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    AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM
    34.
    发明公开
    AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM 审中-公开

    公开(公告)号：EP3371673A1

    公开(公告)日：2018-09-12

    申请号：EP16793988.3

    申请日：2016-11-03

    申请人： BAE Systems PLC

    发明人： VICKERS, Mark, Gordon ,  SHARPE, Douglas, John

    IPC分类号： G05D23/13 ,  B64D13/08 ,  F02C6/08

    CPC分类号： G05D23/1931 ,  B64D13/06 ,  B64D13/08 ,  B64D2013/0618 ,  F02C6/08 ,  G01K7/25 ,  G05D23/24

    摘要： An aircraft environmental control system (4) for controlling a temperature of a fluid, the control system (4) comprising: a first temperature sensor (30) configured to measure a first temperature and to generate a first signal, the first temperature being a temperature of the fluid, the first signal being indicative of the measured first temperature; an amplifier (76) configured to amplify the first signal; one or more processors (64) configured to, using the amplified first signal, generate a control signal for controlling the temperature of the fluid; and a second temperature sensor (68) configured to measure a second temperature, the second temperature being a temperature of an operational environment of the amplifier (76); wherein the one or more processors (64) are further configured to, responsive to the determining that the measured second temperature satisfies one or more predetermined criteria, modify a gain of the amplifier (76) and wherein: the aircraft environmental control system (4) further comprises a baseline signal generation module (70) configured to generate a baseline signal, the baseline signal being independent of the measured temperature of the operational environment of the amplifier (76); the amplifier (76) is further configured to amplify the baseline signal; and the one or more processors (64) are further configured to, responsive to the determining that measured second temperature satisfies the one or more criteria, modify the gain of the amplifier (76) using the amplified baseline signal.

    AIR DISTRIBUTION SYSTEM WITH RECIRCULATING ZONE TRIM TEC
    36.
    发明公开
    AIR DISTRIBUTION SYSTEM WITH RECIRCULATING ZONE TRIM TEC 审中-公开

    公开(公告)号：EP3333078A1

    公开(公告)日：2018-06-13

    申请号：EP17206189.7

    申请日：2017-12-08

    申请人： Hamilton Sundstrand Corporation

    发明人： ARMY, Donald E.

    IPC分类号： B64D13/06 ,  B64D13/08

    摘要： Disclosed is a system for distributing air to plural aircraft zones that receive manifold air from a mix manifold (16), the system has: a thermal electronic cooler trim module (TEC) (24), fluidly connected between a recirculating fan (21) and the mix manifold (16); the TEC has: multiple TEC zones (26, 28), each fluidly connected to, and sized relative to heating requirements of, a respective one of the aircraft zones; a first TEC inlet (30), through which a first portion of the recirculated air enters the TEC, is heat treated in a first heating direction, and is exhausted toward the mix manifold; and a second TEC inlet (32), through which a second portion of the recirculated air enters the TEC zones, is heat treated in a second heating direction, and is exhausted toward the aircraft zones for mixing with the manifold air.

    HEAT RECOVERY SYSTEM, IN PARTICULAR FOR USE ON AIRCRAFT, USING A TWO-PHASE FLUID CIRCUIT
    37.
    发明授权
    HEAT RECOVERY SYSTEM, IN PARTICULAR FOR USE ON AIRCRAFT, USING A TWO-PHASE FLUID CIRCUIT 有权

    公开(公告)号：EP3095704B1

    公开(公告)日：2018-05-23

    申请号：EP16170051.3

    申请日：2016-05-18

    申请人： LEONARDO S.P.A.

    发明人： Moscatelli, Antonio ,  Mancuso, Gianni

    IPC分类号： B64D13/08 ,  F28D15/02 ,  B64D15/02 ,  B64D37/34

    CPC分类号： B64D13/08 ,  B64D15/02 ,  B64D37/34 ,  B64D2013/0607 ,  B64D2013/0648 ,  B64D2013/0674 ,  F28D15/0266 ,  F28D15/043 ,  Y02T50/56

    摘要： The system comprises at least one evaporator device (12) arranged around a tube (10) inside which a hot fluid flows and, for each evaporator device (12), a respective conduit (24) connected at its opposite ends to the evaporator device (12) so as to form with the latter a closed circuit containing a two-phase fluid. Each evaporator device (12) comprises a casing, having an inner wall (14) in contact with the respective tube (10) and an outer wall (16) enclosing a cavity (20) with the inner wall (14), and a separating member (22) of porous material arranged inside the casing so as to divide radially the cavity (20) into an inner cavity (20a), extending between the inner wall (14) and the separating member (22), and an outer cavity (20b) extending between the separating member (22) and the outer wall (16). Each conduit (24) is in fluid communication at its opposite ends with the inner cavity (20a) and with the outer cavity (20b), respectively, of the respective evaporator device (12) so as to allow fluid in vapour phase to flow out from the evaporator device (12) and the fluid in liquid phase to flow back into the evaporator device (12), respectively.

    ENVIRONMENTAL CONTROL SYSTEM
    38.
    发明公开
    ENVIRONMENTAL CONTROL SYSTEM 审中-公开
    环境控制系统

    公开(公告)号：EP3312091A1

    公开(公告)日：2018-04-25

    申请号：EP17197940.4

    申请日：2017-10-24

    申请人： Hamilton Sundstrand Corporation

    发明人： SHEA, Brian R.

    IPC分类号： B64D13/06 ,  B64D13/02 ,  B64D13/08

    CPC分类号： B64D13/06 ,  B64D13/02 ,  B64D13/08 ,  B64D2013/0618 ,  B64D2013/0625 ,  B64D2013/064

    摘要： An environmental control system (10) includes a turbo-compressor assembly (20) and a ram air system (22). The turbo-compressor assembly (20) includes a first turbine (32), a first compressor (30), and a first heat exchanger (34). The first heat exchanger has a first heat exchanger first side (60) in fluid communication with a first turbine outlet (52), a first heat exchanger second side (62), a first heat exchanger inlet (64) in fluid communication with a first compressor outlet (44), and a first heat exchanger outlet (66). The ram air system (22) has a first ram air inlet (90), a second ram air inlet (92) being in fluid communication with the first heat exchanger second side (62), and a second heat exchanger (94) being in fluid communication with at least one of the first ram air inlet (90) and the second ram air inlet (92).

    摘要翻译： 环境控制系统（10）包括涡轮压缩机组件（20）和冲压空气系统（22）。 涡轮压缩机组件（20）包括第一涡轮机（32），第一压缩机（30）和第一热交换器（34）。 第一热交换器具有与第一涡轮机出口（52）流体连通的第一热交换器第一侧（60），第一热交换器第二侧（62），与第一热交换器第一侧（60）流体连通的第一热交换器入口（64） 压缩机出口（44）和第一热交换器出口（66）。 冲压空气系统（22）具有第一冲压空气入口（90），与第一热交换器第二侧（62）流体连通的第二冲压空气入口（92），以及处于第一热交换器 与第一冲压空气入口（90）和第二冲压空气入口（92）中的至少一个流体连通。

    AIRCRAFT ELECTRONICS THERMAL REGULATION SYSTEM
    39.
    发明公开
    AIRCRAFT ELECTRONICS THERMAL REGULATION SYSTEM 审中-公开
    飞机电子热调节系统

    公开(公告)号：EP3279091A1

    公开(公告)日：2018-02-07

    申请号：EP17184407.9

    申请日：2017-08-02

    申请人： Hamilton Sundstrand Corporation

    发明人： PAL, Debabrata

    IPC分类号： B64D13/08 ,  B64D13/06 ,  B64D37/34 ,  F28D9/00

    摘要： An electronics cooling system (100) for an aircraft includes a heat exchanger (101) comprising a coolant circuit (103), an air circuit (105) and a fuel circuit (107) such that each of the circuits is in thermal communication with the other circuit. The coolant circuit (103) is in thermal communication with one or more aircraft electronics. The air circuit (105) is fluidly connectable with at least one air source,.The fuel circuit (107) is fluidly connectable with a fuel tank (111) between the fuel tank (111) and an engine of the aircraft and/or fluidly connectable with a fuel loop that returns to the fuel tank (111).

    摘要翻译： 一种用于飞机的电子冷却系统（100）包括热交换器（101），该热交换器包括冷却剂回路（103），空气回路（105）和燃料回路（107），使得每个回路与 其他电路。 冷却剂回路（103）与一个或多个飞机电子器件热连通。 空气回路（105）可与至少一个空气源流体连通。燃料回路（107）可与燃料箱（111）和飞机发动机之间的燃料箱（111）流体连接，和/或流体连接 可与返回到燃料箱（111）的燃料回路连接。