DE69407518D1 - Rotorschaufel - Google Patents

Rotorschaufel

Info

Publication number
DE69407518D1
DE69407518D1 DE69407518T DE69407518T DE69407518D1 DE 69407518 D1 DE69407518 D1 DE 69407518D1 DE 69407518 T DE69407518 T DE 69407518T DE 69407518 T DE69407518 T DE 69407518T DE 69407518 D1 DE69407518 D1 DE 69407518D1
Authority
DE
Germany
Prior art keywords
rotor blade
rotor
blade
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 - Fee Related
Application number
DE69407518T
Other languages
English (en)
Other versions
DE69407518T2 (de
Inventor
John J Ciokajlo
Michael Thomas O'brien
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 DE69407518D1 publication Critical patent/DE69407518D1/de
Publication of DE69407518T2 publication Critical patent/DE69407518T2/de
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F02K3/072—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 counter-rotating, e.g. fan rotors
    • 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)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
DE69407518T 1993-09-14 1994-09-02 Rotorschaufel Expired - Fee Related DE69407518T2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US08/120,897 US5388964A (en) 1993-09-14 1993-09-14 Hybrid rotor blade

Publications (2)

Publication Number Publication Date
DE69407518D1 true DE69407518D1 (de) 1998-02-05
DE69407518T2 DE69407518T2 (de) 1998-07-09

Family

ID=22393159

Family Applications (1)

Application Number Title Priority Date Filing Date
DE69407518T Expired - Fee Related DE69407518T2 (de) 1993-09-14 1994-09-02 Rotorschaufel

Country Status (4)

Country Link
US (1) US5388964A (de)
EP (1) EP0643199B1 (de)
JP (1) JP2698324B2 (de)
DE (1) DE69407518T2 (de)

Families Citing this family (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5735673A (en) * 1996-12-04 1998-04-07 United Technologies Corporation Turbine engine rotor blade pair
US5725353A (en) * 1996-12-04 1998-03-10 United Technologies Corporation Turbine engine rotor disk
DE19828562B4 (de) * 1998-06-26 2005-09-08 Mtu Aero Engines Gmbh Triebwerk mit gegenläufig drehenden Rotoren
US6145300A (en) * 1998-07-09 2000-11-14 Pratt & Whitney Canada Corp. Integrated fan / low pressure compressor rotor for gas turbine engine
US6739120B2 (en) * 2002-04-29 2004-05-25 General Electric Company Counterrotatable booster compressor assembly for a gas turbine engine
US6666017B2 (en) * 2002-05-24 2003-12-23 General Electric Company Counterrotatable booster compressor assembly for a gas turbine engine
US6763654B2 (en) * 2002-09-30 2004-07-20 General Electric Co. Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans
US7063505B2 (en) * 2003-02-07 2006-06-20 General Electric Company Gas turbine engine frame having struts connected to rings with morse pins
US7246484B2 (en) 2003-08-25 2007-07-24 General Electric Company FLADE gas turbine engine with counter-rotatable fans
US6901739B2 (en) * 2003-10-07 2005-06-07 General Electric Company Gas turbine engine with variable pressure ratio fan system
US7395657B2 (en) * 2003-10-20 2008-07-08 General Electric Company Flade gas turbine engine with fixed geometry inlet
US7216475B2 (en) * 2003-11-21 2007-05-15 General Electric Company Aft FLADE engine
FR2866073B1 (fr) * 2004-02-11 2006-07-28 Snecma Moteurs Turboreacteur ayant deux soufflantes contrarotatives solidaires d'un compresseur a basse pression contrarotatif
FR2866387B1 (fr) * 2004-02-12 2008-03-14 Snecma Moteurs Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante
EP1607612B1 (de) * 2004-05-28 2009-03-04 Rolls-Royce Plc Gasturbine
US7134271B2 (en) * 2004-11-05 2006-11-14 General Electric Company Thrust vectoring aft FLADE engine
FR2889863B1 (fr) 2005-08-22 2007-11-02 Snecma Compresseur comportant une pluralite de caissons reconstituant un volume annulaire de separation de flux dans une turbomachine.
US7832193B2 (en) * 2006-10-27 2010-11-16 General Electric Company Gas turbine engine assembly and methods of assembling same
US8402742B2 (en) * 2007-12-05 2013-03-26 United Technologies Corporation Gas turbine engine systems involving tip fans
US8141366B2 (en) * 2008-08-19 2012-03-27 United Technologies Corporation Gas turbine engine with variable area fan nozzle
US8128021B2 (en) 2008-06-02 2012-03-06 United Technologies Corporation Engine mount system for a turbofan gas turbine engine
US20140174056A1 (en) 2008-06-02 2014-06-26 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
US8443586B2 (en) * 2009-11-24 2013-05-21 United Technologies Corporation Variable area fan nozzle bearing track
US20110120078A1 (en) * 2009-11-24 2011-05-26 Schwark Jr Fred W Variable area fan nozzle track
US9631558B2 (en) 2012-01-03 2017-04-25 United Technologies Corporation Geared architecture for high speed and small volume fan drive turbine
US9239012B2 (en) 2011-06-08 2016-01-19 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US9011087B2 (en) 2012-03-26 2015-04-21 United Technologies Corporation Hybrid airfoil for a gas turbine engine
US10036351B2 (en) 2012-04-02 2018-07-31 United Technologies Corporation Geared turbofan with three co-rotating turbines
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US9074485B2 (en) 2012-04-25 2015-07-07 United Technologies Corporation Geared turbofan with three turbines all counter-rotating
US10036350B2 (en) 2012-04-30 2018-07-31 United Technologies Corporation Geared turbofan with three turbines all co-rotating
US8572943B1 (en) 2012-05-31 2013-11-05 United Technologies Corporation Fundamental gear system architecture
US20150308351A1 (en) 2012-05-31 2015-10-29 United Technologies Corporation Fundamental gear system architecture
US8756908B2 (en) 2012-05-31 2014-06-24 United Technologies Corporation Fundamental gear system architecture
EP2971656B1 (de) 2013-03-15 2020-03-04 United Technologies Corporation Aerodynamische schienenverkleidung für die lüftungsgondel eines gasturbinenmotors
EP3006135B1 (de) 2013-06-04 2021-03-10 Kawasaki Jukogyo Kabushiki Kaisha Verfahren zur verdichtung und umformung durch drehungen sowie vorrichtung zur verdichtung und umformung durch drehungen
JP6445779B2 (ja) * 2014-04-21 2018-12-26 川崎重工業株式会社 予備成形体および軸対称部品の製造方法
US10961850B2 (en) * 2017-09-19 2021-03-30 General Electric Company Rotatable torque frame for gas turbine engine
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
GB2603148A (en) * 2021-01-28 2022-08-03 Rolls Royce Plc Gas turbine engine

