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    VARIABLE AREA TURBINE
    134.
    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
    135.
    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
    137.
    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.

    ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO
    138.
    发明专利
    ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO 未知

    公开(公告)号：CA2898207A1

    公开(公告)日：2014-08-14

    申请号：CA2898207

    申请日：2014-02-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  MALECKI ROBERT E

    IPC: F02K3/068

    Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.

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