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GB201104994D0 - a rotor having an annulus filler - Google Patents

a rotor having an annulus filler

Info

Publication number
GB201104994D0
GB201104994D0 GBGB1104994.7A GB201104994A GB201104994D0 GB 201104994 D0 GB201104994 D0 GB 201104994D0 GB 201104994 A GB201104994 A GB 201104994A GB 201104994 D0 GB201104994 D0 GB 201104994D0
Authority
GB
United Kingdom
Prior art keywords
rotor
annulus filler
annulus
filler
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
GBGB1104994.7A
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 GBGB1104994.7A priority Critical patent/GB201104994D0/en
Publication of GB201104994D0 publication Critical patent/GB201104994D0/en
Priority to US13/404,445 priority patent/US20120244003A1/en
Priority to EP12156804.2A priority patent/EP2503102A3/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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
GBGB1104994.7A 2011-03-25 2011-03-25 a rotor having an annulus filler Ceased GB201104994D0 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GBGB1104994.7A GB201104994D0 (en) 2011-03-25 2011-03-25 a rotor having an annulus filler
US13/404,445 US20120244003A1 (en) 2011-03-25 2012-02-24 Rotor having an annulus filler
EP12156804.2A EP2503102A3 (en) 2011-03-25 2012-02-24 A rotor having an annulus filler

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB1104994.7A GB201104994D0 (en) 2011-03-25 2011-03-25 a rotor having an annulus filler

Publications (1)

Publication Number Publication Date
GB201104994D0 true GB201104994D0 (en) 2011-05-11

Family

ID=44067330

Family Applications (1)

Application Number Title Priority Date Filing Date
GBGB1104994.7A Ceased GB201104994D0 (en) 2011-03-25 2011-03-25 a rotor having an annulus filler

Country Status (3)

Country Link
US (1) US20120244003A1 (en)
EP (1) EP2503102A3 (en)
GB (1) GB201104994D0 (en)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201020857D0 (en) * 2010-12-09 2011-01-26 Rolls Royce Plc Annulus filler
US9303520B2 (en) 2011-12-09 2016-04-05 General Electric Company Double fan outlet guide vane with structural platforms
US20130149127A1 (en) * 2011-12-09 2013-06-13 General Electric Company Structural Platforms for Fan Double Outlet Guide Vane
US9303531B2 (en) 2011-12-09 2016-04-05 General Electric Company Quick engine change assembly for outlet guide vanes
FR2991372B1 (en) * 2012-06-04 2014-05-16 Snecma TURBINE WHEEL IN A TURBOMACHINE
WO2014126704A1 (en) * 2013-02-12 2014-08-21 United Technologies Corporation Fan blade including external cavities
GB201314542D0 (en) * 2013-08-14 2013-09-25 Rolls Royce Plc Annulus Filler
GB201314541D0 (en) * 2013-08-14 2013-09-25 Rolls Royce Plc Annulus Filler
GB201314540D0 (en) * 2013-08-14 2013-09-25 Rolls Royce Plc Annulus filler
WO2015076900A2 (en) 2013-10-11 2015-05-28 United Technologies Corporation Fan rotor with integrated platform attachment
US10024234B2 (en) * 2014-09-08 2018-07-17 Rolls-Royce Deutschland Ltd & Co Kg Panels of a fan of a gas turbine
FR3029563B1 (en) * 2014-12-08 2020-01-17 Safran Aircraft Engines LOW HUB RATIO PLATFORM
US9988920B2 (en) * 2015-04-08 2018-06-05 United Technologies Corporation Fan blade platform seal with leading edge winglet
FR3038654B1 (en) * 2015-07-08 2017-08-04 Snecma ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK
FR3038653B1 (en) * 2015-07-08 2017-08-04 Snecma ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK
US9976426B2 (en) * 2015-07-21 2018-05-22 United Technologies Corporation Fan platform with stiffening feature
FR3048997B1 (en) * 2016-03-21 2020-03-27 Safran Aircraft Engines BLADE PLATFORM AND AERONAUTICAL TURBOMACHINE BLOWER DISC
US10458425B2 (en) 2016-06-02 2019-10-29 General Electric Company Conical load spreader for composite bolted joint
US10746031B2 (en) 2017-07-18 2020-08-18 Rolls-Royce Corporation Annulus filler
US11078839B2 (en) 2018-01-22 2021-08-03 Rolls-Royce Corporation Composite nosecone
US10724390B2 (en) 2018-03-16 2020-07-28 General Electric Company Collar support assembly for airfoils
US11815017B2 (en) * 2020-04-16 2023-11-14 Rtx Corporation Fan blade platform for gas turbine engine
US11421538B2 (en) 2020-05-12 2022-08-23 Rolls-Royce Corporation Composite aerofoils
US11506083B2 (en) 2020-06-03 2022-11-22 Rolls-Royce Corporalion Composite liners for turbofan engines
US12012857B2 (en) 2022-10-14 2024-06-18 Rtx Corporation Platform for an airfoil of a gas turbine engine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2608674B1 (en) * 1986-12-17 1991-04-19 Snecma CERAMIC BLADE TURBINE WHEEL
GB2299834B (en) * 1995-04-12 1999-09-08 Rolls Royce Plc Gas turbine engine rotary disc
US6290466B1 (en) * 1999-09-17 2001-09-18 General Electric Company Composite blade root attachment
FR2831207B1 (en) * 2001-10-24 2004-06-04 Snecma Moteurs PLATFORMS FOR BLADES OF A ROTARY ASSEMBLY
FR2844562B1 (en) * 2002-09-18 2004-10-29 Snecma Moteurs CONTROL OF THE AXIAL POSITION OF A BLOWER ROTOR BLADE
US7094033B2 (en) * 2004-01-21 2006-08-22 General Electric Company Methods and apparatus for assembling gas turbine engines
FR2913735B1 (en) * 2007-03-16 2013-04-19 Snecma ROTOR DISC OF A TURBOMACHINE
US8616849B2 (en) * 2009-02-18 2013-12-31 Pratt & Whitney Canada Corp. Fan blade platform

Also Published As

Publication number Publication date
US20120244003A1 (en) 2012-09-27
EP2503102A3 (en) 2017-08-09
EP2503102A2 (en) 2012-09-26

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Legal Events

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