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    ICING CONDITION IDENTIFICATION FOR GAS TURBINE ENGINE
    1.
    发明公开
    ICING CONDITION IDENTIFICATION FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20240247612A1

    公开(公告)日：2024-07-25

    申请号：US18100765

    申请日：2023-01-24

    申请人： Pratt & Whitney Canada Corp.

    发明人： Zubair Ahmad

    IPC分类号： F02C7/047 ,  F02C9/00

    CPC分类号： F02C7/047 ,  F02C9/00 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/80 ,  F05D2270/09

    摘要： A gas turbine engine includes a propulsor for providing air into a core engine housing, and for providing air as propulsion air. An aircraft fluid moves within an inlet to the gas turbine engine, and is exposed to inlet air at the inlet. There is a first temperature sensor for sensing a first temperature of the aircraft at a first upstream point and a second temperature sensor for sensing a second temperature of the aircraft fluid at a second downstream point where the aircraft fluid has been exposed to the inlet air for a period of time. A control determines a temperature differential between first and second temperatures sensed by the first and second temperature sensors, the temperature differential associated with a likelihood that an icing condition will occur. The control is programmed to take a corrective action should an icing condition be identified. A method is also disclosed.

    Aircraft turboprop engine inlet compact profile configuration to improve air intake efficiency and without loss of anti-icing ability
    4.
    发明授权
    Aircraft turboprop engine inlet compact profile configuration to improve air intake efficiency and without loss of anti-icing ability 有权

    公开(公告)号：US12012891B1

    公开(公告)日：2024-06-18

    申请号：US17746747

    申请日：2022-05-17

    申请人： American Aviation, Inc.

    发明人： Stephen R. Speer ,  Alexlander J. Duncan ,  Jayme S. Bartlett ,  George R. Kemner

    IPC分类号： F02C7/047 ,  B64D33/02

    CPC分类号： F02C7/047 ,  B64D2033/0233

    摘要： A turboprop powered aircraft having a cowling or nacelle surrounding the engine, said cowling incorporates an air inlet and internal ducting to the engine wherein the inlet incorporated anti icing ducts, said inlet shape has a closed oval or other non-circular shape that is not coaxial to the engine propeller drive shaft. Inlet anti-icing heating duct means are provided for channeling a portion of the engines exhaust to the interior of the inlet rim. A further improvement in inlet efficiency can be achieved by reducing the thickness of the inlet cross-section, but this results in less space available for the hot exhaust connections. To provide for the inlet reduced section thickness, the exhaust flow connections also incorporate reduced thickness sections to facilitate cooling and insulation of the adjacent cowling and inlet duct surfaces from the excessive heat associated with the hot exhaust gas connection. Additional cooling means utilize air flow from openings in the engine cowling that are channeled to cool internal surfaces of the cowling that may be exposed to excessive heat.

    Air inlet and method for de-icing an air inlet into a nacelle of an aircraft turbojet engine
    9.
    发明授权
    Air inlet and method for de-icing an air inlet into a nacelle of an aircraft turbojet engine 有权

    公开(公告)号：US11773779B2

    公开(公告)日：2023-10-03

    申请号：US17776433

    申请日：2020-11-20

    申请人： SAFRAN NACELLES

    发明人： Hervé Léopold Hurlin

    IPC分类号： F02C7/047 ,  F02C7/04

    CPC分类号： F02C7/047 ,  F02C7/04 ,  F05D2220/323 ,  F05D2260/20

    摘要： An air inlet into a nacelle of an aircraft turbojet engine having a de-icing device and extends along an axis X, an air stream flowing in the air inlet from upstream to downstream, the inlet comprising an inner wall and an outer wall which are connected by a leading edge, the inner wall having a plurality of air delivery lines, each air delivery line having a plurality of through-holes designed to blow elementary streams from the hot air source in order to de-ice said inner wall, the air delivery lines being parallel to one another in a cylindrical projection plane, each air delivery line having a depth P3 defined along the axis X as well as a length L3 defined along the axis Y in the cylindrical projection plane, two adjacent air delivery lines being spaced apart by a distance D3, each position along the axis Y with no more than one through-hole, the ratio of the distances L3/D3 being between 0.8 and 1.