EP3722563A1 - System zur detektion von anormaler bewegung einer welle in einem gasturbinenmotor - Google Patents

System zur detektion von anormaler bewegung einer welle in einem gasturbinenmotor Download PDF

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Publication number
EP3722563A1
EP3722563A1 EP20165374.8A EP20165374A EP3722563A1 EP 3722563 A1 EP3722563 A1 EP 3722563A1 EP 20165374 A EP20165374 A EP 20165374A EP 3722563 A1 EP3722563 A1 EP 3722563A1
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EP
European Patent Office
Prior art keywords
plunger
fuse
shaft
ceramic
gas turbine
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
EP20165374.8A
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English (en)
French (fr)
Other versions
EP3722563B1 (de
Inventor
Dean Dobson
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.)
Weston Aerospace Ltd
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Weston Aerospace Ltd
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Publication date
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Publication of EP3722563A1 publication Critical patent/EP3722563A1/de
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Publication of EP3722563B1 publication Critical patent/EP3722563B1/de
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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
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • 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
    • F01D21/02—Shutting-down responsive to overspeed
    • 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
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/09—Purpose of the control system to cope with emergencies

Definitions

  • the present invention is concerned with a system for detecting a broken shaft in a gas turbine engine and a detector element for use in such a system.
  • a broken shaft in a gas turbine engine results in the risk of so-called "turbine over-speed".
  • the compressor mass is lost to the rotating system so the shaft and turbine then rotates significantly more quickly.
  • the movement of the turbine can be sufficiently fast to cause the turbine to fly apart and break.
  • Gas turbine engines include a rotating shaft having compressor and/or turbine blades mounted thereon and rotating therewith.
  • Axial movement of the shaft relative to the remainder of the engine is considered to be an abnormal movement and indicative of engine failure (e.g. shaft breakage). Detection of axial movement of the shaft relative to the remainder of the engine can therefore be used to detect engine failure and used to prevent further damage to the engine by activating a shut off of the engine.
  • a shaft links the turbine and compressor. If the shaft is broken, the turbine portion moves backwards because of the effect of combustion gases. The compressor elements would lose power and stop rotating.
  • US 6,607,349 discloses a broken shaft detection system and a method which uses a detector assembly mounted downstream of a power turbine wheel of a gas turbine engine to detect rearward axial motion of the wheel and thereby a broken shaft event.
  • the detector assembly has a plunger positioned to be axially displaced against a metal conductive wire fuse link connected in an electrical circuit.
  • the metal wire link may be broken when the plunger is displaced thereby creating an open circuit that may be detected by a detection and test element.
  • the breaking may be communicated to an over-speed circuit that controls a shut off switch that interrupts fuel flow to the engine.
  • the metal wire link may be connected to the detection and test element by two pairs of parallel wires to facilitate monitoring of circuit function and to detect failures that are not broken shaft event failures.
  • US 2003/0091430 , GB 2,468,686 and WO 99/00585 disclose similar arrangements.
  • the inventor of the subject application has realised arrangements such as those described in US 6,607,349 with a metal wire link forming a fuse element do not always break reliably.
  • the inventor has recognised that the metallic wire element may fail in a ductile manner which decreases the likelihood of the circuit being broken when required.
  • support the metal wire link on an insulating ceramic medium by applying a metallic, electrically conductive track to a ceramic medium. This can create further reliability problems due to the differences in thermal expansion between the metal track and the ceramic on which it is laid.
  • a gas turbine or jet engine is an extremely hot environment (with the temperature of the exhaust gases being perhaps 900 degrees Celsius) and those high temperatures and materials with differing rates of thermal expansion mean that the track may come loose from the supporting ceramic medium.
  • the differential thermal expansion of the different materials mean that a relatively large shaft movement is necessary for breaking of the fuse.
  • shaft movement resulting from shaft breakage may be quite small (of the order of 5 to 7 mm).
  • the claimed invention allows one to produce a more reliable fuse.
  • Reliable fuse performance is very important in a jet engine: accidental breaking of the fuse would cause the engine to switch off unnecessarily; the fuse not breaking on shaft breakage would cause the engine to explode.
  • EP 3 106 626 describes a system in which the fuse link is a solid metal link rather than a wire supported on a ceramic structure. This arrangement, however, continues to have a metal fuse link which will fail in a ductile manner when a breaking load is applied by the plunger. This ductile failure mode means that the fuse link is unlikely to break if subjected to a small displacement. Shaft movement resulting from shaft breakage can be quite small (of the order of 5 to 7 mm).
  • a further problem of metallic fuse links arises from the fact that gas turbines and jet engines, in use, shake and create environment vibration loads which the fuse link must be able to withstand. If the fuse link is metallic it is difficult to design a fuse link which will fail consistently under small plunger displacements but will still withstand the unavoidable environment vibration loads associated with a working gas turbine.
  • the present invention provides a system for detecting abnormal movement of a shaft in a gas turbine engine, the system comprising a detection circuit, the detection circuit including a frangible fuse portion and a plunger connected to or adjacent the frangible fuse portion, wherein the plunger may be displaced as a result of abnormal movement of the gas turbine shaft to break the frangible fuse portion and thereby alter the detection circuit, and wherein the frangible fuse is conductive ceramic.
  • Ceramic materials are usually made by the processing (often by sintering or firing) of powder pre-forms. This means that they also lend themselves easily to being shaped into a designed form which, for example, maximises the likelihood of failure when impacted by a moving plunger.
