EP1847688B1 - Système de détection d'arrêt d'urgence pour une turbine à gaz - Google Patents

Système de détection d'arrêt d'urgence pour une turbine à gaz Download PDF

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Publication number
EP1847688B1
EP1847688B1 EP07004819.4A EP07004819A EP1847688B1 EP 1847688 B1 EP1847688 B1 EP 1847688B1 EP 07004819 A EP07004819 A EP 07004819A EP 1847688 B1 EP1847688 B1 EP 1847688B1
Authority
EP
European Patent Office
Prior art keywords
sensor element
resistors
gas turbine
line
emergency shutdown
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 - Fee Related
Application number
EP07004819.4A
Other languages
German (de)
English (en)
Other versions
EP1847688A3 (fr
EP1847688A2 (fr
Inventor
Gustavo Argüello
Clemens Chaskel
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
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1847688A2 publication Critical patent/EP1847688A2/fr
Publication of EP1847688A3 publication Critical patent/EP1847688A3/fr
Application granted granted Critical
Publication of EP1847688B1 publication Critical patent/EP1847688B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D21/06—Shutting-down
    • 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
    • F01D17/02—Arrangement of sensing elements
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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

Definitions

  • the invention relates to a Notabschaltdetektorvortechnische for a gas turbine, in particular for a Notabschaltdetektorvortechnische, which responds to a shaft fracture of a gas turbine to interrupt the fuel supply in such an emergency or to control the turbine control accordingly.
  • the DE 197 27 296 A1 shows switching elements which are actuated by an axial displacement of a broken shaft.
  • the invention has for its object to provide a Notabschaltdetektorvortechnische for a gas turbine, which has a high level of reliability with a simple design and simple, cost-effective manufacturability.
  • the emergency shutdown detector device is based on the basic idea by means of at least one resistor To provide a circuit which not only has an infinitely large or infinitely small electrical resistance (depending on whether an electrical line is interrupted or has contact), but which has a defined electrical resistance, which allows a definitive statement about whether a there is another electrical defect of the emergency shutdown detector device, the sensor element or the associated control, or whether a shaft break has occurred in which the sensor element has been mechanically severed.
  • the controller can easily see that there is no break in the shaft and thus no separation of the free end region of the sensor element. If the supply lines are interrupted, for example due to contact difficulties or other defects, an infinite resistance would result. This too can not be an indication of a wave breakage.
  • the inventive design is thus ensured that there is a defined resistance in the overall circuit, which can only occur when a shaft break occurs and according to the free end of the sensor element is separated or sheared off.
  • Other disturbances for example, a short circuit in the region of the sensor element, lead to changed resistance values, which specifically correspond to the resistors used and thus can be detected by the controller.
  • the embodiment according to the invention also has the advantage that, given temperature changes in the region of the resistors, which may occur, for example, in a range from -55 ° C. to + 260 ° C., a defined mode of operation results. Since the resistivity values of the individual resistors change proportionally to each other during such temperature changes, the specific proportionality or assignment of resistance values described above with different malfunctions or with an actual shaft breakage is still present. In particular when using resistors with standardized temperature coefficients, the device according to the invention thus has the highest degree of operational safety.
  • the Fig. 1 shows a schematic representation of a portion of a gas turbine in section.
  • a sensor element 5 is shown, which is designed in the form of an elongated sensor and has a connection region 6, which can be mounted in the usual way.
  • a separating projection 12 is formed, which is axially displaced at a shaft break and by engaging in the grooves 10, 11 comes into contact with the free end 7 of the sensor element 5 and the tip region separates or shears.
  • the shearing occurs in the area of one in the 3 and 4 schematically shown dividing line 13th
  • the Fig. 3 shows a schematic representation of the electrical circuit of Notabschaltdetektorvoroplasty invention. This includes an already mentioned connection area 6, which is connected via not shown electrical connection elements with a control / regulation. At the connection region 6, the sensor element 5 is fixed, the free end 7 along the dividing line 13 is separable.
  • the two supply lines 3, 4 are electrically connected via a resistor R1.
  • the supply lines 1, 3 are electrically connected via a second electrical resistance R2.
  • the resistors R1 and R2 are arranged in parallel.
  • a resistor R3 is further arranged in series.
  • the embodiment of Fig. 4 differs from the embodiment of Fig. 3 in that the resistor R1 is likewise arranged adjacent to the connection region 6, so that both the supply line 3 and the discharge line 4 each run in a loop like the free end 7 of the sensor element 5. This arrangement is chosen so that all three resistors same thermal Environment have. This results in a further increase in reliability.
  • the reference numeral 14 designates a flange which may be provided for mounting the emergency shutdown detector device or the connection region 6.
  • the total resistance is 1499 ⁇ .
  • an interruption of one of the lines 3 and 4 in the sensor element 5 and in the free end 7 results in a resistance of 2518 ⁇ .
  • a short circuit between the lines 3, 4 results in a resistance of 769 ⁇ .
  • a short circuit between lines 1 and 2 results in a very low resistance ( ⁇ 13 ⁇ ). If one of the lines 1 or 2 breaks, an infinite resistance results.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Investigating Or Analyzing Materials By The Use Of Electric Means (AREA)

Claims (4)

  1. Dispositif de détection d'arrêt d'urgence pour une turbine à gaz comprenant un élément capteur (5) oblong, mécaniquement sectionnable à une extrémité, dans lequel est prévu de manière isolée au moins un câble électrique comprenant une ligne d'arrivée électrique (1, 3) et une ligne de sortie électrique (2, 4) qui sont électriquement interconnectées dans la zone de l'extrémité libre (7) dudit élément capteur (5), caractérisé en ce qu'au moins une résistance électrique (R1 jusqu'à R3) est disposée de telle sorte dans le câble électrique que lors du sectionnement de l'élément capteur (5) une valeur de résistance prédéterminée est obtenue.
  2. Dispositif selon la revendication n° 1, caractérisé en ce qu'une résistance (R3) est disposée en série dans la ligne d'arrivée (1, 3) et qu'en aval deux résistances (R2 et R1), connectées en parallèle, sont prévues, sachant que la ligne d'arrivée (1, 3) et la ligne de sortie (2, 4) sont exclusivement reliées par lesdites deux résistances.
  3. Dispositif selon la revendication n° 2, caractérisé en ce qu'une (R1) des résistances parallèles est disposée dans la zone de l'extrémité libre et mécaniquement sectionnable dudit élément capteur (5) et que les deux autres résistances (R2, R3) sont disposées dans la zone de connexion (6) dudit dispositif.
  4. Dispositif selon la revendication n° 2, caractérisé en ce que toutes les résistances (R1 jusqu'à R3) sont disposées dans la zone de connexion (6) dudit dispositif.
EP07004819.4A 2006-04-05 2007-03-08 Système de détection d'arrêt d'urgence pour une turbine à gaz Expired - Fee Related EP1847688B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006016011A DE102006016011A1 (de) 2006-04-05 2006-04-05 Notabschaltdetektorvorrichtung für eine Gasturbine

Publications (3)

Publication Number Publication Date
EP1847688A2 EP1847688A2 (fr) 2007-10-24
EP1847688A3 EP1847688A3 (fr) 2016-03-23
EP1847688B1 true EP1847688B1 (fr) 2019-05-08

Family

ID=38514390

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07004819.4A Expired - Fee Related EP1847688B1 (fr) 2006-04-05 2007-03-08 Système de détection d'arrêt d'urgence pour une turbine à gaz

Country Status (3)

Country Link
US (1) US7782221B2 (fr)
EP (1) EP1847688B1 (fr)
DE (1) DE102006016011A1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009009079B4 (de) * 2009-02-14 2012-04-26 Man Diesel & Turbo Se Axialströmungsmaschine
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
GB2494703B (en) 2011-09-16 2016-08-03 Weston Aerospace Ltd System and method for detecting abnormal movement in a gas turbine shaft
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
US10190440B2 (en) * 2015-06-10 2019-01-29 Rolls-Royce North American Technologies, Inc. Emergency shut-down detection system for a gas turbine
GB2540784A (en) 2015-07-27 2017-02-01 Weston Aerospace Ltd Magnetic sensor system for detecting abnormal movement in a gas turbine shaft
US11504813B2 (en) 2020-05-18 2022-11-22 Rolls-Royce Plc Methods for health monitoring of ceramic matrix composite components in gas turbine engines

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DE1915930B2 (de) * 1968-04-03 1971-06-09 Motoren und Turbinen Union München GmbH, 8000 München Vorrichtung an tirbomaschinen zum fruehzeitigen erkennen von schaufelschaeden
DE2062047A1 (de) 1970-12-16 1972-07-06 Motoren Turbinen Union Warnvorrichtung
DE3483058D1 (de) * 1983-03-23 1990-10-04 Nippon Steel Corp Verankerungskabel einer struktur.
JPH0355104Y2 (fr) * 1986-07-31 1991-12-06
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US5637794A (en) * 1995-12-22 1997-06-10 Eaton Corporation Resistive brake lining wear and temperature sensing system
US5841617A (en) * 1997-04-07 1998-11-24 Bpw, Inc. Electrical safety device with conductive polymer sensor
DE19727296A1 (de) * 1997-06-27 1999-01-07 Mtu Muenchen Gmbh Einrichtung zur Notabschaltung einer Gasturbine
US6445099B1 (en) * 2000-05-09 2002-09-03 Trw, Inc. Bearing failure detector for electrical generator
US6360850B1 (en) * 2000-07-20 2002-03-26 Dana Corporation Progressive brake lining wear sensor
US7289302B1 (en) * 2001-10-04 2007-10-30 Maxtor Corporation On slider inductors and capacitors to reduce electrostatic discharge damage
US6607349B2 (en) * 2001-11-14 2003-08-19 Honeywell International, Inc. Gas turbine engine broken shaft detection system
DE10210299A1 (de) * 2002-03-08 2003-10-02 Reinhold Ott Sensorelement für eine Überwachungsvorrichtung
CA2409624C (fr) * 2002-10-25 2011-03-29 Intelligent Devices Inc. Systeme electronique de detection de trafiquage
US7873723B2 (en) * 2003-01-30 2011-01-18 Hewlett-Packard Development Company, L.P. Device data
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Also Published As

Publication number Publication date
US20070241921A1 (en) 2007-10-18
EP1847688A3 (fr) 2016-03-23
DE102006016011A1 (de) 2007-10-18
US7782221B2 (en) 2010-08-24
EP1847688A2 (fr) 2007-10-24

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