WO2014018137A3 - Aircraft engine driveshaft vessel assembly and method of assembling the same - Google Patents

Aircraft engine driveshaft vessel assembly and method of assembling the same Download PDF

Info

Publication number
WO2014018137A3
WO2014018137A3 PCT/US2013/037270 US2013037270W WO2014018137A3 WO 2014018137 A3 WO2014018137 A3 WO 2014018137A3 US 2013037270 W US2013037270 W US 2013037270W WO 2014018137 A3 WO2014018137 A3 WO 2014018137A3
Authority
WO
WIPO (PCT)
Prior art keywords
driveshaft
vessel
vessel assembly
assembling
same
Prior art date
Application number
PCT/US2013/037270
Other languages
French (fr)
Other versions
WO2014018137A2 (en
Inventor
Mark Gregory WOTZAK
Original Assignee
General Electric Company
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 Company filed Critical General Electric Company
Priority to CA2870669A priority Critical patent/CA2870669A1/en
Priority to BR112014026258A priority patent/BR112014026258A2/en
Priority to JP2015507199A priority patent/JP5856711B2/en
Priority to CN201380021840.XA priority patent/CN104350237B/en
Priority to US14/395,879 priority patent/US9657646B2/en
Priority to EP13785968.2A priority patent/EP2841712A2/en
Publication of WO2014018137A2 publication Critical patent/WO2014018137A2/en
Publication of WO2014018137A3 publication Critical patent/WO2014018137A3/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Motor Power Transmission Devices (AREA)

Abstract

A driveshaft vessel assembly for a gas turbine engine is disclosed. The driveshaft vessel assembly comprises a driveshaft vessel and an outlet guide vane. The driveshaft vessel includes a forward face, an aft face, and opposing side faces and is configured to house at least a portion of a radial driveshaft. The outlet guide vane includes a leading edge and a trailing edge. The length of the trailing edge is substantially equal to a length of the forward face of the driveshaft vessel such that the trailing edge of the outlet guide vane is faired into the forward face of the driveshaft vessel.
PCT/US2013/037270 2012-04-25 2013-04-19 Aircraft engine driveshaft vessel assembly and method of assembling the same WO2014018137A2 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
CA2870669A CA2870669A1 (en) 2012-04-25 2013-04-19 Aircraft engine driveshaft vessel assembly and method of assembling the same
BR112014026258A BR112014026258A2 (en) 2012-04-25 2013-04-19 container assembly, method for mounting a gas turbine container and engine assembly
JP2015507199A JP5856711B2 (en) 2012-04-25 2013-04-19 Aircraft engine drive shaft compartment assembly and method of assembling an aircraft engine drive shaft compartment assembly
CN201380021840.XA CN104350237B (en) 2012-04-25 2013-04-19 The method of airplane engine transmission shaft container assemblies and the described assembly of assembling
US14/395,879 US9657646B2 (en) 2012-04-25 2013-04-19 Aircraft engine driveshaft vessel assembly and method of assembling the same
EP13785968.2A EP2841712A2 (en) 2012-04-25 2013-04-19 Aircraft engine driveshaft vessel assembly and method of assembling the same

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201261637954P 2012-04-25 2012-04-25
US61/637,954 2012-04-25

Publications (2)

Publication Number Publication Date
WO2014018137A2 WO2014018137A2 (en) 2014-01-30
WO2014018137A3 true WO2014018137A3 (en) 2014-04-17

Family

ID=49517623

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2013/037270 WO2014018137A2 (en) 2012-04-25 2013-04-19 Aircraft engine driveshaft vessel assembly and method of assembling the same

Country Status (7)

