中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

124 records (took 0.024 seconds)

    motor de turbina a gás
    81.
    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.

    VARIABLE AREA TURBINE
    86.
    发明专利
    VARIABLE AREA TURBINE 未知

    公开(公告)号：SG11201403916SA

    公开(公告)日：2014-10-30

    申请号：SG11201403916S

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

    IPC: F02C7/042 ,  F01D17/16

    Abstract: A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    87.
    发明专利
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 未知

    公开(公告)号：SG11201403012PA

    公开(公告)日：2014-10-30

    申请号：SG11201403012P

    申请日：2013-01-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

    IPC: F02C7/06 ,  F01D25/16

    Abstract: A gas turbine engine (20) includes a fan (42), a compressor section (24), a combustor section (26) and a turbine section (28). A speed reduction device (48), such as an epicyclical gear assembly, may be utilized to drive the fan (42) at a speed different than the turbine section (28) so as to increase the overall propulsive efficiency of the engine (20). A shaft driven (30) by the turbine section (28) provides an input to the epicyclical gear assembly (48) such that both the turbine section (28) and the fan (42) can rotate at closer to optimal speeds providing increased performance attributes and performance.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    88.
    发明专利
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 未知

    公开(公告)号：SG11201402824RA

    公开(公告)日：2014-09-26

    申请号：SG11201402824R

    申请日：2013-01-30

    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 (42), a compressor section (24), a combustor section (26) and a turbine section (46). A speed reduction device (48) such as an epicyclical gear assembly may be utilized to drive the fan section (42) such that the fan section (42) may rotate at a speed different than the turbine section (46) so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft (40) driven by one of the turbine sections (46) provides an input to the epicyclical gear assembly that drives the fan section (42) at a speed different than the turbine section (46) such that both the turbine section (46) and the fan section (42) 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.

Patent Agency Ranking