EP1664490A2 - Einrichtung zur detektion eines wellenbruchs an einer gasturbine sowie gasturbine - Google Patents
Einrichtung zur detektion eines wellenbruchs an einer gasturbine sowie gasturbineInfo
- 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
Links
- 238000007789 sealing Methods 0.000 claims description 9
- 238000002485 combustion reaction Methods 0.000 claims description 7
- 241000937413 Axia Species 0.000 claims 2
- 238000010008 shearing Methods 0.000 claims 2
- 235000008694 Humulus lupulus Nutrition 0.000 claims 1
- 244000025221 Humulus lupulus Species 0.000 claims 1
- 238000005056 compaction Methods 0.000 claims 1
- 238000001514 detection method Methods 0.000 description 4
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 239000000919 ceramic Substances 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
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
Description
Claims
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 (de) | 2004-07-14 | 2005-07-07 | Einrichtung zur detektion eines wellenbruchs an einer gasturbine sowie gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1664490A2 true EP1664490A2 (de) | 2006-06-07 |
EP1664490B1 EP1664490B1 (de) | 2007-10-24 |
Family
ID=35458000
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05766945A Expired - Fee Related EP1664490B1 (de) | 2004-07-14 | 2005-07-07 | Einrichtung zur detektion eines wellenbruchs an einer gasturbine sowie gasturbine |
Country Status (5)
Country | Link |
---|---|
US (1) | US7758301B2 (de) |
EP (1) | EP1664490B1 (de) |
DE (2) | DE102004033924A1 (de) |
RU (1) | RU2377420C2 (de) |
WO (1) | WO2006005319A2 (de) |
Families Citing this family (17)
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 |
Family Cites Families (30)
Publication number | Priority date | Publication date | Assignee | Title |
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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 |
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 |
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 |
-
2004
- 2004-07-14 DE DE102004033924A patent/DE102004033924A1/de not_active Withdrawn
-
2005
- 2005-07-07 RU RU2006116454/06A patent/RU2377420C2/ru not_active IP Right Cessation
- 2005-07-07 DE DE502005001773T patent/DE502005001773D1/de active Active
- 2005-07-07 US US10/587,345 patent/US7758301B2/en not_active Expired - Fee Related
- 2005-07-07 WO PCT/DE2005/001206 patent/WO2006005319A2/de active IP Right Grant
- 2005-07-07 EP EP05766945A patent/EP1664490B1/de not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2006005319A3 * |
Also Published As
Publication number | Publication date |
---|---|
WO2006005319A3 (de) | 2006-02-23 |
EP1664490B1 (de) | 2007-10-24 |
US20070160457A1 (en) | 2007-07-12 |
DE502005001773D1 (de) | 2007-12-06 |
US7758301B2 (en) | 2010-07-20 |
WO2006005319A2 (de) | 2006-01-19 |
DE102004033924A1 (de) | 2006-02-09 |
RU2377420C2 (ru) | 2009-12-27 |
RU2006116454A (ru) | 2008-09-27 |
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