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    DRAW-THROUGH FAN ASSEMBLY AND HEAT EXCHANGER SYSTEM
    1.
    发明公开
    DRAW-THROUGH FAN ASSEMBLY AND HEAT EXCHANGER SYSTEM 审中-公开

    公开(公告)号：EP4464898A1

    公开(公告)日：2024-11-20

    申请号：EP24176738.3

    申请日：2024-05-17

    Applicant: Carrier Corporation

    Inventor： NGUYEN, Danny ,  BUSHNELL, Peter ,  DYGERT, Ryan ,  STARK, Michael ,  RAHHAL, Charbel

    IPC: F04D19/00 ,  F04D29/16 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  F04D29/60 ,  F04D29/64

    Abstract: A draw-through fan assembly and heat exchanger system configuration is disclosed, comprising a fan deck (102) adapted to mount the fan assembly (200), an axial fan (202) with a rotating shroud (212), a heat exchanger section located upstream of the fan (202) and the fan assembly (200), and a J-shaped inlet bell mouth (104) configured upstream of the fan deck (102) that is located within a space (304) between heat exchangers (302). Further, a motor (204) associated with the fan assembly (200) and one or more motor struts (106) are positioned upstream of the fan (202). The fan (202) is mounted on the bottom of the struts (106), such that once the fan-mounted assembly is configured at the outlet of the heat exchangers (302), the bell mouth (104) and fan (202) remain below the fan deck (102) and are disposed in a space (304) between the heat exchangers (302).

    ROTATING SEAL WITH OIL SLINGER
    2.
    发明公开
    ROTATING SEAL WITH OIL SLINGER 审中-公开

    公开(公告)号：EP4442965A1

    公开(公告)日：2024-10-09

    申请号：EP24168531.2

    申请日：2024-04-04

    Applicant: Hamilton Sundstrand Corporation

    Inventor： KRECKLOW, Joshua J.

    IPC: F01D11/00 ,  F04D29/16 ,  F16J15/34 ,  F01D25/00

    CPC classification number: F16J15/3404 ,  F01D25/183 ,  F05D2300/22420130101 ,  F05D2300/4320130101 ,  F05D2300/2120130101 ,  F04D29/124 ,  F04D29/128

    Abstract: A face seal assembly includes a rotationally fixed first component (12) at least partially defining an interior chamber (20) containing a volume of lubricant (24). The first component includes a rotationally fixed seal element (32). A rotatable second component (14) is rotatable about an axis of rotation relative to the first component. The second component includes a second component body (54) extending along the axis of rotation from the interior chamber to outside of the interior chamber. An axially facing component surface (48) is located in the interior chamber and is configured to engage with an axially-facing element surface (34) of the seal element to define a seal interface (28) of the face seal. A plurality of fins (56) extend radially outwardly from the second component body in the chamber interior, such that the plurality of fins create a centrifugal force on the volume of lubricant to urge the volume of lubricant away from the seal interface.

    METHOD FOR CONFIGURING LEADING EDGE OF STATOR PLATFORM OF COMPRESSOR, AND CORRESPONDING STATOR PLATFORM
    8.
    发明公开
    METHOD FOR CONFIGURING LEADING EDGE OF STATOR PLATFORM OF COMPRESSOR, AND CORRESPONDING STATOR PLATFORM 审中-公开

    公开(公告)号：EP4257827A1

    公开(公告)日：2023-10-11

    申请号：EP21902271.2

    申请日：2021-11-03

    Applicant: AECC Shanghai Commercial Aircraft Engine Manufacturing Co., Ltd. ,  Aecc Commercial Aircraft Engine Co., Ltd.

    Inventor： CAO, Chuanjun ,  WANG, Jinchun ,  YIN, Zeyong ,  LI, Jibao ,  WU, Fan ,  ZHANG, Xiaoshi ,  ZHAI, Zhilong ,  JIANG, Yixuan

    IPC: F04D29/54 ,  F04D29/16

    Abstract: The present invention relates to a method for configuring a leading edge of a stator platform of a compressor, and a corresponding stator platform. Said configuration method comprises: simplifying the flowing of an airflow at the root of a rotor blade into the flowing of a free jet, and determining an airflow expansion angle according to the Mach number of the incoming flow at the root of a stator blade; calculating a radial height difference between a first end point on a leading edge of a stator platform and a trailing edge of an adjacent rotor platform by using an axial distance between the trailing edge of the adjacent rotor platform and the leading edge of the stator platform, the airflow expansion angle and a deviation coefficient; determining, on the basis of the radial height difference, the position of the first end point on the leading edge of the stator platform; determining the intersection point of the leading edge of the stator blade and the stator platform as the position of a second end point on the leading edge of the stator platform; and determining a profile line between the first end point and the second end point by bridging spline curves, so that the tail end of the profile line is tangent to the intersection line of the root of the stator blade and the stator platform, and the starting end of the profile line is kept on the same plane as the side wall of the leading edge of the stator platform.

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