EP1457643B1 - Système électronique de contrôle pour éviter une condition de survitesse due à la rupture de l'arbre moteur - Google Patents

Système électronique de contrôle pour éviter une condition de survitesse due à la rupture de l'arbre moteur Download PDF

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Publication number
EP1457643B1
EP1457643B1 EP04090043A EP04090043A EP1457643B1 EP 1457643 B1 EP1457643 B1 EP 1457643B1 EP 04090043 A EP04090043 A EP 04090043A EP 04090043 A EP04090043 A EP 04090043A EP 1457643 B1 EP1457643 B1 EP 1457643B1
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EP
European Patent Office
Prior art keywords
shaft
light guide
safety system
measuring
accordance
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.)
Expired - Lifetime
Application number
EP04090043A
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German (de)
English (en)
Other versions
EP1457643A2 (fr
EP1457643A3 (fr
Inventor
Detlef Rensch
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
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Rolls Royce Deutschland Ltd and Co KG
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Publication date
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Publication of EP1457643A3 publication Critical patent/EP1457643A3/fr
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Publication of EP1457643B1 publication Critical patent/EP1457643B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/09—Purpose of the control system to cope with emergencies
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/09—Purpose of the control system to cope with emergencies
    • F05D2270/091—Purpose of the control system to cope with emergencies in particular sudden load loss
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments