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH162526A (de) * 1932-06-06 1933-06-30 Escher Wyss Maschf Ag Hohle Schaufel für Kreiselmaschinen, insbesondere Wasserturbinen.
DE869448C (de) * 1944-09-28 1953-03-05 Daimler Benz Ag Umkleidung von Propellerblattfuessen, z. B. bei Zweikreis-Turbinenstrahltriebwerken
US2605851A (en) * 1946-11-30 1952-08-05 Chrysler Corp Air intake for aircraft turbopropeller power plant
US3053437A (en) * 1960-10-18 1962-09-11 Gen Electric Turbo-fan rotor hub
GB1089247A (en) * 1966-06-03 1967-11-01 Rolls Royce Method of manufacturing a hollow aerofoil section blade for a fluid flow machine
US3528246A (en) * 1966-12-29 1970-09-15 Helen M Fischer Fan arrangement for high bypass ratio turbofan engine
GB1212167A (en) * 1969-02-05 1970-11-11 Rolls Royce Bladed rotor for a fluid flow machine
GB1309721A (en) * 1971-01-08 1973-03-14 Secr Defence Fan
US4043121A (en) * 1975-01-02 1977-08-23 General Electric Company Two-spool variable cycle engine
GB1497477A (en) * 1975-07-19 1978-01-12 Rolls Royce Gas turbine engine
US4288983A (en) * 1978-10-19 1981-09-15 United Technologies Corporation Turbofan engine having core supercharging stage
US4732538A (en) * 1984-03-02 1988-03-22 General Electric Company Blade hub air scoop
US4758129A (en) * 1985-05-31 1988-07-19 General Electric Company Power frame
GB2195712B (en) * 1986-10-08 1990-08-29 Rolls Royce Plc A turbofan gas turbine engine
GB2207191B (en) * 1987-07-06 1992-03-04 Gen Electric Gas turbine engine
WO1989010300A1 (en) * 1988-04-28 1989-11-02 Allied-Signal Inc. Spinner ducted exhaust for pusher turboprop engines
US4936748A (en) * 1988-11-28 1990-06-26 General Electric Company Auxiliary power source in an unducted fan gas turbine engine
US5224341A (en) * 1992-01-06 1993-07-06 United Technologies Corporation Separable fan strut for a gas turbofan powerplant
US5222360A (en) * 1991-10-30 1993-06-29 General Electric Company Apparatus for removably attaching a core frame to a vane frame with a stable mid ring
US5197857A (en) * 1991-06-06 1993-03-30 General Electric Company Multiple rotor disk assembly
US5261227A (en) * 1992-11-24 1993-11-16 General Electric Company Variable specific thrust turbofan engine

Also Published As

Publication number Publication date
JPH07166960A (ja) 1995-06-27
US5388964A (en) 1995-02-14
EP0643199A1 (de) 1995-03-15
DE69407518T2 (de) 1998-07-09
EP0643199B1 (de) 1997-12-29
JP2698324B2 (ja) 1998-01-19

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition
8339 Ceased/non-payment of the annual fee