  • the conductive ceramic is a silicon carbide ceramic or the like.
  • a silicon carbide ceramic has particularly suitable material properties.
  • the plunger is insulating ceramic.
  • an insulating ceramic has particularly suitable material properties. It will also have a very similar rate of thermal expansion to the ceramic fuse link and thereby reduce the strains and stresses that might be created by differential thermal expansion of the adjacent fuse link and plunger components in the hot gas turbine working environment. Ceramic materials are usually made by the processing (often by sintering or firing) of powder pre-forms. This means that they also lend themselves easily to being shaped into a designed form which, for example, maximises the likelihood of failure when impacting a fuse link.
  • the insulating ceramic is an alumina ceramic or the like.
  • an alumina ceramic has particularly suitable material properties.
  • the fuse includes weakened portion or portions to facilitate breaking of the fuse at the weakened portion or portion.
  • the ceramic fuse link can be formed into a shape or shapes which have points or lines of weakness which are designed to fail when impacted by the force of a moving plunger.
  • the weakened portion or portions are surface notches or surface defects.
  • Surface notches and surface defects are easy to introduce accurately into a ceramic component when it is formed.
  • the surface defects might be other materials (e.g. thin wall tubes or other shapes) embedded in the fuse portion.
  • the weakened portion or portions are located in the middle and/or edges of the frangible fuse portion.
  • the plunger is adjacent the frangible fuse and a plunger end portion adjacent the fuse is of narrower cross-section than the remainder of the plunger.
  • a plunger end portion adjacent the fuse is of narrower cross-section than the remainder of the plunger.
  • the plunger end portion is tapered. This a strong and easy to form structure with a narrowing of the plunger towards the fuse link impact point to achieve the advantages discussed above.
  • the plunger end portion is a protrusion from a plunger body. This a strong and easy to form structure with a narrowing of the plunger towards the fuse link impact point to achieve the advantages discussed above.
  • a gas turbine 1 includes a shaft 2 to which are mounted compressor blades 3 and turbine blades 4. This is well-known and standard technology so will not be described in any detail.
  • the system of the subject invention is intended to warn when the shaft 2 breaks. If the shaft were to break along line 5 , the shaft will move to the right (in a rearwards direction through the gas turbine housing) as shown by arrow A in figure 1 .
  • the system comprises a detector assembly 10 which forms part of a detection circuit or circuits.
  • the detector assembly comprises an electrically conductive brittle fuse link 12 that connects two parallel sets of wires 14, 16.
  • the brittle fuse link 12 is a conductive ceramic such as a silicon carbide ceramic (for example that available under the ROCAR registered trade mark).
  • the parallel set of wires connect to a controller (not shown).
  • the controller is able to determine if the electrically conductive ceramic link is intact, as shown in Figure 1a , or if the electrically conductive ceramic link is broken, as shown in Figure 2b , by monitoring the voltages or currents on the parallel wires.
  • the pairs of parallel wires 14, 16 may be split to connect to a second controller (not shown) to provide redundancy.
  • the electrically conductive ceramic link 12 is mounted in the gas turbine engine proximate to a plunger 18.
  • the plunger 18 is mounted adjacent to a shaft disc 20 so that, if the shaft breaks and moves rearward in the engine the shaft disc 20 pushes the plunger 18 against the link 12 thereby breaking the link.
  • the plunger 18 is formed from an electrically insulating ceramic such as an alumina ceramic.
  • the plunger 18 should have a much lower conductivity than the fuse link 12 (perhaps 1/1000 of the fuse link conductivity).
  • a brittle ceramic fuse link means that the fuse link 12 will break cleanly (i.e. total material fracture across a section so that electrical conductivity across the section no longer remains) with a small plunger displacement (1-5 mm of the plunger 18).
  • the controller When the controller detects that the link is broken, it can communicate with an engine shut down circuit to ensure that the fuel supply to the engine is shut off and catastrophic engine over speed is prevented.
  • the detector assembly 10 is fixed to the engine casing 24.
  • the detector may be protected from the harsh environment of the interior of the gas turbine engine by a collapsible cap 25 over the plunger.
  • a shaft disc 20 is illustrated adjacent the plunger 18, with the cover 25 interposed between them. When the shaft disc moves as a result of a shaft breakage, it drives the plunger against the link 12 and thereby breaks the frangible link 12 (see figures 4a and 4b ).
  • a controller 8 that is connected to the detector and can determine when the frangible link 12 has been broken. The controller 8 can then send a signal to an engine shut down circuit as previously described.
  • the surface of the fuse link 12 may include surface defects such as the notches 13 shown in figure 5 .
  • Such notches 13 weaken the ceramic fuse link 12 and reduce the risk of a small movement not breaking the fuse link 12 and hence breaking the detection circuit.
  • Weakened fuse link portions such as the notches 13 may be arranged such that the fuse link 12 is broken by plunger 18 into small pieces which can easily clear or fall away from the fuse area.
  • the notches 13 (or alternative weakened fuse portions) may preferably be located in the middle and/or edges of the frangible fuse link 12.
  • the likelihood of an impact between the plunger 18 and ceramic fuse link 12 resulting in breakage can be improved by having the impact end 19 of the plunger of a narrow cross-section (see figure 6 ).
  • the narrower cross-section may be achieved by, for example, having a plunger impact protrusion 17 on the plunger end surface 21 as shown in figure 6 .
  • Alternatives include a tapered or sharpened plunger end. It can be seen that a system and detector as described can be made in a simple and inexpensive manner and can provide significant reliability improvements over existing systems for detecting a broken shaft in a gas turbine engine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuses (AREA)
  • Testing Of Engines (AREA)
  • Supercharger (AREA)
EP20165374.8A 2019-04-09 2020-03-24 System zur detektion von anormaler bewegung einer welle in einem gasturbinenmotor Active EP3722563B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1905005.3A GB2583078B (en) 2019-04-09 2019-04-09 System for detecting abnormal movement of a shaft in a gas turbine engine

