SG10201401514UA - Geared architecture for high speed and small volume fan drive turbine - Google Patents

Geared architecture for high speed and small volume fan drive turbine

Info

Publication number
SG10201401514UA
SG10201401514UA SG10201401514UA SG10201401514UA SG10201401514UA SG 10201401514U A SG10201401514U A SG 10201401514UA SG 10201401514U A SG10201401514U A SG 10201401514UA SG 10201401514U A SG10201401514U A SG 10201401514UA SG 10201401514U A SG10201401514U A SG 10201401514UA
Authority
SG
Singapore
Prior art keywords
fan drive
high speed
small volume
geared architecture
drive turbine
Prior art date
Application number
SG10201401514UA
Other languages
English (en)
Inventor
e mccune Michael
Husband Jason
M Schwarz Frederick
Bernard Kupratis Daniel
L Suciu Gabriel
K Ackermann William
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=50238097&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=SG10201401514U(A) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Priority claimed from US13/908,177 external-priority patent/US9631558B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of SG10201401514UA publication Critical patent/SG10201401514UA/en

Links

Classifications

    • 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
    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • 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
    • 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
    • F02K3/068—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 being characterised by a short axial length relative to the diameter
    • 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
SG10201401514UA 2013-06-03 2014-04-14 Geared architecture for high speed and small volume fan drive turbine SG10201401514UA (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/908,177 US9631558B2 (en) 2012-01-03 2013-06-03 Geared architecture for high speed and small volume fan drive turbine

Publications (1)

Publication Number Publication Date
SG10201401514UA true SG10201401514UA (en) 2015-01-29

Family

ID=50238097

Family Applications (1)

Application Number Title Priority Date Filing Date
SG10201401514UA SG10201401514UA (en) 2013-06-03 2014-04-14 Geared architecture for high speed and small volume fan drive turbine

Country Status (6)

Country Link
EP (6) EP2811120B1 (fr)
JP (1) JP5732562B2 (fr)
CN (1) CN104213985B (fr)
CA (1) CA2845618C (fr)
RU (1) RU2639821C2 (fr)
SG (1) SG10201401514UA (fr)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9410608B2 (en) 2011-06-08 2016-08-09 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US9239012B2 (en) 2011-06-08 2016-01-19 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US9631558B2 (en) 2012-01-03 2017-04-25 United Technologies Corporation Geared architecture for high speed and small volume fan drive turbine
US10287914B2 (en) 2012-01-31 2019-05-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
US20130192263A1 (en) 2012-01-31 2013-08-01 Gabriel L. Suciu Gas turbine engine with high speed low pressure turbine section
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
EP2811120B1 (fr) 2013-06-03 2017-07-12 United Technologies Corporation Architecture à engrenages pour l'entraînement d'une soufflante par une turbine de petit volume et grande vitesse
US20160333786A1 (en) * 2015-05-13 2016-11-17 General Electric Company System for supporting rotor shafts of an indirect drive turbofan engine
FR3039132B1 (fr) * 2015-07-20 2017-08-11 Airbus Operations Sas Ensemble moteur a helice a axe horizontal pour aeronef
EP3165754A1 (fr) * 2015-11-03 2017-05-10 United Technologies Corporation Moteur à turbine à gaz ayant une section basse pression haute vitesse et éléments de support de palier
CN105443270B (zh) * 2015-12-29 2017-11-03 中国航空工业集团公司沈阳发动机设计研究所 一种航空涡轮风扇发动机
US10364752B2 (en) 2016-05-17 2019-07-30 General Electric Company System and method for an integral drive engine with a forward main gearbox
US10815881B2 (en) 2017-09-20 2020-10-27 General Electric Company Counter rotating turbine with reversing speed reduction assembly
GB201804128D0 (en) * 2018-03-15 2018-05-02 Rolls Royce Plc Electrical power generator system
IT201800005822A1 (it) * 2018-05-29 2019-11-29 Attacco di un gruppo ingranaggio per un motore a turbina a gas
CN113495001B (zh) * 2020-04-02 2022-06-21 中国航发商用航空发动机有限责任公司 压气机盘腔卷吸流量比的测量装置及方法
CN113833573B (zh) * 2020-06-24 2022-08-16 中国航发商用航空发动机有限责任公司 双转子双支点燃气轮机
US11428160B2 (en) * 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IL82840A0 (en) * 1986-07-15 1987-12-20 Savyon Diagnostics Ltd Method and compositions for the determination of occult blood
US5433674A (en) 1994-04-12 1995-07-18 United Technologies Corporation Coupling system for a planetary gear train
GB2322914B (en) * 1997-03-05 2000-05-24 Rolls Royce Plc Ducted fan gas turbine engine
US6223616B1 (en) 1999-12-22 2001-05-01 United Technologies Corporation Star gear system with lubrication circuit and lubrication method therefor
US7338259B2 (en) 2004-03-02 2008-03-04 United Technologies Corporation High modulus metallic component for high vibratory operation
GB0406174D0 (en) * 2004-03-19 2004-04-21 Rolls Royce Plc Turbine engine arrangement
US7631484B2 (en) * 2006-03-13 2009-12-15 Rollin George Giffin High pressure ratio aft fan
US20070214795A1 (en) * 2006-03-15 2007-09-20 Paul Cooker Continuous real time EGT margin control
BE1017135A3 (nl) 2006-05-11 2008-03-04 Hansen Transmissions Int Een tandwielkast voor een windturbine.
US8585538B2 (en) * 2006-07-05 2013-11-19 United Technologies Corporation Coupling system for a star gear train in a gas turbine engine
US7704178B2 (en) * 2006-07-05 2010-04-27 United Technologies Corporation Oil baffle for gas turbine fan drive gear system
RU2330170C2 (ru) * 2006-09-11 2008-07-27 Открытое акционерное общество "Авиадвигатель" Двухконтурный газотурбинный двигатель сверхвысокой степени двухконтурности
US7950237B2 (en) * 2007-06-25 2011-05-31 United Technologies Corporation Managing spool bearing load using variable area flow nozzle
US8844265B2 (en) * 2007-08-01 2014-09-30 United Technologies Corporation Turbine section of high bypass turbofan
US8297916B1 (en) * 2011-06-08 2012-10-30 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US9631558B2 (en) 2012-01-03 2017-04-25 United Technologies Corporation Geared architecture for high speed and small volume fan drive turbine
US9133729B1 (en) * 2011-06-08 2015-09-15 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
CA2789465C (fr) * 2011-10-27 2016-08-09 United Technologies Corporation Architecture de corps central avant de moteur a turbine a gaz
CA2789325C (fr) * 2011-10-27 2015-04-07 United Technologies Corporation Architecture de corps central avant de moteur a turbine a gaz
US20130192266A1 (en) 2012-01-31 2013-08-01 United Technologies Corporation Geared turbofan gas turbine engine architecture
US20130259653A1 (en) * 2012-04-02 2013-10-03 Frederick M. Schwarz Geared turbofan engine with power density range
EP2811120B1 (fr) 2013-06-03 2017-07-12 United Technologies Corporation Architecture à engrenages pour l'entraînement d'une soufflante par une turbine de petit volume et grande vitesse

Also Published As

Publication number Publication date
EP3467273A1 (fr) 2019-04-10
EP2811120A1 (fr) 2014-12-10
CN104213985A (zh) 2014-12-17
CA2845618A1 (fr) 2014-05-22
EP2949882A1 (fr) 2015-12-02
RU2014110925A (ru) 2015-09-27
EP2949881B1 (fr) 2018-08-29
EP3467272A1 (fr) 2019-04-10
EP4209661A2 (fr) 2023-07-12
EP2949882B1 (fr) 2017-08-23
EP2949881A1 (fr) 2015-12-02
JP2014234822A (ja) 2014-12-15
RU2639821C2 (ru) 2017-12-22
BR102014007285A2 (pt) 2015-05-26
EP4209661A3 (fr) 2023-11-22
CN104213985B (zh) 2017-09-22
JP5732562B2 (ja) 2015-06-10
EP2811120B1 (fr) 2017-07-12
CA2845618C (fr) 2015-06-02

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