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    NACELLE FOR AN AIRCRAFT BYPASS TURBOJET ENGINE
    1.
    发明申请
    NACELLE FOR AN AIRCRAFT BYPASS TURBOJET ENGINE 审中-公开
    用于飞机旁路涡轮发动机的NACELLE

    公开(公告)号：US20150030446A1

    公开(公告)日：2015-01-29

    申请号：US13946316

    申请日：2013-07-19

    申请人： Aircelle

    发明人： Patrick Gonidec ,  Laurent Albert Blin

    IPC分类号： B64D29/06 ,  B64D33/02

    CPC分类号： B64D29/06 ,  B64D33/02 ,  B64D2033/0226 ,  B64D2033/0266 ,  B64D2033/0273 ,  B64D2033/0286 ,  F02C7/042 ,  F02C7/047 ,  F02K1/30 ,  Y02T50/671 ,  Y10T137/0536

    摘要： The disclosure relates to a nacelle for a turbojet engine, including an upstream section forming an air intake lip and defining a space for the circulation of a main air flow. The nacelle includes a device for modulating the cross-section of the space and has means for injecting an auxiliary flow of a gas by means of an induced ejector effect; suction means for drawing in the injected auxiliary flow; and an internal auxiliary flow return area in one or more walls, the area being configured to allow the circulation of the injected auxiliary flow and the drawn-in auxiliary flow and to bring part of the injected auxiliary flow into contact with the main air flow. The internal return area includes an outer front part forming an area in which the thickness of the internal return area is reduced.

    摘要翻译： 本发明涉及一种用于涡轮喷气发动机的机舱，包括形成进气口的上游部分并且限定用于主空气流的循环的空间。 机舱包括用于调节空间横截面的装置，并具有用于通过感应喷射器效应喷射气体的辅助流的装置; 用于吸入注入的辅助流的抽吸装置; 以及在一个或多个壁中的内部辅助流量返回区域，所述区域被配置为允许注入的辅助流和吸入的辅助流的循环，并使部分喷射的辅助流与主空气流接触。 内部返回区域包括外部前部，形成内部返回区域的厚度减小的区域。

    Multi-stage turbocharging compressor for fuel cell systems
    2.
    发明授权
    Multi-stage turbocharging compressor for fuel cell systems 有权

    公开(公告)号：US11749818B2

    公开(公告)日：2023-09-05

    申请号：US17819564

    申请日：2022-08-12

    申请人： ZeroAvia, Inc.

    发明人： Valery Miftakhov

    IPC分类号： H01M8/04 ,  H01M8/04111 ,  F02C1/02 ,  H01M8/04082 ,  F02C6/18 ,  F02C7/36 ,  B64D33/02 ,  B64D31/00 ,  B64D41/00

    CPC分类号： H01M8/04111 ,  B64D33/02 ,  F02C1/02 ,  F02C6/18 ,  F02C7/36 ,  H01M8/04201 ,  B64D31/00 ,  B64D2033/024 ,  B64D2033/0266 ,  B64D2041/005 ,  F05D2220/323 ,  F05D2220/60 ,  F05D2260/211 ,  H01M2250/20

    摘要： An aircraft power plant for a fuel cell including a turbo assembly, a compressor assembly, a turbo assembly, a compressor assembly controller, a first stage turbo assembly and compressor assembly operation configured to generate a first stage compressed fluid generated from ambient air and excess oxygen exhausted from a fuel cell of an aircraft power plant. A second stage turbo assembly and compressor assembly operation configured to receive the first stage compressed fluid, and a controller bleed valve coupled with the first stage turbo assembly and compressor assembly and the second stage turbo assembly and compressor assembly. An oxygen supply system, the oxygen supply system fluidically coupled with the first stage turbo assembly and compressor assembly wherein a first compressed oxygen is generated by the first stage turbo assembly is combined with a second compressed oxygen generated by the second stage turbo assembly to generate a combined oxygen controlled by the controller bleed valve. A third stage turbo assembly and compressor assembly operation configured to receive the combined oxygen, and a hydrogen supply system configured to provide hydrogen fluidically coupled with the third stage turbo assembly and compressor assembly.