IL143787A - Conforming platform fan blade - Google Patents

Conforming platform fan blade

Info

Publication number
IL143787A
IL143787A IL14378701A IL14378701A IL143787A IL 143787 A IL143787 A IL 143787A IL 14378701 A IL14378701 A IL 14378701A IL 14378701 A IL14378701 A IL 14378701A IL 143787 A IL143787 A IL 143787A
Authority
IL
Israel
Prior art keywords
platform
airfoil
root
sides
trailing
Prior art date
Application number
IL14378701A
Other languages
English (en)
Other versions
IL143787A0 (en
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of IL143787A0 publication Critical patent/IL143787A0/xx
Publication of IL143787A publication Critical patent/IL143787A/en

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/327—Application in turbines in gas turbines to drive shrouded, high solidity propeller
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/34—Arrangement of components translated
    • 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
    • F05D2250/71—Shape curved
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
IL14378701A 2000-06-30 2001-06-15 Conforming platform fan blade IL143787A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US09/607,491 US6338611B1 (en) 2000-06-30 2000-06-30 Conforming platform fan blade

Publications (2)

Publication Number Publication Date
IL143787A0 IL143787A0 (en) 2002-04-21
IL143787A true IL143787A (en) 2004-06-20

Family

ID=24432503

Family Applications (1)

Application Number Title Priority Date Filing Date
IL14378701A IL143787A (en) 2000-06-30 2001-06-15 Conforming platform fan blade

Country Status (6)

Country Link
US (1) US6338611B1 (ru)
EP (1) EP1167688A3 (ru)
JP (1) JP5290484B2 (ru)
CN (1) CN100379940C (ru)
IL (1) IL143787A (ru)
RU (1) RU2272180C2 (ru)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7063505B2 (en) 2003-02-07 2006-06-20 General Electric Company Gas turbine engine frame having struts connected to rings with morse pins
US7261794B2 (en) * 2003-05-16 2007-08-28 International Automotive Components Group, Llc Method and apparatus for bonding a cover to a substrate using high frequency microwaves
US6991428B2 (en) 2003-06-12 2006-01-31 Pratt & Whitney Canada Corp. Fan blade platform feature for improved blade-off performance
GB0614518D0 (en) 2006-07-21 2006-08-30 Rolls Royce Plc A fan blade for a gas turbine engine
US9920625B2 (en) 2011-01-13 2018-03-20 Siemens Energy, Inc. Turbine blade with laterally biased airfoil and platform centers of mass
US9267386B2 (en) 2012-06-29 2016-02-23 United Technologies Corporation Fairing assembly
US10344601B2 (en) 2012-08-17 2019-07-09 United Technologies Corporation Contoured flowpath surface
EP2971521B1 (en) 2013-03-11 2022-06-22 Rolls-Royce Corporation Gas turbine engine flow path geometry
CN105756723B (zh) * 2014-12-15 2017-06-06 中航商用航空发动机有限责任公司 一种主动熔断装置、方法及航空发动机
UA114769C2 (uk) * 2016-06-21 2017-07-25 Андрій Іванович Панфілов Робоче колесо відцентрового вентилятора
US10774679B2 (en) * 2018-02-09 2020-09-15 General Electric Company Turbine engine airfoil assembly
US11156110B1 (en) * 2020-08-04 2021-10-26 General Electric Company Rotor assembly for a turbine section of a gas turbine engine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2441249C3 (de) * 1974-08-28 1979-01-04 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Axiallaufrad für hochtourige Turbomaschinen
JPS53113902A (en) * 1977-03-16 1978-10-04 Hitachi Ltd Turbine blade mounting structure
US4621979A (en) * 1979-11-30 1986-11-11 United Technologies Corporation Fan rotor blades of turbofan engines
US4541778A (en) * 1984-05-18 1985-09-17 The United States Of America As Represented By The Secretary Of The Navy Pin rooted blade biaxial air seal
US5242270A (en) * 1992-01-31 1993-09-07 Westinghouse Electric Corp. Platform motion restraints for freestanding turbine blades
US5310318A (en) * 1993-07-21 1994-05-10 General Electric Company Asymmetric axial dovetail and rotor disk
US5443365A (en) * 1993-12-02 1995-08-22 General Electric Company Fan blade for blade-out protection
FR2743845B1 (fr) * 1996-01-23 1998-02-20 Snecma Aube mobile de soufflante a profil de securite
GB9823840D0 (en) * 1998-10-30 1998-12-23 Rolls Royce Plc Bladed ducting for turbomachinery

Also Published As

Publication number Publication date
JP2002115695A (ja) 2002-04-19
EP1167688A2 (en) 2002-01-02
IL143787A0 (en) 2002-04-21
EP1167688A3 (en) 2003-08-13
US6338611B1 (en) 2002-01-15
JP5290484B2 (ja) 2013-09-18
RU2272180C2 (ru) 2006-03-20
CN1331380A (zh) 2002-01-16
CN100379940C (zh) 2008-04-09

Similar Documents

Publication Publication Date Title
CA2614406C (en) Methods and apparatus for fabricating a fan assembly for use with turbine engines
EP2199543B1 (en) Rotor blade for a gas turbine engine and method of designing an airfoil
EP0902165B1 (en) Impact resistant hollow airfoils
EP2305954B1 (en) Internally damped blade
US5443365A (en) Fan blade for blade-out protection
US8834129B2 (en) Turbofan flow path trenches
CA1233126A (en) Gas turbine bladed disk assembly
US6364603B1 (en) Fan case for turbofan engine having a fan decoupler
CN107829958B (zh) 带有低部分翼展实度的飞行器风扇
EP1942252B1 (en) Airfoil tip for a rotor assembly
US6338611B1 (en) Conforming platform fan blade
EP2372094A2 (en) Non-Integral Platform and Damper for a gas turbine engine blade
EP0924380B1 (en) Striated turbomachine blade
EP3084139B1 (en) A gas turbine engine integrally bladed rotor with asymmetrical trench fillets
US10408068B2 (en) Fan blade dovetail and spacer
US6422820B1 (en) Corner tang fan blade
US20180017075A1 (en) Airfoil with stress-reducing fillet adapted for use in a gas turbine engine
CA2547172C (en) Angled cooling divider wall in blade attachment
CA2881943C (en) Turbine blade for a gas turbine engine
GB2295861A (en) Split disc gas turbine engine blade support
US7066714B2 (en) High speed rotor assembly shroud

Legal Events

Date Code Title Description
FF Patent granted
KB Patent renewed
KB Patent renewed
KB Patent renewed
MM9K Patent not in force due to non-payment of renewal fees