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GB201415201D0 - A wear monitor for a gas turbine engine fan - Google Patents

A wear monitor for a gas turbine engine fan

Info

Publication number
GB201415201D0
GB201415201D0 GBGB1415201.1A GB201415201A GB201415201D0 GB 201415201 D0 GB201415201 D0 GB 201415201D0 GB 201415201 A GB201415201 A GB 201415201A GB 201415201 D0 GB201415201 D0 GB 201415201D0
Authority
GB
United Kingdom
Prior art keywords
gas turbine
turbine engine
engine fan
wear monitor
wear
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.)
Ceased
Application number
GBGB1415201.1A
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
Priority to GBGB1415201.1A priority Critical patent/GB201415201D0/en
Publication of GB201415201D0 publication Critical patent/GB201415201D0/en
Priority to US14/833,808 priority patent/US20160061050A1/en
Priority to EP15182102.2A priority patent/EP2990660B8/en
Ceased legal-status Critical Current

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)
GBGB1415201.1A 2014-08-28 2014-08-28 A wear monitor for a gas turbine engine fan Ceased GB201415201D0 (en)

Priority Applications (3)

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
US14/833,808 US20160061050A1 (en) 2014-08-28 2015-08-24 Wear monitor for a gas turbine engine
EP15182102.2A EP2990660B8 (en) 2014-08-28 2015-08-24 A wear monitor for a gas turbine engine

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 (1)

Publication Number Publication Date
GB201415201D0 true GB201415201D0 (en) 2014-10-15

Family

ID=51752240

Family Applications (1)

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

Country Status (3)

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

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014158236A1 (en) * 2013-03-12 2014-10-02 United Technologies Corporation Cantilever stator with vortex initiation feature
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
US20200182083A1 (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
US12366918B2 (en) * 2023-09-08 2025-07-22 Pratt & Whitney Canada Corp. Augmented reality machining aid

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
US20160061050A1 (en) 2016-03-03
EP2990660A1 (en) 2016-03-02
EP2990660B1 (en) 2020-02-05
EP2990660B8 (en) 2020-03-11

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Legal Events

Date Code Title Description
AT Applications terminated before publication under section 16(1)