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    TURBOPROP
    3.
    发明申请
    TURBOPROP 审中-公开

    公开(公告)号：US20180009522A1

    公开(公告)日：2018-01-11

    申请号：US15547118

    申请日：2016-01-27

    申请人： Safran Aircraft Engines

    发明人： Paul Antoine FORESTO ,  Anthony BINDER ,  Alexandre Gerard Francois COUILLEAUX ,  Norman Bruno Andre JODET

    IPC分类号： B64C11/24 ,  F01D5/18 ,  F02C7/04

    摘要： A turboprop including a propeller including a blade extending in a direction, which also includes a root, a leading edge, a trailing edge, and a wing tip, and an inner air stream channel, wherein the inner air stream channel includes an inlet located at the root of the blade and an outlet leading to the trailing edge of the blade transversely directed in relation to the main elongation direction, such that an inner stream of air flowing in the inner air stream channel by entering via the inlet adjacent to the root of the blade is discharged via the outlet adjacent to the trailing edge of the blade by forming a stream of blown air that moves away from the trailing edge in a direction which is transverse to the main elongation direction and which has a component in the direction of a skeleton line of the blade at the trailing edge.

    INTERMEDIATE CASING FOR A GAS TURBINE ENGINE
    6.
    发明公开
    INTERMEDIATE CASING FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20230220786A1

    公开(公告)日：2023-07-13

    申请号：US17916333

    申请日：2021-04-01

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： Paul Antoine FORESTO

    IPC分类号： F01D25/26 ,  F01D9/06 ,  F01D5/14

    CPC分类号： F01D25/26 ,  F01D9/065 ,  F01D5/143 ,  F05D2240/14 ,  F05D2250/10 ,  F05D2250/73

    摘要： An intermediate casing includes an inner wall having an outer surface extending along a longitudinal axis, the outer surface having a first profile in a first plane, an outer wall having an inner surface a second profile in the first plane, and first through fourth arms each extending radially. The outer and inner surfaces and the first and second arms delimit a first cavity, the first cavity having a first area and the outer and inner surfaces being separated by a first distance. The outer and inner surfaces and the third and fourth arms delimit a second cavity, the second cavity having a second area and the outer and inner surfaces being separated by a second distance. The first and second profiles are such that the first area is substantially identical to the second area and the first distance is different from the second distance.

    MODULE OF AN AIRCRAFT BYPASS ENGINE OF WHICH ONE ARM INTEGRATES A STATOR BLADE
    7.
    发明申请
    MODULE OF AN AIRCRAFT BYPASS ENGINE OF WHICH ONE ARM INTEGRATES A STATOR BLADE 审中-公开

    公开(公告)号：US20200332743A1

    公开(公告)日：2020-10-22

    申请号：US16455126

    申请日：2019-06-27

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： Paul Antoine FORESTO

    IPC分类号： F02K3/02 ,  F02K3/075

    摘要： The invention relates to a module of an aircraft bypass engine including an annular flow path of a secondary flow of gas wherein is mounted an annular row of stator blades configured to straighten the gas flow, an arm extending in the flow path downstream from said annular row of blades and being connected physically to one of the stator blades so as to form a unitary aerodynamic assembly, wherein at least one of the two blades adjacent to the blade of the unitary aerodynamic assembly is of a variable pitch type and capable of being rotationally moved about a substantially radial axis with respect to a longitudinal axis of the engine.