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    HIGH TURNING FAN EXIT STATOR
    1.
    发明公开
    HIGH TURNING FAN EXIT STATOR 审中-实审

    公开(公告)号：EP4306788A3

    公开(公告)日：2024-04-17

    申请号：EP23212765.4

    申请日：2013-01-28

    申请人： RTX Corporation

    发明人： BRILLIANT, Lisa I. ,  ROSE, Becky E. ,  DONG, Yuan ,  BALAMUCKI, Stanley J.

    IPC分类号： F02K3/072 ,  F02C7/36

    CPC分类号： F01D5/141 ,  F05D2220/3620130101 ,  F02K3/072 ,  F02C7/36 ,  Y02T50/60

    摘要： A turbine engine (20) includes a fan exit stator (62) located between a fan section (22) and a compressor section (24). The fan exit stator (62) includes an airfoil (72) that defines an entrance angle (J°) with respect to a leading edge (74) of the airfoil (72) and a line parallel to the longitudinal axis (A), and defines an exit angle (K°) with respect to a trailing edge (76) of the airfoil (72) and a line parallel to the longitudinal axis (A). The difference between the entrance angle (J°) and the exit angle (K°) is between about 45° and about 65°. A portion of the compressor section (24) is driven by a portion of a turbine section (28).

    TURBOFAN WITH AIR-COOLED HEAT EXCHANGER IN THE INLET FLOW UPSTREAM OF THE FAN
    6.
    发明公开
    TURBOFAN WITH AIR-COOLED HEAT EXCHANGER IN THE INLET FLOW UPSTREAM OF THE FAN 审中-公开

    公开(公告)号：EP3981970A1

    公开(公告)日：2022-04-13

    申请号：EP21200618.3

    申请日：2021-10-04

    申请人： Rolls-Royce plc

    发明人： Bradbrook, Stephen ,  Goodhand, Martin ,  Hield, Paul ,  Parsley, Andrew ,  Wong, Natalie ,  Corin, Robert ,  Binnington, Thomas

    IPC分类号： F02C7/04 ,  F02C7/047 ,  F02C7/14 ,  F28D1/02 ,  F01D9/06 ,  F01D25/02 ,  F02K3/072 ,  F01D9/04

    摘要： A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module comprises a plurality of radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger module is divided between a set of vane airflows through each of the hollow vanes, and a set of channel airflows through each of the channels. Each vane airflow has a vane mass flow rate Flow Vane ,, and each channel air flow has a channel mass flow rate Flow Chan . Each of the hollow vanes accommodates at least one heat transfer element for the transfer of heat from a first fluid contained within the or each heat transfer element to the corresponding vane airflow passing over a surface of the or each heat transfer element.
    Each hollow vane comprises, in axial flow sequence, an inlet portion, a heat transfer portion, and an exhaust portion, with the inlet portion comprising a diffuser element, and the heat transfer portion comprising at least one heat transfer element. The diffuser element is configured to cause the vane mass flow rate Flow Vane to be lower than the channel mass flow rate Flow Chan by a user-defined margin.

    TURBOFAN WITH AIR-COOLED HEAT EXCHANGER IN THE INLET FLOW UPSTREAM OF THE FAN
    7.
    发明公开
    TURBOFAN WITH AIR-COOLED HEAT EXCHANGER IN THE INLET FLOW UPSTREAM OF THE FAN 审中-公开

    公开(公告)号：EP3981968A1

    公开(公告)日：2022-04-13

    申请号：EP21198481.0

    申请日：2021-09-23

    申请人： Rolls-Royce plc

    发明人： Bradbrook, Stephen J ,  Goodhand, Martin N ,  Hield, Paul M ,  Parsley, Andrew ,  Wong, Natalie C ,  Corin, Robert J ,  Binnington, Thomas S

    IPC分类号： F02C7/04 ,  F02C7/047 ,  F02C7/14 ,  F28D1/02 ,  F01D9/06 ,  F01D25/02 ,  F02K3/072 ,  F01D9/04

    摘要： A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module comprises a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger module is divided between a set of vane airflows through each of the hollow vanes and a set of channel airflows through each of the channels. Each vane airflow having a vane mass flow rate Flow Vane , and each channel air flow has a channel mass flow rate Flow Chan . At least one of the hollow vanes accommodates at least one heat transfer element for the transfer of heat from a first fluid contained within the or each heat transfer element to the or each corresponding vane airflow passing over a surface of the or each heat transfer element.
    In use, a Vane Airflow Ratio parameter V AR is defined as: VAR = Flow VaneTot Flow ChanTot where:
    Flow VaneTot = total mass flow rate of the vane mass flow rates, Flow Vane ; and
    Flow ChanTot = total mass flow rate of the channel mass flow rates, Flow Chan ; and the V AR parameter is in the range of 0.05 to 3.0.