Definitions

  • the invention relates to an electronic safety system for preventing an overspeed state in a shaft break by detecting the shaft break and then interrupting the further power supply, in a gas turbine engine.
  • the known electro-optical sensor for detecting axial deviations of the turbine of a gas turbine engine from the normal position comprises a pair of optical fibers, which are connected via a fragile element arranged near the rotor. By an axial displacement of the rotor from its normal position, the fragile component is destroyed, thereby breaking the connection with an electronics, so that a signal for indicating a fault is output.
  • inductive sensors are arranged on the drive side (turbine rotor) and driven side (fan) toothed turbine shaft, each generating a number of pulses counted corresponding speed proportional signal.
  • a magnetic fuel valve is actuated and the fuel supply is interrupted, so that the turbine rotor can not be driven further.
  • the invention has for its object to provide a safety system for detecting a shaft fracture and to interrupt the further supply of energy to the drive end of the shaft, which works reliably and wear with low assembly, design and space requirements and ensures short shutdown.
  • the essence of the invention consists in the fixed assignment of a light guide to the circumference of the shaft to be monitored, in the longitudinal direction and with this rotating, as well as connected to a wave break separation of the light guide and the corresponding interruption of the forwarding of the in this way as a measuring element serving light guide at its entrance side light supplied.
  • This interruption is detected by a sensor at the other end of the measuring light guide and transmitted via an evaluation and control electronics used as a signal for the shutdown of the drive power supply.
  • the safety system formed on this basis does not require any cooling devices in the case of the possible external arrangement of the required optical sensors and light sources. Only a small number of simple components is necessary. The assembly, repair and maintenance costs are correspondingly low. Due to the speed of light and the associated rapid detection of a shaft break, short turn-off times for the power supply can be realized.
  • a plurality of measuring optical fibers may be provided, which may also be returned as a loop to the light entrance side.
  • the light source and the sensors can be arranged directly upstream of the measuring optical fiber (s) or can be arranged externally (using additional optical fibers for the supply and removal of the light).
  • the inlet side of the measuring optical fibers can be arranged axially centrally or offset from the center.
  • the light emission can take place in the axial or radial direction and be detected.
  • the additional light guide or the light source for the supply of light may be annular in order to supply light from only one light source to a plurality of measuring light guides arranged in a circular line.
  • the fixed assignment of the measuring light guide to the shaft to be monitored and thus the rotation of the measuring light guide is realized together with the shaft by a coaxial with the shaft, at both ends connected to this measuring sleeve.
  • the measuring sleeve is also destroyed, thereby severing the measuring light guide. That's because of Missing light line through the measuring optical fiber at the optical transmitter registered signal is used after appropriate evaluation in the transmitter to control a shutdown mechanism for the drive side of the shaft.
  • the measuring sleeve consists of an inner tube and an outer tube.
  • the inner tube extending in the longitudinal direction retaining grooves for receiving the measuring optical fibers, so that in a connected to a shaft breakage of the measuring sleeve and the measuring optical fiber is severed immediately.
  • the outer tube whose strength is higher than that of the inner tube, serves to support the measuring optical fiber / s and the inner tube.
  • the measuring sleeve 4 consists of an inner tube 7 and an outer tube 8, which are closed at both end faces in each case by a bottom plate 9a, b and 10a, b.
  • the inner tube 7 In the outer peripheral surface of the inner tube 7 are two opposite, extending in the longitudinal direction of the measuring sleeve 4 retaining grooves 11, 12, in which a measuring optical fiber 13 - is flush with the surface of the inner tube 7 - inserted.
  • the outer tube (support tube) 8 supports the measuring optical fiber 13 against the high centrifugal forces to the outside and fixes it radially in the retaining grooves 11, 12.
  • the measuring optical fiber 13 is thus embedded in the peripheral wall of the measuring sleeve 4.
  • the outer tube 8, which serves to accommodate the centrifugal forces and the centering of the measuring sleeve 4, has a strength corresponding to the prevailing force effects.
  • the inner tube 7, which functions as a predetermined breaking tube consists of a less strong, easily breaking material.
  • the measuring optical fiber 13 starting from a central input bore 14 in the rear floor panel 9a, first between the two rear floor panels 9a and 10a, then in the lower retaining groove 12, then between the two front floor panels 9b and 10b and finally back to the exit side in the upper retaining groove 11 to terminate in an exit bore 15 at the outer edge of the rear floor panel 9a.
  • the light source 18 and the optical sensor 19 may also be arranged directly behind the input or output bores 14, 15 for the measuring optical waveguide 13, in which case corresponding cooling devices may be provided have to.
  • the optical sensor 19 is connected to evaluation electronics 20 and an electronic controller 21, via which a fuel shut-off valve 22 integrated in the fuel supply is actuated on the basis of the signals received by the optical sensor 19.
  • first additional light guide 16 About the light emitting end of the centrally located input bore 14 lying light supply cable (first additional light guide 16) light is constantly passed through the measuring light guide 13 and received as a repetitive light pulse due to the rotation of the measuring sleeve 4 at the light exit side (output hole 15) .
  • the measuring sleeve 4 which is connected at both ends to the latter and otherwise arranged with play in the low-pressure turbine shaft 1, preferably breaks down its inner tube 7, which has a low strength (predetermined breaking tube). Due to the fixation of the measuring light guide 13 in the retaining groove 11, 12 this is also severed quickly and the light beam interrupted.
  • the light supply interruption registered by the optical sensor 19 serves as a signal to the transmitter 20 and the electronic controller 21 to indicate a rupture of the shaft and to stop the supply of fuel to the fuel shut-off valve 22 so as not to further accelerate the low-pressure turbine shaft 1 and resulting from an overspeed restrict or prevent dangerous consequences.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Monitoring And Testing Of Nuclear Reactors (AREA)
  • Optical Transform (AREA)
  • Length Measuring Devices By Optical Means (AREA)

Claims (11)

