EP2932047A4 - Gebläseschaufelplattformdichtung für gasturbinenmotor - Google Patents

Gebläseschaufelplattformdichtung für gasturbinenmotor

Info

Publication number
EP2932047A4
EP2932047A4 EP13862661.9A EP13862661A EP2932047A4 EP 2932047 A4 EP2932047 A4 EP 2932047A4 EP 13862661 A EP13862661 A EP 13862661A EP 2932047 A4 EP2932047 A4 EP 2932047A4
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine engine
fan blade
blade platform
engine fan
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.)
Withdrawn
Application number
EP13862661.9A
Other languages
English (en)
French (fr)
Other versions
EP2932047A1 (de
Inventor
Andrew G Alarcon
Royce E Tatton
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP2932047A1 publication Critical patent/EP2932047A1/de
Publication of EP2932047A4 publication Critical patent/EP2932047A4/de
Withdrawn legal-status Critical Current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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/437—Silicon polymers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Architecture (AREA)
EP13862661.9A 2012-12-14 2013-11-14 Gebläseschaufelplattformdichtung für gasturbinenmotor Withdrawn EP2932047A4 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/715,388 US20140169979A1 (en) 2012-12-14 2012-12-14 Gas turbine engine fan blade platform seal
PCT/US2013/070096 WO2014092925A1 (en) 2012-12-14 2013-11-14 Gas turbine engine fan blade platform seal

Publications (2)

Publication Number Publication Date
EP2932047A1 EP2932047A1 (de) 2015-10-21
EP2932047A4 true EP2932047A4 (de) 2015-12-09

Family

ID=50931100

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13862661.9A Withdrawn EP2932047A4 (de) 2012-12-14 2013-11-14 Gebläseschaufelplattformdichtung für gasturbinenmotor

Country Status (3)

Country Link
US (1) US20140169979A1 (de)
EP (1) EP2932047A4 (de)
WO (1) WO2014092925A1 (de)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10119423B2 (en) 2012-09-20 2018-11-06 United Technologies Corporation Gas turbine engine fan spacer platform attachments
US20150117804A1 (en) * 2013-10-30 2015-04-30 United Technologies Corporation Gas turbine engine bushing
US9988920B2 (en) 2015-04-08 2018-06-05 United Technologies Corporation Fan blade platform seal with leading edge winglet
FR3052822B1 (fr) 2016-06-16 2020-03-27 Safran Aircraft Engines Aube de turbomachine equipee d'un joint en elastomere
GB2554650B (en) 2016-09-30 2019-02-06 Rolls Royce Plc Side seal for a gas turbine engine
FR3082876B1 (fr) 2018-06-21 2021-01-22 Safran Aircraft Engines Soufflante comprenant une plateforme et un verrou de blocage
US11028714B2 (en) * 2018-07-16 2021-06-08 Raytheon Technologies Corporation Fan platform wedge seal

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2436087A (en) * 1944-12-04 1948-02-17 Ernest H Benson Cooling fan for aircraft engines
US3451654A (en) * 1967-08-25 1969-06-24 Gen Motors Corp Blade vibration damping
GB1331209A (en) * 1969-10-28 1973-09-26 Secr Defence Bladed rotors for fluid flow machines
EP0277884A2 (de) * 1987-02-05 1988-08-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" In das Gehäuse eingepresster Aussenring eines Stators für den Bläser eines Turbotriebwerks
US6634863B1 (en) * 2000-11-27 2003-10-21 General Electric Company Circular arc multi-bore fan disk assembly
EP1609952A1 (de) * 2004-06-23 2005-12-28 General Electric Company Manschettendichtung für Turbinenleitschaufeln
US20110037233A1 (en) * 2009-08-14 2011-02-17 Rolls-Royce Plc Sealing assembly
US7972113B1 (en) * 2007-05-02 2011-07-05 Florida Turbine Technologies, Inc. Integral turbine blade and platform
US20120244007A1 (en) * 2011-03-22 2012-09-27 Rolls-Royce Plc Bladed rotor

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4045149A (en) * 1976-02-03 1977-08-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Platform for a swing root turbomachinery blade
GB9209895D0 (en) * 1992-05-07 1992-06-24 Rolls Royce Plc Rotors for gas turbine engines
GB9602129D0 (en) * 1996-02-02 1996-04-03 Rolls Royce Plc Rotors for gas turbine engines
US6161839A (en) * 1998-02-27 2000-12-19 United Technologies Corporation Valve seal assembly
GB9915637D0 (en) * 1999-07-06 1999-09-01 Rolls Royce Plc A rotor seal
US6343912B1 (en) * 1999-12-07 2002-02-05 General Electric Company Gas turbine or jet engine stator vane frame
US6431835B1 (en) * 2000-10-17 2002-08-13 Honeywell International, Inc. Fan blade compliant shim
GB0614640D0 (en) * 2006-07-22 2006-08-30 Rolls Royce Plc An annulus filler seal
FR2939836B1 (fr) * 2008-12-12 2015-05-15 Snecma Joint d'etancheite de plateforme dans un rotor de turbomachine
US8382432B2 (en) * 2010-03-08 2013-02-26 General Electric Company Cooled turbine rim seal

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2436087A (en) * 1944-12-04 1948-02-17 Ernest H Benson Cooling fan for aircraft engines
US3451654A (en) * 1967-08-25 1969-06-24 Gen Motors Corp Blade vibration damping
GB1331209A (en) * 1969-10-28 1973-09-26 Secr Defence Bladed rotors for fluid flow machines
EP0277884A2 (de) * 1987-02-05 1988-08-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" In das Gehäuse eingepresster Aussenring eines Stators für den Bläser eines Turbotriebwerks
US6634863B1 (en) * 2000-11-27 2003-10-21 General Electric Company Circular arc multi-bore fan disk assembly
EP1609952A1 (de) * 2004-06-23 2005-12-28 General Electric Company Manschettendichtung für Turbinenleitschaufeln
US7972113B1 (en) * 2007-05-02 2011-07-05 Florida Turbine Technologies, Inc. Integral turbine blade and platform
US20110037233A1 (en) * 2009-08-14 2011-02-17 Rolls-Royce Plc Sealing assembly
US20120244007A1 (en) * 2011-03-22 2012-09-27 Rolls-Royce Plc Bladed rotor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2014092925A1 *

Also Published As

Publication number Publication date
US20140169979A1 (en) 2014-06-19
EP2932047A1 (de) 2015-10-21
WO2014092925A1 (en) 2014-06-19

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RIN1 Information on inventor provided before grant (corrected)

Inventor name: ALARCON, ANDREW G.

Inventor name: TATTON, ROYCE E.

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Effective date: 20151111

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Ipc: F01D 11/08 20060101AFI20151105BHEP

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Owner name: UNITED TECHNOLOGIES CORPORATION

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