WO2014204526A3 - Family of geared turbo fan engines - Google Patents

Family of geared turbo fan engines Download PDF

Info

Publication number
WO2014204526A3
WO2014204526A3 PCT/US2014/015500 US2014015500W WO2014204526A3 WO 2014204526 A3 WO2014204526 A3 WO 2014204526A3 US 2014015500 W US2014015500 W US 2014015500W WO 2014204526 A3 WO2014204526 A3 WO 2014204526A3
Authority
WO
WIPO (PCT)
Prior art keywords
engines
fan
distinct
family
turbo fan
Prior art date
Application number
PCT/US2014/015500
Other languages
French (fr)
Other versions
WO2014204526A2 (en
Inventor
Karl HASEL
Jessica TSAY
Original Assignee
United Technologies Corporation
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 Corporation filed Critical United Technologies Corporation
Publication of WO2014204526A2 publication Critical patent/WO2014204526A2/en
Publication of WO2014204526A3 publication Critical patent/WO2014204526A3/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
    • 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
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

A method of configuring a plurality of substantially mutually distinct gas turbine engines includes the steps of providing each of the engines with respective ones of a plurality of substantially mutually distinct propulsors. Each include a fan and a fan drive gear architecture. Each of the engines is provided with respective ones of a plurality of substantially mutually alike gas generators, each with a compressor section, combustor, and a turbine section configured to drive at a common speed. The plurality of mutually distinct propulsors have a mutually distinct diameter fan and/or fan drive architecture with distinct gear reduction ratio.
PCT/US2014/015500 2013-02-17 2014-02-10 Family of geared turbo fan engines WO2014204526A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201361765738P 2013-02-17 2013-02-17
US61/765,738 2013-02-17

Publications (2)

Publication Number Publication Date
WO2014204526A2 WO2014204526A2 (en) 2014-12-24
WO2014204526A3 true WO2014204526A3 (en) 2015-03-05

Family

ID=52105463

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2014/015500 WO2014204526A2 (en) 2013-02-17 2014-02-10 Family of geared turbo fan engines

Country Status (1)

Country Link
WO (1) WO2014204526A2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11578663B2 (en) 2018-09-11 2023-02-14 Pratt & Whitney Canada Corp. Engine family platform design
US11629665B2 (en) * 2018-09-11 2023-04-18 Pratt & Whitney Canada Corp. Gas turbine engine and method of creating classes of same

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040112041A1 (en) * 2002-12-13 2004-06-17 Chi Law Coated journals
US20080098713A1 (en) * 2006-10-27 2008-05-01 Robert Joseph Orlando Gas turbine engine assembly and methods of assembling same
US20120192570A1 (en) * 2010-10-12 2012-08-02 Mccune Michael E Planetary gear system arrangement with auxiliary oil system
US20120222397A1 (en) * 2007-07-27 2012-09-06 Smith Peter G Gas turbine engine with low fan pressure ratio
US20120315130A1 (en) * 2007-09-21 2012-12-13 Hasel Karl L Gas turbine engine compressor arrangement

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040112041A1 (en) * 2002-12-13 2004-06-17 Chi Law Coated journals
US20080098713A1 (en) * 2006-10-27 2008-05-01 Robert Joseph Orlando Gas turbine engine assembly and methods of assembling same
US20120222397A1 (en) * 2007-07-27 2012-09-06 Smith Peter G Gas turbine engine with low fan pressure ratio
US20120315130A1 (en) * 2007-09-21 2012-12-13 Hasel Karl L Gas turbine engine compressor arrangement
US20120192570A1 (en) * 2010-10-12 2012-08-02 Mccune Michael E Planetary gear system arrangement with auxiliary oil system

Also Published As

Publication number Publication date
WO2014204526A2 (en) 2014-12-24

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