  1. Système de sécurité électronique combiné à un arbre et destiné à être mis en oeuvre dans une turbine à gaz pour éviter un état de surrégime en cas de rupture d'arbre par détection de la rupture d'arbre suivie de l'interruption de l'alimentation en énergie, caractérisé par au moins un guide de lumière mesureur (13) s'étendant à l'état monté dans le sens longitudinal de l'arbre (1), associé rigidement à l'arbre et tournant avec lui, auquel sont associés une source de lumière (18) du côté d'entrée et un capteur optique (19) d'un côté de sortie axial ou radial de la lumière, sachant qu'une séparation du/des guide(s) de lumière mesureur (13) lié(s) à l'arbre (1) due à une rupture d'arbre et que la réception de signaux lumineux modifiés au capteur optique (19) provoquent la détection de la rupture d'arbre par l'intermédiaire d'une unité électronique d'interprétation et de commande (20, 21), ainsi que l'interruption de l'alimentation en énergie du côté de l'entraînement de l'arbre (1) pendant le fonctionnement de la turbine à gaz.
  2. Système de sécurité selon la revendication n° 1, caractérisé en ce que la source de lumière (18) et le capteur (19) sont directement associés au côté d'entrée de la lumière ou au côté de sortie de la lumière du guide de lumière (13).
  3. Système de sécurité selon la revendication n° 1, caractérisé en ce que la source de lumière (18) et le capteur (19) sont placés à l'extérieur et respectivement associés, par l'intermédiaire de guides de lumière supplémentaires (16, 17), au(x) guide(s) de lumière mesureur(s) (13) couplé(s) à l'arbre (1).
  4. Système de sécurité selon la revendication n° 1, caractérisé en ce que le côté d'entrée de l'au moins un guide de lumière mesureur (13) est situé dans l'axe de l'arbre (1), alors que le(s) guide(s) de lumière mesureur(s) (13) et son/leurs côté(s) de sortie sont disposés de manière décentrée en analogie avec la circonférence de l'arbre.
  5. Système de sécurité selon la revendication n° 1, caractérisé en ce que le côté d'entrée et le côté de sortie de l'au moins un guide de lumière mesureur (13) sont disposés de manière décentrée en analogie avec la circonférence de l'arbre.
  6. Système de sécurité selon la revendication n° 5, caractérisé en ce qu'un guide de lumière annulaire ou une source de lumière annulaire est disposé(e) pour acheminer la lumière vers les guides de lumière (13).
  7. Système de sécurité selon la revendication n° 6, caractérisé en ce que le guide de lumière annulaire est directement relié aux guides de lumière mesureurs (13).
  8. Système de sécurité selon la revendication n° 1, caractérisé en ce que l'au moins un guide de lumière mesureur (13) a la forme d'une boucle, sachant que les côtés d'entrée et de sortie se trouvent à la même extrémité de l'arbre.
  9. Système de sécurité selon une des revendications n° 1 à 8, caractérisé en ce qu'à l'arbre (1) est associée une douille de mesure (4) fixée aux extrémités de l'arbre sur ou dans laquelle est maintenu l'au moins un guide de lumière mesureur (13).
  10. Système de sécurité selon la revendication n° 9, caractérisé en ce que la douille de mesure (4) comprend un tube intérieur (7) avec au moins une encoche d'arrêt (11, 12) formée sur sa circonférence extérieure et dans laquelle est maintenu au moins un guide de lumière mesureur (13), et un tube extérieur (8) entourant le tube intérieur (7) pour supporter radialement et, en interaction avec l'encoche d'arrêt, pour supporter dans le sens circonférentiel le(s) guide(s) de lumière mesureur(s) (13).
  11. Système de sécurité selon la revendication n° 10, caractérisé en ce que le tube intérieur (7) faisant office de tube destiné à la rupture est constitué d'un matériau de faible degré de résistance.
EP04090043A 2003-03-13 2004-02-11 Système électronique de contrôle pour éviter une condition de survitesse due à la rupture de l'arbre moteur Expired - Lifetime EP1457643B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10310900A DE10310900A1 (de) 2003-03-13 2003-03-13 Elekronisches Sicherheitssystem zur Vermeidung eines Überdrehzahlzustandes bei einem Wellenbruch
DE10310900 2003-03-13

Publications (3)

Publication Number Publication Date
EP1457643A2 EP1457643A2 (fr) 2004-09-15
EP1457643A3 EP1457643A3 (fr) 2007-03-21
EP1457643B1 true EP1457643B1 (fr) 2009-07-08