Country Link
US (1) US9657646B2 (en)
EP (1) EP2841712A2 (en)
JP (1) JP5856711B2 (en)
CN (1) CN104350237B (en)
BR (1) BR112014026258A2 (en)
CA (1) CA2870669A1 (en)
WO (1) WO2014018137A2 (en)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3022301B1 (en) * 2014-06-12 2016-07-29 Snecma TURBOMACHINE COMPRISING A DRIVE SYSTEM OF AN EQUIPMENT SUCH AS AN ACCESSORY HOUSING
US9915225B2 (en) * 2015-02-06 2018-03-13 United Technologies Corporation Propulsion system arrangement for turbofan gas turbine engine
FR3039598B1 (en) * 2015-07-29 2019-12-27 Safran Aircraft Engines AIR FLOW RECTIFICATION ASSEMBLY WITH IMPROVED AERODYNAMIC PERFORMANCE
US11014513B2 (en) 2016-05-18 2021-05-25 Rolls-Royce North American Technologies Inc. Control of low pressure generator for gas turbine engine
DE102016215030A1 (en) * 2016-08-11 2018-02-15 Rolls-Royce Deutschland Ltd & Co Kg Turbofan engine with a lying in the secondary flow channel and a separate end element panel
US11022042B2 (en) 2016-08-29 2021-06-01 Rolls-Royce North American Technologies Inc. Aircraft having a gas turbine generator with power assist
US10654577B2 (en) * 2017-02-22 2020-05-19 General Electric Company Rainbow flowpath low pressure turbine rotor assembly
US11255215B2 (en) 2017-07-06 2022-02-22 Rolls-Royce North American Technologies Inc. Gas turbine engine with microchannel cooled electric device
FR3071868B1 (en) * 2017-10-02 2019-09-27 Safran Aircraft Engines ARM FOR TURBOMACHINE CASING COMPRISING A BODY AND A REMOVABLE PART
FR3090033B1 (en) * 2018-12-18 2020-11-27 Safran Aircraft Engines TURBOMACHINE OUTLET AND BIFURCATION DIRECTOR VANE ASSEMBLY
US10823006B2 (en) * 2019-03-14 2020-11-03 Raytheon Technologies Corporation Lubrication systems and methods with superposition gearbox

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB926947A (en) * 1961-11-27 1963-05-22 Rolls Royce Improvements relating to gas turbine engine casings
US20080173114A1 (en) * 2006-10-13 2008-07-24 Snecma Turbojet engine accessory gear box driveshaft; modular additional accessory
EP2169182A2 (en) * 2008-09-30 2010-03-31 General Electric Company Integrated guide vane assembly
US20100206982A1 (en) * 2009-02-13 2010-08-19 The Boeing Company Counter rotating fan design and variable blade row spacing optimization for low environmental impact

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4722666A (en) 1987-06-29 1988-02-02 United Technologies Corporation Nose cowl mounted oil lubricating and cooling system
US5080555A (en) 1990-11-16 1992-01-14 General Motors Corporation Turbine support for gas turbine engine
DE69318713T2 (en) 1992-06-22 1999-01-21 United Technologies Corp Unmanned aerial vehicle with opposed jacket rotors
GB9606546D0 (en) 1996-03-28 1996-06-05 Rolls Royce Plc Gas turbine engine system
US6195983B1 (en) 1999-02-12 2001-03-06 General Electric Company Leaned and swept fan outlet guide vanes
JP2002081326A (en) 2000-09-05 2002-03-22 Ishikawajima Harima Heavy Ind Co Ltd Intermediate part support device of radial drive shaft of engine for aircraft
JP4192661B2 (en) 2003-04-14 2008-12-10 株式会社Ｉｈｉ Gas turbine vertical shaft support structure
GB0315894D0 (en) 2003-07-08 2003-08-13 Rolls Royce Plc Aircraft engine arrangement
US7233295B2 (en) 2005-05-03 2007-06-19 Florenio Pinili Regala Conformal driveshaft cover SATCOM antenna
US7500365B2 (en) * 2005-05-05 2009-03-10 United Technologies Corporation Accessory gearbox
GB0520850D0 (en) * 2005-10-14 2005-11-23 Rolls Royce Plc Fan static structure
US7607308B2 (en) 2005-12-08 2009-10-27 General Electric Company Shrouded turbofan bleed duct
GB0608983D0 (en) 2006-05-06 2006-06-14 Rolls Royce Plc Aeroengine mount
US20080159851A1 (en) 2006-12-29 2008-07-03 Thomas Ory Moniz Guide Vane and Method of Fabricating the Same
FR2921973B1 (en) 2007-10-04 2011-04-29 Snecma INTERMEDIATE CASING OF TURBOJET AND TURBOREACTOR
GB0719786D0 (en) 2007-10-11 2007-11-21 Rolls Royce Plc A vane and a vane assembly for a gas turbine engine
US9121351B2 (en) * 2008-10-30 2015-09-01 Rolls-Royce North American Technologies, Inc. Gas turbine engine accessory system
US8514136B2 (en) 2009-10-26 2013-08-20 The Boeing Company Conformal high frequency antenna
US9297312B2 (en) * 2012-12-29 2016-03-29 United Technologies Corporation Circumferentially retained fairing

