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    Internal combustion engines equipped with a turbocompressor unit with heating upstream of the turbine and methods of starting up their turbocompressor units
    61.
    发明授权
    Internal combustion engines equipped with a turbocompressor unit with heating upstream of the turbine and methods of starting up their turbocompressor units 失效
    内燃机配备有在涡轮机上游加热的涡轮压缩机单元以及启动其涡轮压缩机单元的方法

    公开(公告)号：US3949555A

    公开(公告)日：1976-04-13

    申请号：US436728

    申请日：1974-01-25

    申请人： Jean Melchior

    发明人： Jean Melchior

    IPC分类号： F02B37/20 ,  F01M5/02 ,  F02B3/06 ,  F02B37/00 ,  F02B37/16 ,  F02B39/14 ,  F02C7/27 ,  F02P7/08 ,  F02B33/44 ,  F02B33/32

    CPC分类号： F01M5/025 ,  F02B37/166 ,  F02B39/14 ,  F02B3/06 ,  Y02T10/144

    摘要： Diesel engines, equipped with a turbocompressor unit with a combustion chamber upstream of the turbine, comprising a by-pass duct enabling direct and permanent passage between the outlet of the compressor of the turbocompressor unit and said combustion chamber, comprise in addition, for the starting of the turbocompressor unit, a starting device comprising pressure difference generating means. These means are positioned in the by-pass duct in the midst of the air-flow between the compressor and the turbine and arranged to create a flow in the direction of the turbine of the turbocompressor unit. The pressure difference generating means may be constituted by a blower driven by an electric motor, or by an injector supplied with air under pressure and generating a flow by the effect of induction.

    摘要翻译： 配备有在涡轮机上游具有燃烧室的涡轮压缩机单元的柴油发动机包括能够在涡轮压缩机单元的压缩机和所述燃烧室的出口之间直接和永久地通过的旁路管道，还包括用于起动 涡轮压缩机单元的起动装置，包括压差发生装置。 这些装置在压缩机和涡轮机之间的空气流中间位于旁通管道中，并被布置成在涡轮压缩机单元的涡轮机的方向上产生流动。 压力差产生装置可以由电动机驱动的鼓风机，或由压力下供给空气的喷射器构成，并通过感应产生流动。

    AIRCRAFT TURBOMACHINE COMPRISING MEANS FOR PRIMING THE LUBRICATING PUMP
    70.
    发明申请
    AIRCRAFT TURBOMACHINE COMPRISING MEANS FOR PRIMING THE LUBRICATING PUMP 有权

    公开(公告)号：US20220235708A1

    公开(公告)日：2022-07-28

    申请号：US17597047

    申请日：2020-06-19

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： Jérémy Edmond FERT ,  Nicolas Vincent Pierre-Yves COTEREAU

    IPC分类号： F02C7/27 ,  B64D27/02 ,  F01D19/00 ,  F01D25/18

    摘要： An aircraft turbomachine includes a lubricating circuit notably including a reservoir of lubricating fluid, a pump drawing lubricating fluid from the reservoir to inject it toward several components of the turbomachine, and an intake pipe connecting the reservoir to an intake orifice of the pump, the turbomachine further including a pneumatic starting circuit including a starting tube through which there circulates a flow of compressed air intended to supply a pneumatic starter of the turbomachine, wherein it includes a pneumatic line extending from the starting tube as far as the reservoir so as to supply the reservoir with compressed air so as to cause the lubricating fluid to circulate through the intake pipe towards the pump.