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    Multi core geared gas turbine engine
    1.
    发明授权
    Multi core geared gas turbine engine 有权

    公开(公告)号：US11781478B2

    公开(公告)日：2023-10-10

    申请号：US17571720

    申请日：2022-01-10

    Applicant: Raytheon Technologies Corporation

    Inventor： Marc J. Muldoon ,  Joseph B. Staubach ,  Jesse M. Chandler ,  Neil Terwilliger ,  Gabriel L. Suciu

    IPC: F02K3/12 ,  F02C6/20 ,  F02C7/36

    CPC classification number: F02C6/20 ,  F02C7/36 ,  F02K3/12

    Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.

    Turbine section of high bypass turbofan
    4.
    发明授权
    Turbine section of high bypass turbofan 有权

    公开(公告)号：US11480108B2

    公开(公告)日：2022-10-25

    申请号：US17230271

    申请日：2021-04-14

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C7/36 ,  F02C3/107 ,  F02C9/18 ,  F01D11/12 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F02K3/075 ,  F02K3/06 ,  F04D29/32 ,  F04D29/54

    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including a circumferential array of fan blades, a compressor in fluid communication with the fan, the compressor including a low pressure compressor section and a high pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the a low pressure compressor section inlet, a turbine in fluid communication with the combustor, the turbine having a high pressure turbine section and a low pressure turbine that drives the fan, a speed reduction mechanism coupled to the fan and rotatable by the low pressure turbine section to allow the low pressure turbine section to turn faster than the fan, wherein the low pressure turbine section includes a maximum gas path radius and the fan blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is between 0.50 and 0.55, or is greater than 0.55 and less than or equal to 0.65.

    Low pressure environmental control system with safe pylon transit
    8.
    发明授权
    Low pressure environmental control system with safe pylon transit 有权

    公开(公告)号：US11072429B2

    公开(公告)日：2021-07-27

    申请号：US16152929

    申请日：2018-10-05

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: B64D13/06 ,  B64D27/26 ,  F02K3/04 ,  F02C6/08 ,  F02C7/20

    Abstract: A disclosed gas turbine engine includes a fan section delivering air into a compressor section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into 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. 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.

    SEALED CMC TURBINE CASE
    9.
    发明申请
    SEALED CMC TURBINE CASE 有权

    公开(公告)号：US20210087948A1

    公开(公告)日：2021-03-25

    申请号：US17016749

    申请日：2020-09-10

    Applicant: Raytheon Technologies Corporation

    Inventor： Gabriel L. Suciu

    IPC: F01D25/24 ,  F01D5/28 ,  F01D11/20 ,  F01D11/18

    Abstract: An embodiment of a turbine engine outer case ring assembly includes a substantially circular first main body and a sealant layer covering at least a main gas-facing surface of the inner gas path side, the sealant layer having at least one coating sufficient to prevent infiltration of working gas into pores of the main body.

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