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB926947A (en) * 1961-11-27 1963-05-22 Rolls Royce Improvements relating to gas turbine engine casings
US20080173114A1 (en) * 2006-10-13 2008-07-24 Snecma Turbojet engine accessory gear box driveshaft; modular additional accessory
EP2169182A2 (en) * 2008-09-30 2010-03-31 General Electric Company Integrated guide vane assembly
US20100206982A1 (en) * 2009-02-13 2010-08-19 The Boeing Company Counter rotating fan design and variable blade row spacing optimization for low environmental impact

Also Published As

Publication number Publication date
US20150139791A1 (en) 2015-05-21
WO2014018137A2 (en) 2014-01-30
US9657646B2 (en) 2017-05-23
EP2841712A2 (en) 2015-03-04
CA2870669A1 (en) 2014-01-30
BR112014026258A2 (en) 2017-06-27
CN104350237B (en) 2016-03-02
JP2015514909A (en) 2015-05-21
JP5856711B2 (en) 2016-02-10
CN104350237A (en) 2015-02-11

Similar Documents

Publication Publication Date Title
WO2014018137A3 (en) Aircraft engine driveshaft vessel assembly and method of assembling the same
WO2014028095A3 (en) Blade outer air seal with cored passages
WO2014035517A3 (en) Gas turbine engine turbine vane platform core
WO2014028090A3 (en) Blade outer air seal for a gas turbine engine
WO2015057310A3 (en) Platform cooling core for a gas turbine engine rotor blade
WO2013074165A8 (en) Asymmetric radial spline seal for a gas turbine engine
WO2014058493A3 (en) Suction side turbine blade tip cooling
EP2620591B8 (en) Gas turbine engine stator vane assembly with inner shroud
WO2014197037A3 (en) Bench aft sub-assembly for turbine exhaust case fairing
WO2014011242A3 (en) Hybrid airfoil for a gas turbine engine
EP2653652A3 (en) Axially-split radial turbine
WO2014143344A3 (en) Mount with an axial upstream linkage for connecting a gearbox to a turbine engine case
WO2015069338A3 (en) Gas turbine engine blade outer air seal thermal control system
WO2014204542A3 (en) Lightweight blade for gas turbine engine
WO2014058496A3 (en) Blade outer air seal for a gas turbine engine
WO2014099074A3 (en) Gas turbine engine combustor with integrated combustor vane
WO2014133649A3 (en) Component retention with probe
WO2014116308A3 (en) Geared turbine engine with a d-duct and a thrust reverser
EP4306788A3 (en) High turning fan exit stator
WO2014133647A3 (en) Circumferentially retained fairing
EP3070264A4 (en) Vane structure for axial flow turbomachine and gas turbine engine
WO2014074196A3 (en) Singlet vane cluster assembly
WO2014099097A3 (en) Combustor seal mistake-proofing for a gas turbine engine
EP2554794A3 (en) Vane assembly for a gas turbine engine
WO2014099076A3 (en) Gas turbine engine combustor with integrated combustor vane

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 13785968

Country of ref document: EP

Kind code of ref document: A2

ENP Entry into the national phase

Ref document number: 2870669

Country of ref document: CA

ENP Entry into the national phase

Ref document number: 2015507199

Country of ref document: JP

Kind code of ref document: A

WWE Wipo information: entry into national phase

Ref document number: 14395879

Country of ref document: US

WWE Wipo information: entry into national phase

Ref document number: 2013785968

Country of ref document: EP

121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 13785968

Country of ref document: EP

Kind code of ref document: A2

REG Reference to national code

Ref country code: BR

Ref legal event code: B01A

Ref document number: 112014026258

Country of ref document: BR

ENP Entry into the national phase

Ref document number: 112014026258

Country of ref document: BR

Kind code of ref document: A2

Effective date: 20141021