EP2971726A4 - Thrust efficient turbofan engine - Google Patents

Thrust efficient turbofan engine

Info

Publication number
EP2971726A4
EP2971726A4 EP14807688.8A EP14807688A EP2971726A4 EP 2971726 A4 EP2971726 A4 EP 2971726A4 EP 14807688 A EP14807688 A EP 14807688A EP 2971726 A4 EP2971726 A4 EP 2971726A4
Authority
EP
European Patent Office
Prior art keywords
turbofan engine
thrust
efficient turbofan
thrust efficient
engine
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.)
Withdrawn
Application number
EP14807688.8A
Other languages
German (de)
French (fr)
Other versions
EP2971726A2 (en
Inventor
Jayant Sabnis
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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
Priority claimed from US13/854,225 external-priority patent/US9624827B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2971726A2 publication Critical patent/EP2971726A2/en
Publication of EP2971726A4 publication Critical patent/EP2971726A4/en
Withdrawn legal-status Critical Current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
    • 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
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP14807688.8A 2013-03-15 2014-03-14 Thrust efficient turbofan engine Withdrawn EP2971726A4 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US201361787321P 2013-03-15 2013-03-15
US13/854,225 US9624827B2 (en) 2013-03-15 2013-04-01 Thrust efficient turbofan engine
US201361884327P 2013-09-30 2013-09-30
PCT/US2014/027105 WO2014197075A2 (en) 2013-03-15 2014-03-14 Thrust efficient turbofan engine

Publications (2)

Publication Number Publication Date
EP2971726A2 EP2971726A2 (en) 2016-01-20
EP2971726A4 true EP2971726A4 (en) 2016-11-16

Family

ID=52008711

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14807688.8A Withdrawn EP2971726A4 (en) 2013-03-15 2014-03-14 Thrust efficient turbofan engine

Country Status (2)

Country Link
EP (1) EP2971726A4 (en)
WO (1) WO2014197075A2 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015048464A1 (en) 2013-09-30 2015-04-02 United Technologies Corporation Thrust efficient turbofan engine
GB201810885D0 (en) * 2018-07-03 2018-08-15 Rolls Royce Plc High efficiency gas turbine engine
GB201813086D0 (en) 2018-08-10 2018-09-26 Rolls Royce Plc Efficient gas turbine engine
GB201813079D0 (en) 2018-08-10 2018-09-26 Rolls Royce Plc Effcient gas turbine engine
GB201813082D0 (en) 2018-08-10 2018-09-26 Rolls Royce Plc Efficient gas turbine engine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110289900A1 (en) * 2007-10-15 2011-12-01 Stern Alfred M Thrust reversing variable area nozzle
US20120171018A1 (en) * 2007-09-21 2012-07-05 Hasel Karl L Gas turbine engine compressor arrangement

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120124964A1 (en) * 2007-07-27 2012-05-24 Hasel Karl L Gas turbine engine with improved fuel efficiency
US8943796B2 (en) * 2011-06-28 2015-02-03 United Technologies Corporation Variable cycle turbine engine
US9506422B2 (en) * 2011-07-05 2016-11-29 United Technologies Corporation Efficient, low pressure ratio propulsor for gas turbine engines

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120171018A1 (en) * 2007-09-21 2012-07-05 Hasel Karl L Gas turbine engine compressor arrangement
US20110289900A1 (en) * 2007-10-15 2011-12-01 Stern Alfred M Thrust reversing variable area nozzle

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
D P EDKINS ET AL: "NASA CR-120914 TF34 TURBOFAN QUIET ENGINE STUDY FINAL REPORT", 1 January 1972 (1972-01-01), XP055309404, Retrieved from the Internet <URL:http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19720026093.pdf> [retrieved on 20161011] *
DENÓS R ET AL: "GEARED FAN", AERO-ENGINE DESIGN: FROM STATE-OF-THE-ART TURBOFANS TOWARDS INNOVATIVE ARCHITECTURES - HARDCOVER. LECTURES SERIES 2008-03,, 3 March 2008 (2008-03-03), pages 1 - 26, XP003035510 *
MARK H WATERS ET AL: "NASA TECHNICAL MEMORANDUM ANALYSIS OF TURBOFAN PROPULSION SYSTEM WEIGHT AND DIMENSIGNS", 1 January 1977 (1977-01-01), XP055309222, Retrieved from the Internet <URL:http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19770012125.pdf> [retrieved on 20161010] *
See also references of WO2014197075A2 *

Also Published As

Publication number Publication date
WO2014197075A2 (en) 2014-12-11
EP2971726A2 (en) 2016-01-20
WO2014197075A3 (en) 2015-03-05

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