EP2990660B8 - A wear monitor for a gas turbine engine - Google Patents

A wear monitor for a gas turbine engine Download PDF

Info

Publication number
EP2990660B8
EP2990660B8 EP15182102.2A EP15182102A EP2990660B8 EP 2990660 B8 EP2990660 B8 EP 2990660B8 EP 15182102 A EP15182102 A EP 15182102A EP 2990660 B8 EP2990660 B8 EP 2990660B8
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine engine
wear monitor
wear
monitor
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.)
Active
Application number
EP15182102.2A
Other languages
German (de)
French (fr)
Other versions
EP2990660B1 (en
EP2990660A1 (en
Inventor
Michael Keenan
Nicholas Thomas
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 PLC
Original Assignee
Rolls Royce PLC
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 PLC filed Critical Rolls Royce PLC
Publication of EP2990660A1 publication Critical patent/EP2990660A1/en
Application granted granted Critical
Publication of EP2990660B1 publication Critical patent/EP2990660B1/en
Publication of EP2990660B8 publication Critical patent/EP2990660B8/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • 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
    • 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
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/305—Tolerances
    • 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
    • F05D2270/80—Devices generating input signals, e.g. transducers, sensors, cameras or strain gauges
    • F05D2270/821—Displacement measuring means, e.g. inductive

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP15182102.2A 2014-08-28 2015-08-24 A wear monitor for a gas turbine engine Active EP2990660B8 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB1415201.1A GB201415201D0 (en) 2014-08-28 2014-08-28 A wear monitor for a gas turbine engine fan

Publications (3)

Publication Number Publication Date
EP2990660A1 EP2990660A1 (en) 2016-03-02
EP2990660B1 EP2990660B1 (en) 2020-02-05
EP2990660B8 true EP2990660B8 (en) 2020-03-11

Family

ID=51752240

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15182102.2A Active EP2990660B8 (en) 2014-08-28 2015-08-24 A wear monitor for a gas turbine engine

Country Status (3)

Country Link
US (1) US20160061050A1 (en)
EP (1) EP2990660B8 (en)
GB (1) GB201415201D0 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10240471B2 (en) * 2013-03-12 2019-03-26 United Technologies Corporation Serrated outer surface for vortex initiation within the compressor stage of a gas turbine
US10352236B2 (en) * 2013-10-30 2019-07-16 United Technologies Corporation Nosecap
US10428674B2 (en) * 2017-01-31 2019-10-01 Rolls-Royce North American Technologies Inc. Gas turbine engine features for tip clearance inspection
US10612413B2 (en) * 2017-03-06 2020-04-07 United Technologies Corporation Wear indicator for determining wear on a component of a gas turbine engine
WO2020117882A1 (en) * 2018-12-06 2020-06-11 Gulfstream Aerospace Corporation Visual detection of fan case liner damage for turbine engine
FR3091548B1 (en) * 2019-01-09 2022-12-09 Safran Aircraft Engines Abradable turbomachine element provided with visual wear indicators
FR3095045B1 (en) * 2019-04-12 2021-12-10 Safran Aircraft Engines METHOD OF DETECTION OF ASPERITY ON AN ABRADABLE LAYER IN A BLOWER HOUSING
US11326469B2 (en) * 2020-05-29 2022-05-10 Rolls-Royce Corporation CMCs with luminescence environmental barrier coatings
FR3125316A1 (en) * 2021-07-16 2023-01-20 Safran Aircraft Engines ABRADABLE ELEMENT INCLUDING A WEAR INDICATOR

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3575427A (en) * 1969-11-03 1971-04-20 United Aircraft Corp Composite abradable seal
US3843278A (en) * 1973-06-04 1974-10-22 United Aircraft Corp Abradable seal construction
FR2339741A1 (en) * 1976-01-30 1977-08-26 Snecma ABRADABLE STATOR GASKET FOR AXIAL TURBOMACHINE AND ITS EXECUTION PROCESS
US4239452A (en) * 1978-06-26 1980-12-16 United Technologies Corporation Blade tip shroud for a compression stage of a gas turbine engine
US4566700A (en) * 1982-08-09 1986-01-28 United Technologies Corporation Abrasive/abradable gas path seal system
JPS62207885A (en) * 1986-03-07 1987-09-12 Toshiba Corp High temperature heat resistant member
DE19717816A1 (en) * 1997-04-26 1998-10-29 Asea Brown Boveri Device and method for measuring a distance between rotating and stationary parts of a turbine
US6340286B1 (en) * 1999-12-27 2002-01-22 General Electric Company Rotary machine having a seal assembly
US6838157B2 (en) * 2002-09-23 2005-01-04 Siemens Westinghouse Power Corporation Method and apparatus for instrumenting a gas turbine component having a barrier coating
DE102005047739B3 (en) * 2005-09-29 2007-02-08 Siemens Ag Substrate with matrix layer for turbine systems and production process has multilayer of and or encapsulated nanoparticles that release a colored material above a threshold temperature
GB0600532D0 (en) * 2006-01-12 2006-02-22 Rolls Royce Plc A blade and rotor arrangement
US7871244B2 (en) * 2007-02-15 2011-01-18 Siemens Energy, Inc. Ring seal for a turbine engine
US7819625B2 (en) * 2007-05-07 2010-10-26 Siemens Energy, Inc. Abradable CMC stacked laminate ring segment for a gas turbine
US8079806B2 (en) * 2007-11-28 2011-12-20 United Technologies Corporation Segmented ceramic layer for member of gas turbine engine
FR2929349B1 (en) * 2008-03-28 2010-04-16 Snecma CARTER FOR MOBILE WHEEL TURBOMACHINE WHEEL
GB0911459D0 (en) * 2009-07-02 2009-08-12 Rolls Royce Plc An assembly providing contaminant removal
US8684669B2 (en) * 2011-02-15 2014-04-01 Siemens Energy, Inc. Turbine tip clearance measurement
FR2981131B1 (en) * 2011-10-07 2013-11-01 Turbomeca CENTRIFUGAL COMPRESSOR EQUIPPED WITH A WEAR MEASUREMENT MARKER AND WEAR FOLLOWING METHOD USING THE MARKER
FR3006013B1 (en) * 2013-05-21 2017-10-13 Turbomeca TURBOMACHINE COMPRISING A WEAR OF THE CARTER
US10309243B2 (en) * 2014-05-23 2019-06-04 United Technologies Corporation Grooved blade outer air seals
US10125625B2 (en) * 2015-08-03 2018-11-13 Siemens Energy, Inc. Gas turbine engine component with performance feature

Also Published As

Publication number Publication date
EP2990660B1 (en) 2020-02-05
GB201415201D0 (en) 2014-10-15
US20160061050A1 (en) 2016-03-03
EP2990660A1 (en) 2016-03-02

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