in the flow direction.
  • the rotor blade ring of the turbine which is connected to the shaft to be monitored with respect to the wave breaking through or severed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Measuring Fluid Pressure (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un dispositif de détection d'une rupture d'un arbre au niveau d'un rotor d'une turbine (10), au moins un élément de détection (16) côté stator étant positionné en aval de la turbine (10), en particulier dans la zone d'une couronne directrice côté stator d'une autre turbine (11). En en cas de rupture d'arbre du rotor de la turbine (10), un segment (17) situé radialement à l'intérieur d'une dernière couronne d'aubes mobiles côté rotor, vu dans le sens du courant, coopère directement et/ou instantanément avec le ou chacun des éléments de détection (16), afin de générer un signal électrique correspondant à la rupture de l'arbre.
EP07722167A 2006-04-15 2007-04-04 Dispositif de détection de rupture d'arbre d'une turbine à gaz et turbine à gaz Withdrawn EP2007971A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006017790A DE102006017790B3 (de) 2006-04-15 2006-04-15 Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine
PCT/DE2007/000609 WO2007118452A1 (fr) 2006-04-15 2007-04-04 Dispositif de détection de rupture d'arbre d'une turbine à gaz et turbine à gaz

Publications (1)

Publication Number Publication Date
EP2007971A1 true EP2007971A1 (fr) 2008-12-31

Family

ID=38219994

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07722167A Withdrawn EP2007971A1 (fr) 2006-04-15 2007-04-04 Dispositif de détection de rupture d'arbre d'une turbine à gaz et turbine à gaz

Country Status (4)

Country Link
US (1) US8568087B2 (fr)
EP (1) EP2007971A1 (fr)
DE (1) DE102006017790B3 (fr)
WO (1) WO2007118452A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10316689B2 (en) 2016-08-22 2019-06-11 Rolls-Royce Corporation Gas turbine engine health monitoring system with shaft-twist sensors
US20260092534A1 (en) * 2024-09-30 2026-04-02 Rtx Corporation Gas turbine engine with inspection port and method for using the same

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1326867A (en) * 1918-12-06 1919-12-30 Gen Electric Elastic-fluid turbine.
DE1227704B (de) * 1959-08-21 1966-10-27 Licentia Gmbh Einrichtung zum Ausloesen eines Druckimpulses beim UEberschreiten der hoechstzulaessigen Lageaenderung von Maschinenteilen
SU1229563A1 (ru) * 1983-12-30 1986-05-07 Казанский компрессорный завод Сигнализатор перемещени ротора компрессора
JPH03121219A (ja) * 1989-10-03 1991-05-23 Mitsubishi Heavy Ind Ltd エンジンの緊急停止装置
US5411364A (en) * 1993-12-22 1995-05-02 Allied-Signal Inc. Gas turbine engine failure detection system
DE19727296A1 (de) * 1997-06-27 1999-01-07 Mtu Muenchen Gmbh Einrichtung zur Notabschaltung einer Gasturbine
US6179560B1 (en) * 1998-12-16 2001-01-30 United Technologies Corporation Turbomachinery module with improved maintainability
US6607349B2 (en) * 2001-11-14 2003-08-19 Honeywell International, Inc. Gas turbine engine broken shaft detection system
US20050198967A1 (en) * 2002-09-23 2005-09-15 Siemens Westinghouse Power Corp. Smart component for use in an operating environment
US6962043B2 (en) * 2003-01-30 2005-11-08 General Electric Company Method and apparatus for monitoring the performance of a gas turbine system
DE10310900A1 (de) * 2003-03-13 2004-09-23 Rolls-Royce Deutschland Ltd & Co Kg Elekronisches Sicherheitssystem zur Vermeidung eines Überdrehzahlzustandes bei einem Wellenbruch
DE102004026366A1 (de) * 2004-05-29 2005-12-15 Mtu Aero Engines Gmbh Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine
DE102004033924A1 (de) * 2004-07-14 2006-02-09 Mtu Aero Engines Gmbh Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2007118452A1 *

Also Published As

Publication number Publication date
DE102006017790B3 (de) 2007-07-26
WO2007118452A1 (fr) 2007-10-25
US20090148270A1 (en) 2009-06-11
US8568087B2 (en) 2013-10-29

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