DE60023979D1 - Bläserplattform - Google Patents

Bläserplattform

Info

Publication number
DE60023979D1
DE60023979D1 DE60023979T DE60023979T DE60023979D1 DE 60023979 D1 DE60023979 D1 DE 60023979D1 DE 60023979 T DE60023979 T DE 60023979T DE 60023979 T DE60023979 T DE 60023979T DE 60023979 D1 DE60023979 D1 DE 60023979D1
Authority
DE
Germany
Prior art keywords
fan platform
fan
platform
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.)
Expired - Lifetime
Application number
DE60023979T
Other languages
English (en)
Other versions
DE60023979T2 (de
Inventor
John Andrew Ravenhall
Brian Michael Davis
Thomas Carl Mesing
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Application granted granted Critical
Publication of DE60023979D1 publication Critical patent/DE60023979D1/de
Publication of DE60023979T2 publication Critical patent/DE60023979T2/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
DE60023979T 1999-04-20 2000-04-19 Bläserplattform Expired - Lifetime DE60023979T2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US294551 1999-04-20
US09/294,551 US6217283B1 (en) 1999-04-20 1999-04-20 Composite fan platform

Publications (2)

Publication Number Publication Date
DE60023979D1 true DE60023979D1 (de) 2005-12-22
DE60023979T2 DE60023979T2 (de) 2006-08-03

Family

ID=23133929

Family Applications (1)

Application Number Title Priority Date Filing Date
DE60023979T Expired - Lifetime DE60023979T2 (de) 1999-04-20 2000-04-19 Bläserplattform

Country Status (4)

Country Link
US (1) US6217283B1 (de)
EP (1) EP1046785B1 (de)
JP (1) JP4572411B2 (de)
DE (1) DE60023979T2 (de)