Publications (2)

Publication Number Publication Date
EP3722563A1 true EP3722563A1 (de) 2020-10-14
EP3722563B1 EP3722563B1 (de) 2023-12-27

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP20165374.8A Active EP3722563B1 (de) 2019-04-09 2020-03-24 System zur detektion von anormaler bewegung einer welle in einem gasturbinenmotor

Country Status (4)

Country Link
US (1) US20200325793A1 (de)
EP (1) EP3722563B1 (de)
CA (1) CA3077832A1 (de)
GB (1) GB2583078B (de)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999000585A1 (de) 1997-06-27 1999-01-07 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Einrichtung zur notabschaltung einer gasturbine
US20030091430A1 (en) 2001-11-14 2003-05-15 Honeywell International, Inc Gas turbine engine broken shaft detection system
GB2468686A (en) 2009-03-18 2010-09-22 Weston Aerospace Ltd System and method for detecting abnormal movement in a gas turbine shaft
EP3106626A1 (de) 2015-06-15 2016-12-21 Weston Aerospace Limited System zur detektion von anormaler bewegung einer welle in einem gasturbinenmotor
EP3128307A1 (de) * 2015-07-27 2017-02-08 Weston Aerospace Limited Magnetisches sensorsystem zur detektion abnormaler bewegungen in einer gasturbinenwelle
EP3435058A1 (de) * 2017-07-28 2019-01-30 Rolls-Royce Deutschland Ltd & Co KG Anordnung und verfahren zur erkennung eines wellenbruchs

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004033924A1 (de) * 2004-07-14 2006-02-09 Mtu Aero Engines Gmbh Einrichtung zur Detektion eines Wellenbruchs an einer Gasturbine sowie Gasturbine
GB2494703B (en) * 2011-09-16 2016-08-03 Weston Aerospace Ltd System and method for detecting abnormal movement in a gas turbine shaft

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999000585A1 (de) 1997-06-27 1999-01-07 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Einrichtung zur notabschaltung einer gasturbine
US20030091430A1 (en) 2001-11-14 2003-05-15 Honeywell International, Inc Gas turbine engine broken shaft detection system
US6607349B2 (en) 2001-11-14 2003-08-19 Honeywell International, Inc. Gas turbine engine broken shaft detection system
GB2468686A (en) 2009-03-18 2010-09-22 Weston Aerospace Ltd System and method for detecting abnormal movement in a gas turbine shaft
EP3106626A1 (de) 2015-06-15 2016-12-21 Weston Aerospace Limited System zur detektion von anormaler bewegung einer welle in einem gasturbinenmotor
EP3128307A1 (de) * 2015-07-27 2017-02-08 Weston Aerospace Limited Magnetisches sensorsystem zur detektion abnormaler bewegungen in einer gasturbinenwelle
EP3435058A1 (de) * 2017-07-28 2019-01-30 Rolls-Royce Deutschland Ltd & Co KG Anordnung und verfahren zur erkennung eines wellenbruchs

Also Published As

Publication number Publication date
US20200325793A1 (en) 2020-10-15
GB2583078B (en) 2022-10-05
CA3077832A1 (en) 2020-10-09
GB201905005D0 (en) 2019-05-22
GB2583078A (en) 2020-10-21
EP3722563B1 (de) 2023-12-27

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