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EP04090043A Expired - Lifetime EP1457643B1 (fr) 2003-03-13 2004-02-11 Système électronique de contrôle pour éviter une condition de survitesse due à la rupture de l'arbre moteur

Country Status (3)

Country Link
US (1) US7002172B2 (fr)
EP (1) EP1457643B1 (fr)
DE (2) DE10310900A1 (fr)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004009595A1 (de) * 2004-02-27 2005-09-15 Mtu Aero Engines Gmbh Verfahren und Vorrichtung zur Identifikation eines Wellenbruchs und/oder einer Überdrehzahl an einer Gasturbine
EP1727971B1 (fr) * 2004-03-23 2007-10-31 Siemens Aktiengesellschaft Ensemble et procede pour la detection d'un endommagement sur un composant d'une turbomachine
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
DE102004047892A1 (de) 2004-10-01 2006-04-06 Mtu Aero Engines Gmbh Gasturbine und Verfahren zum Abschalten einer Gasturbine bei Identifikation eines Wellenbruchs
DE102005036879A1 (de) * 2005-05-12 2006-11-16 Logos-Innovationen Gmbh Hebevorrichtung mit einer Antriebseinheit zum Heben einer Lastaufnahme
US7536850B2 (en) * 2005-09-27 2009-05-26 Pratt & Whitney Canada Corp. Emergency fuel shutoff system
DE102006017790B3 (de) * 2006-04-15 2007-07-26 Mtu Aero Engines Gmbh Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine
US7581377B2 (en) * 2006-06-14 2009-09-01 Pratt & Whitney Canada Corp. Low-cost frangible cable for gas turbine engine
FR2907839B1 (fr) * 2006-10-25 2011-06-17 Snecma Methode pour reduire la vitesse en cas de rupture d'arbre de turbine de moteur a turbine a gaz
FR2923540B1 (fr) * 2007-11-13 2010-01-29 Snecma Dispositif de detection de rupture d'un arbre de turbomachine
US9169742B2 (en) * 2010-02-26 2015-10-27 Pratt & Whitney Canada Corp. Electronic shaft shear detection conditioning circuit
US10167784B2 (en) 2012-10-26 2019-01-01 Pratt & Whitney Canada Corp. System for detecting shaft shear event
DE102013101791A1 (de) * 2013-02-22 2014-08-28 Rolls-Royce Deutschland Ltd & Co Kg Fluggasturbine mit einer ersten drehbaren Welle
US10316689B2 (en) 2016-08-22 2019-06-11 Rolls-Royce Corporation Gas turbine engine health monitoring system with shaft-twist sensors
DE102017213094A1 (de) * 2017-07-28 2019-01-31 Rolls-Royce Deutschland Ltd & Co Kg Anordnung und Verfahren zur Erkennung eines Wellenbruchs
IT202000028520A1 (it) 2020-11-26 2022-05-26 Ge Avio Srl Sistema e metodo per la mitigazione di velocita' eccessiva di rotore

Family Cites Families (5)

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Publication number Priority date Publication date Assignee Title
US4712372A (en) * 1985-09-18 1987-12-15 Avco Corporation Overspeed system redundancy monitor
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
DE19857552A1 (de) * 1998-12-14 2000-06-15 Rolls Royce Deutschland Verfahren zum Erkennen eines Wellenbruches in einer Strömungskraftmaschine
US6607349B2 (en) * 2001-11-14 2003-08-19 Honeywell International, Inc. Gas turbine engine broken shaft detection system

Also Published As

Publication number Publication date
EP1457643A2 (fr) 2004-09-15
DE502004009705D1 (de) 2009-08-20
DE10310900A1 (de) 2004-09-23
US20050047913A1 (en) 2005-03-03
US7002172B2 (en) 2006-02-21
EP1457643A3 (fr) 2007-03-21

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