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US6524070B1 (en) * 2000-08-21 2003-02-25 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
US6634863B1 (en) * 2000-11-27 2003-10-21 General Electric Company Circular arc multi-bore fan disk assembly
US6579065B2 (en) 2001-09-13 2003-06-17 General Electric Co. Methods and apparatus for limiting fluid flow between adjacent rotor blades
US6792691B2 (en) 2002-11-12 2004-09-21 General Electric Company Gage for milled blade ring segments
US7284958B2 (en) * 2003-03-22 2007-10-23 Allison Advanced Development Company Separable blade platform
US6887043B2 (en) * 2003-03-28 2005-05-03 General Electric Company Methods and apparatus for assembling gas turbine engines
US6991428B2 (en) 2003-06-12 2006-01-31 Pratt & Whitney Canada Corp. Fan blade platform feature for improved blade-off performance
FR2858351B1 (fr) * 2003-07-31 2006-01-13 Snecma Moteurs Plate-forme inter-aubes a flechissement lateral, pour un support d'aubes de turboreacteur
US7094033B2 (en) * 2004-01-21 2006-08-22 General Electric Company Methods and apparatus for assembling gas turbine engines
GB0611031D0 (en) * 2006-06-06 2006-07-12 Rolls Royce Plc An aerofoil stage and a seal for use therein
AT503290B1 (de) * 2006-06-23 2007-09-15 Fischer Adv Components Gmbh Führungsträger für triebwerksverkleidungen
GB0614640D0 (en) 2006-07-22 2006-08-30 Rolls Royce Plc An annulus filler seal
US7762781B1 (en) 2007-03-06 2010-07-27 Florida Turbine Technologies, Inc. Composite blade and platform assembly
FR2914008B1 (fr) 2007-03-21 2009-10-09 Snecma Sa Ensemble rotatif d'une soufflante de turbomachine
US8257045B2 (en) * 2008-08-15 2012-09-04 United Technologies Corp. Platforms with curved side edges and gas turbine engine systems involving such platforms
FR2939836B1 (fr) * 2008-12-12 2015-05-15 Snecma Joint d'etancheite de plateforme dans un rotor de turbomachine
US8568102B2 (en) * 2009-02-18 2013-10-29 Pratt & Whitney Canada Corp. Fan blade anti-fretting insert
US8616849B2 (en) * 2009-02-18 2013-12-31 Pratt & Whitney Canada Corp. Fan blade platform
US8667775B1 (en) * 2009-08-05 2014-03-11 The Boeing Company Reverse flow engine core having a ducted fan with integrated secondary flow blades
US9200593B2 (en) * 2009-08-07 2015-12-01 Hamilton Sundstrand Corporation Energy absorbing fan blade spacer
EP2447476A3 (de) * 2010-11-01 2017-11-15 Rolls-Royce plc Ringförmiges Zwischenstück für eine Rotorscheibe einer Gasturbine
GB201020857D0 (en) * 2010-12-09 2011-01-26 Rolls Royce Plc Annulus filler
US20120156045A1 (en) * 2010-12-17 2012-06-21 General Electric Company Methods, systems and apparatus relating to root and platform configurations for turbine rotor blades
GB201106278D0 (en) 2011-04-14 2011-05-25 Rolls Royce Plc Annulus filler system
US8777576B2 (en) * 2011-08-22 2014-07-15 General Electric Company Metallic fan blade platform
US8985956B2 (en) * 2011-09-19 2015-03-24 General Electric Company Compressive stress system for a gas turbine engine
GB201119655D0 (en) 2011-11-15 2011-12-28 Rolls Royce Plc Annulus filler
FR2992676B1 (fr) * 2012-06-29 2014-08-01 Snecma Plateforme inter-aubes pour une soufflante, rotor d'une soufflante et procede de fabrication associe
US9267386B2 (en) 2012-06-29 2016-02-23 United Technologies Corporation Fairing assembly
WO2014028056A1 (en) * 2012-08-17 2014-02-20 United Technologies Corporation Contoured flowpath surface
US9297268B2 (en) * 2012-09-06 2016-03-29 United Technologies Corporation Fan blade platform flap seal
US9239062B2 (en) * 2012-09-10 2016-01-19 General Electric Company Low radius ratio fan for a gas turbine engine
US10119423B2 (en) 2012-09-20 2018-11-06 United Technologies Corporation Gas turbine engine fan spacer platform attachments
EP2956626B1 (de) * 2013-02-12 2019-11-20 United Technologies Corporation Fanschaufel mit externen hohlräumen
US9845699B2 (en) * 2013-03-15 2017-12-19 Gkn Aerospace Services Structures Corp. Fan spacer having unitary over molded feature
US10145268B2 (en) * 2013-03-15 2018-12-04 United Technologies Corporation Injection molded composite fan platform
US10047625B2 (en) 2013-03-15 2018-08-14 United Technologies Corporation Fan blade root integrated sealing solution
WO2015073096A2 (en) * 2013-09-13 2015-05-21 United Technologies Corporation Fan platform
EP3065937B1 (de) 2013-11-06 2020-11-25 United Technologies Corporation In-situ-entschlichtung für flüssigkeitsinjektionsverfahren
EP3080418B1 (de) * 2013-12-13 2020-06-24 United Technologies Corporation Kantenabdichtung zur plattform eines bläsers
WO2015142395A2 (en) * 2014-01-31 2015-09-24 United Technologies Corporation Compressed chopped fiber composite fan blade platform
US10094282B2 (en) * 2014-07-30 2018-10-09 United Technologies Corporation Spinner aft-extended forward return flange
US9926798B2 (en) 2014-08-13 2018-03-27 Rolls-Royce Corporation Method for manufacturing composite fan annulus filler having nano-coating
US10156151B2 (en) * 2014-10-23 2018-12-18 Rolls-Royce North American Technologies Inc. Composite annulus filler
US9896949B2 (en) * 2014-12-23 2018-02-20 United Technologies Corporation Bonded fan platform
US10605117B2 (en) * 2015-10-08 2020-03-31 General Electric Company Fan platform for a gas turbine engine
US20170101878A1 (en) * 2015-10-08 2017-04-13 General Electric Company Low modulus insert for a component of a gas turbine engine
US10584592B2 (en) * 2015-11-23 2020-03-10 United Technologies Corporation Platform for an airfoil having bowed sidewalls
US10458425B2 (en) 2016-06-02 2019-10-29 General Electric Company Conical load spreader for composite bolted joint
CN105909557A (zh) * 2016-06-21 2016-08-31 中国航空工业集团公司沈阳发动机设计研究所 一种风扇转子叶片安装结构
US10436036B2 (en) * 2016-07-05 2019-10-08 Safran Aircraft Engines Fitted platform for a turbine engine fan, and a method of fabricating it
US10557350B2 (en) * 2017-03-30 2020-02-11 General Electric Company I beam blade platform
US10746031B2 (en) 2017-07-18 2020-08-18 Rolls-Royce Corporation Annulus filler
US10738630B2 (en) 2018-02-19 2020-08-11 General Electric Company Platform apparatus for propulsion rotor
RU2698534C1 (ru) * 2018-03-06 2019-08-28 Публичное Акционерное Общество "Одк-Сатурн" Платформа вентилятора из композиционного материала и способ ее изготовления
US11021984B2 (en) * 2018-03-08 2021-06-01 Raytheon Technologies Corporation Gas turbine engine fan platform
US11136888B2 (en) 2018-10-18 2021-10-05 Raytheon Technologies Corporation Rotor assembly with active damping for gas turbine engines
US11359500B2 (en) * 2018-10-18 2022-06-14 Raytheon Technologies Corporation Rotor assembly with structural platforms for gas turbine engines
US11092020B2 (en) 2018-10-18 2021-08-17 Raytheon Technologies Corporation Rotor assembly for gas turbine engines
US10822969B2 (en) 2018-10-18 2020-11-03 Raytheon Technologies Corporation Hybrid airfoil for gas turbine engines
US11306601B2 (en) 2018-10-18 2022-04-19 Raytheon Technologies Corporation Pinned airfoil for gas turbine engines
US11242763B2 (en) * 2018-10-22 2022-02-08 General Electric Company Platform apparatus for propulsion rotor
FR3091563B1 (fr) * 2019-01-04 2023-01-20 Safran Aircraft Engines Joint d’étanchéité amélioré de plateforme inter-aubes
FR3097904B1 (fr) * 2019-06-26 2021-06-11 Safran Aircraft Engines Plateforme inter-aube avec caisson sacrificiel
US11268396B2 (en) * 2020-01-17 2022-03-08 Raytheon Technologies Corporation Turbine fan fairing platform with protective surface
FR3109793B1 (fr) * 2020-05-04 2022-08-12 Safran Aircraft Engines Plateforme pour un rotor de soufflante d’une turbomachine d’aéronef
US11572794B2 (en) * 2021-01-07 2023-02-07 General Electric Company Inner shroud damper for vibration reduction
US20230114262A1 (en) * 2021-10-08 2023-04-13 Raytheon Technologies Corporation Methods involving and apparatuses for a turbine engine fairing

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Also Published As

Publication number Publication date
US6217283B1 (en) 2001-04-17
EP1046785A3 (de) 2002-10-23
EP1046785B1 (de) 2005-11-16
EP1046785A2 (de) 2000-10-25
DE60023979T2 (de) 2006-08-03
JP4572411B2 (ja) 2010-11-04
JP2000320491A (ja) 2000-11-21

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition