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    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    44.
    发明专利
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 未知

    公开(公告)号：SG11201402667QA

    公开(公告)日：2014-09-26

    申请号：SG11201402667Q

    申请日：2013-01-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

    IPC: F02K3/06

    Abstract: A gas turbine engine (20) typically includes a fan section (22), a compressor section (24), a combustor section (26) and a turbine section (28). A speed reduction device such as an epicyclical gear assembly (48) may be utilized to drive the fan section (22) such that the fan section (22) may rotate at a speed different than the turbine section (28) so as to increase the overall propulsive efficiency of the engine (20). In such engine architectures, a shaft (40) driven by a fan drive turbine section (46) provides an input to the epicyclical gear assembly (48) that drives the fan section (22) at a speed different than the fan drive turbine section (46) such that both the fan drive turbine section (46) and the fan section (22) can rotate at closer to optimal speeds providing increased performance attributes and performance.

    ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ
    48.
    发明专利
    ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ 未知

    公开(公告)号：RU2687861C9

    公开(公告)日：2019-08-01

    申请号：RU2014131372

    申请日：2012-12-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  MERRI BRIAN D ,  DYE CHRISTOPHER M ,  JOHNSON STEVEN B ,  SCHWARZ FREDERICK M

    IPC: F02K3/06 ,  B64D27/40 ,  F02K1/06

    Abstract: Газотурбинныйдвигательсодержитредуктор, расположенныйвдольпродольнойосидвигателя, каскад, гондолувентилятора, внутреннююгондолу, вентилятор, вентиляторноесоплои внутреннийконтур. Каскадвыполненс возможностьюприведенияв действиередуктораи содержиттурбинунизкогодавленияс числомступенейоттрехдошести. Гондолавентилятораустановленавокругвнутреннейгондолыи определяеттрактдлявоздушногопотоканаружногоконтуравентилятора, причемстепеньдвухконтурностипревышаетшесть. Вентиляторноесопловыполненос изменяемойплощадьюсеченияи свозможностьюперемещенияв осевомнаправленииотносительногондолывентиляторас цельюизмененияплощадивыходногосечениявентиляторногосоплаи регулированиявоздушногопотокав наружномконтуревентиляторавовремяработыдвигателя. Вентиляторвыполненс возможностьювращениясоскоростьювентиляторавокругпродольнойосии приводитсяв действиетурбинойнизкогодавленияс помощьюредуктора, причемскоростьвентилятораменьшескороститурбинынизкогодавления. Внутреннийконтурокруженвнутреннейгондолой. Редукторимеетпередаточноеотношение, котороебольшеилиравно 2,3, причемминимальноесоотношениедавленийв вентиляторесоставляетменее 1,45, аминимальнаяприведеннаяокружнаяскоростьлопаткивентиляторасоставляетменее 1150 фут/сек (350,5 м/сек). Изобретениепозволяетобеспечитьболеелегкуюконструкциюгазотурбинногодвигателя, атакжеснизитьшум, производимыйвентилятором. 12 з.п. ф-лы, 15 ил.

    GEARED TURBOFAN ENGINE WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT
    49.
    发明专利
    GEARED TURBOFAN ENGINE WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT 未知

    公开(公告)号：CA2895885C

    公开(公告)日：2017-06-20

    申请号：CA2895885

    申请日：2015-06-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  SUCIU GABRIEL L

    IPC: F02C9/18 ,  B64D13/02 ,  B64D33/00 ,  F02C3/06 ,  F02C7/36

    Abstract: A gas turbine engine assembly includes a fan section delivering air into a main compressor section. The main compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. A pylon supports the gas turbine engine. An environmental control system includes a higher pressure tap at a higher pressure location in the main compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. The pylon includes a lowermost surface and the higher pressure tap does not extend above a plane including the lowermost surface. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use. An environmental control system is also disclosed.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    50.
    发明专利
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 未知

    公开(公告)号：CA2951916C

    公开(公告)日：2017-05-09

    申请号：CA2951916

    申请日：2013-01-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOUSTON DAVID P ,  KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

    IPC: F02C7/36 ,  F01D5/06 ,  F02C3/107 ,  F02K3/06

    Abstract: A gas turbine engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The second turbine is disposed forward of the fan drive turbine. The fan drive turbine includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system is driven by the fan drive turbine for rotating the fan about the axis.

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