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    motor de turbina a gás
    122.
    发明专利
    motor de turbina a gás 未知

    公开(公告)号：BR102016005922A2

    公开(公告)日：2016-10-25

    申请号：BR102016005922

    申请日：2016-03-17

    Applicant: UNITED TECHNOLOGIES CORP

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

    IPC: F02C3/10 ,  F02C6/00 ,  F02K3/00 ,  F02K3/072 ,  F16H1/00

    Abstract: um motor de turbina a gás inclui uma ventoinha passível de girar sobre um eixo, uma seção de compressor, um combustor em comunicação fluida com a seção de compressor, e uma seção de turbina em comunicação fluida com o combustor. a seção de turbina inclui uma turbina de acionamento de ventoinha e uma segunda turbina. a segunda turbina está disposta à frente da turbina de acionamento de ventoinha. a turbina de acionamento de ventoinha inclui pelo menos três rotores e pelo menos um rotor tendo um raio de orifício (r) e um raio de rebordo energizado (r), e uma razão de r/r está entre cerca de 2,00 e cerca de 2,30. um sistema de mudança de velocidade é acionado pela turbina de acionamento de ventoinha para girar a ventoinha sobre o eixo.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    123.
    发明专利
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 未知

    公开(公告)号：CA2857359C

    公开(公告)日：2016-06-28

    申请号：CA2857359

    申请日：2013-01-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

    IPC: F02C7/06 ,  F02C3/107 ,  F02C7/32 ,  F02C7/36 ,  F02K3/072

    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    124.
    发明专利
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 未知

    公开(公告)号：CA2854082C

    公开(公告)日：2016-04-26

    申请号：CA2854082

    申请日：2013-01-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

    IPC: F02K3/06 ,  F02C3/113 ,  F02C7/36 ,  F02K3/072

    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE
    125.
    发明专利
    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE 未知

    公开(公告)号：CA2853694C

    公开(公告)日：2016-03-22

    申请号：CA2853694

    申请日：2013-01-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SMITH PETER G ,  OCHS STUART S ,  SCHWARZ FREDERICK M

    IPC: F01D17/14 ,  F02C9/20 ,  F02K1/12 ,  F02K3/06 ,  F02K3/075

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation, and a gear system driven by a core engine within the core nacelle to drive a fan within the fan nacelle, the gear system defines a gear reduction ratio of greater than or equal to about 2.3.

    GEARED TURBOFAN ENGINE WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT
    126.
    发明专利
    GEARED TURBOFAN ENGINE WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT 未知

    公开(公告)号：CA2895885A1

    公开(公告)日：2015-12-27

    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.

    motor de turbina a gás
    128.
    发明专利
    motor de turbina a gás 未知

    公开(公告)号：BR102014020190A2

    公开(公告)日：2015-09-22

    申请号：BR102014020190

    申请日：2014-08-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M ,  SUCIU GABRIEL L ,  HUSBAND JASON ,  MCCUNE MICHAEL E ,  SHERIDAN WILLIAM G ,  ACKERMANN WILLIAM K

    IPC: F02C3/113

    Abstract: motor de turbina a gás. um sistema de engrenagem de acionamento da ventoinha para um motor de turbina a gás inclui um sistema de engrenagem que proporciona uma reducão de velocidade entre uma turbina de acionamento da ventoinha e uma ventoinha e uni apoio flexivelmente suportando porções do sistema de engrenagem. uni sistenía de lubrificação suportando o sistema de engrenageni de acionamento da ventoinha fornece o lubrificante para o sistema de engrenagem e remove energia térmica produzida pelo sistema de engrenagem.o sistema de lubrificação inclui uma capacidade para a remoção de energia igual a menos do cerca de 2¨% de entrada de energia para o sistema de engrenagem.

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