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WO2018026408A3 - Method and system for a two frame gas turbine engine - Google Patents

Method and system for a two frame gas turbine engine Download PDF

Info

Publication number
WO2018026408A3
WO2018026408A3 PCT/US2017/032319 US2017032319W WO2018026408A3 WO 2018026408 A3 WO2018026408 A3 WO 2018026408A3 US 2017032319 W US2017032319 W US 2017032319W WO 2018026408 A3 WO2018026408 A3 WO 2018026408A3
Authority
WO
WIPO (PCT)
Prior art keywords
compressor
turbine
engine
gas turbine
positioned axially
Prior art date
Application number
PCT/US2017/032319
Other languages
French (fr)
Other versions
WO2018026408A2 (en
Inventor
Brandon Wayne Miller
Thomas Ory MONIZ
Jeffrey Donald Clements
Joseph George ROSE
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 CN201780032101.9A priority Critical patent/CN109196187B/en
Priority to EP17817936.2A priority patent/EP3464833A2/en
Publication of WO2018026408A2 publication Critical patent/WO2018026408A2/en
Publication of WO2018026408A3 publication Critical patent/WO2018026408A3/en
Anticipated expiration legal-status Critical
Ceased 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
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F02C7/06—Arrangements of bearings; Lubricating
    • 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
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The gas turbine engine includes a core engine including a HP compressor, a combustor, and a HP turbine in a serial flow arrangement, A LP turbine is positioned axially aft of the core engine and includes a plurality of stages of rotor blades. A last stage of rotor blades includes a low swirl rotor blade stage. A LP compressor is positioned axially forward of the core engine and coupled to the LP turbine through a gearbox. The LP compressor is positioned radially outward from the gearbox. A fan assembly is directly coupled to the LP compressor such that the fan assembly and the LP compressor rotate at the same speed. An engine frame assembly includes a forward fan frame member positioned axially between the LP compressor and the HP compressor. The engine frame assembly also includes a turbine center frame member positioned between the HP turbine and the LP turbine.
PCT/US2017/032319 2016-05-25 2017-05-12 Method and system for a two frame gas turbine engine Ceased WO2018026408A2 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201780032101.9A CN109196187B (en) 2016-05-25 2017-05-12 Method and system for a two frame gas turbine engine
EP17817936.2A EP3464833A2 (en) 2016-05-25 2017-05-12 Method and system for a two frame gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201615164726A 2016-05-25 2016-05-25
US15/164,726 2016-05-25

Publications (2)

Publication Number Publication Date
WO2018026408A2 WO2018026408A2 (en) 2018-02-08
WO2018026408A3 true WO2018026408A3 (en) 2018-04-26

Family

ID=60766124

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2017/032319 Ceased WO2018026408A2 (en) 2016-05-25 2017-05-12 Method and system for a two frame gas turbine engine

Country Status (3)

Country Link
EP (1) EP3464833A2 (en)
CN (1) CN109196187B (en)
WO (1) WO2018026408A2 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017211649A1 (en) * 2017-07-07 2019-01-10 MTU Aero Engines AG Gas turbine with a high-speed low-pressure turbine and a turbine housing
US11156097B2 (en) * 2019-02-20 2021-10-26 General Electric Company Turbomachine having an airflow management assembly
GB201903257D0 (en) * 2019-03-11 2019-04-24 Rolls Royce Plc Efficient gas turbine engine installation and operation
US11174916B2 (en) 2019-03-21 2021-11-16 Pratt & Whitney Canada Corp. Aircraft engine reduction gearbox
FR3097012B1 (en) * 2019-06-06 2022-01-21 Safran Aircraft Engines Method for regulating an acceleration of a turbomachine
US11572838B2 (en) * 2020-09-29 2023-02-07 General Electric Company Accessory gearbox for a turbine engine
US11560840B2 (en) * 2020-10-16 2023-01-24 General Electric Company Damper engine mount links
US20220259985A1 (en) * 2021-02-15 2022-08-18 General Electric Company Open rotor turbomachinery engines
US11268453B1 (en) 2021-03-17 2022-03-08 Pratt & Whitney Canada Corp. Lubrication system for aircraft engine reduction gearbox

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130186058A1 (en) * 2012-01-24 2013-07-25 William G. Sheridan Geared turbomachine fan and compressor rotation
US20150143794A1 (en) * 2013-11-22 2015-05-28 United Technologies Corporation Geared Turbofan Engine Gearbox Arrangement
EP2975226A1 (en) * 2014-07-15 2016-01-20 United Technologies Corporation Turbine section support for a gas turbine engine
US20160084105A1 (en) * 2014-09-24 2016-03-24 United Technologies Corporation Fan drive gear system

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7513102B2 (en) * 2005-06-06 2009-04-07 General Electric Company Integrated counterrotating turbofan
US7926259B2 (en) * 2006-10-31 2011-04-19 General Electric Company Turbofan engine assembly and method of assembling same
US8678743B1 (en) * 2013-02-04 2014-03-25 United Technologies Corporation Method for setting a gear ratio of a fan drive gear system of a gas turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130186058A1 (en) * 2012-01-24 2013-07-25 William G. Sheridan Geared turbomachine fan and compressor rotation
US20150143794A1 (en) * 2013-11-22 2015-05-28 United Technologies Corporation Geared Turbofan Engine Gearbox Arrangement
EP2975226A1 (en) * 2014-07-15 2016-01-20 United Technologies Corporation Turbine section support for a gas turbine engine
US20160084105A1 (en) * 2014-09-24 2016-03-24 United Technologies Corporation Fan drive gear system

Also Published As

Publication number Publication date
WO2018026408A2 (en) 2018-02-08
CN109196187B (en) 2021-12-07
CN109196187A (en) 2019-01-11
EP3464833A2 (en) 2019-04-10

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