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    GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE
    32.
    发明专利
    GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE 未知

    公开(公告)号：CA2916866A1

    公开(公告)日：2016-07-09

    申请号：CA2916866

    申请日：2016-01-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

    IPC: F02K3/06 ,  F02C3/04 ,  F02C7/36

    Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in a second direction opposed to the first direction.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    36.
    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.

    КОНСТРУКЦИЯ РЕДУКТОРНОГО ТУРБОВЕНТИЛЯТОРНОГО ГАЗОТУРБИННОГО ДВИГАТЕЛЯ
    37.
    发明专利
    КОНСТРУКЦИЯ РЕДУКТОРНОГО ТУРБОВЕНТИЛЯТОРНОГО ГАЗОТУРБИННОГО ДВИГАТЕЛЯ 未知

    公开(公告)号：RU2633495C2

    公开(公告)日：2017-10-12

    申请号：RU2014134792

    申请日：2013-01-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KHYUSTON DEVID P ,  KUPRATIS DANIEL BERNARD ,  SHVARTS FREDERIK M

    IPC: F02K3/02

    Abstract: Газотурбинныйдвигательсодержитвентилятор, выполненныйс возможностьювращениявокругоси, компрессорнуюсекцию, камерусгорания, сообщающуюсяпотекучейсредес компрессорнойсекцией, итурбиннуюсекцию, сообщающуюсяпотекучейсредес камеройсгорания. Турбиннаясекциясодержиттурбинуприводавентилятораи вторуютурбину. Втораятурбинарасположенапередтурбинойприводавентилятора. Турбинаприводавентиляторасодержитпоменьшеймеретриротора, приэтомпоменьшеймереодинроторимеетрадиус (R) каналаи эффективныйрадиус (r) обода, аотношение r/R составляетотприблизительно 2,00 доприблизительно 2,30. Системаизмененияскоростиприводитсяв действиетурбинойприводавентиляторадляобеспечениявращениявентиляторавокругоси. 2 н. и 25 з.п. ф-лы, 1 табл., 12 ил.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    38.
    发明专利
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 未知

    公开(公告)号：CA2857357C

    公开(公告)日：2017-06-06

    申请号：CA2857357

    申请日：2013-01-30

    Applicant: UNITED TECHNOLOGIES CORP

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

    IPC: F02C7/36 ,  F01D1/24 ,  F01D5/06 ,  F02C3/04 ,  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.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    40.
    发明专利
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 未知

    公开(公告)号：CA2933432A1

    公开(公告)日：2017-01-01

    申请号：CA2933432

    申请日：2016-06-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

    IPC: F02C7/36

    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.

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