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    CABIN BLOWER SYSTEM
    1.
    发明申请
    CABIN BLOWER SYSTEM 审中-公开
    客舱喷淋系统

    公开(公告)号：US20160167789A1

    公开(公告)日：2016-06-16

    申请号：US14957972

    申请日：2015-12-03

    申请人： ROLLS-ROYCE plc

    发明人： Glenn A. KNIGHT ,  Alan R. MAGUIRE ,  Daniel ROBINSON

    IPC分类号： B64D13/04

    CPC分类号： F02C7/277 ,  B64D13/02 ,  B64D31/14 ,  B64D2013/0696 ,  F02C7/275 ,  F16H37/086 ,  F16H2015/383 ,  F16H2037/088

    摘要： An aircraft cabin blower system comprising a transmission and a compressor is disclosed. The system has a forward configuration in which the compressor is drivable in use via the transmission. The transmission comprises a toroidal continuously variable transmission giving selectively variable control over the rate at which the compressor is driven.

    摘要翻译： 公开了一种包括变速器和压缩机的飞机机舱鼓风机系统。 该系统具有正向构造，其中压缩机经由变速器在使用中是可驱动的。 变速器包括环形无级变速器，其给出对压缩机被驱动的速率的选择性可变的控制。

    Flexible power and thermal architectures using a common machine
    5.
    发明申请
    Flexible power and thermal architectures using a common machine 有权
    使用普通机器的灵活的电源和散热架构

    公开(公告)号：US20070266695A1

    公开(公告)日：2007-11-22

    申请号：US11435997

    申请日：2006-05-17

    申请人： Clarence Lui ,  Yu-Hang Ho ,  Chris Lee

    发明人： Clarence Lui ,  Yu-Hang Ho ,  Chris Lee

    IPC分类号： B64G1/40

    CPC分类号： B64D13/06 ,  B64D2013/0644 ,  B64D2013/0659 ,  B64D2013/0696 ,  Y02T50/44 ,  Y02T50/56

    摘要： A power and cooling management system configured to flexibly couple various adaptive modules to an integrated power and cooling unit to suit any aircraft platform is provided. The integrated power and cooling unit has a compressor, a power turbine, a cooling turbine and an integral starter generator mounted to the shaft of the power and cooling turbine. The integrated power and cooling unit may be pneumatically and/or pneumatically coupled to an adaptive module that comprises an additional compressor and an additional turbine or electrically coupled to a fuel cell which provides the main power after entering the full operation mode. When the engine includes an integral starter generator mounted thereto, the integral starter generator of the integrated power and cooling unit is operative to receive electric power from the engine mounted generator. Alternatively, a motor/generator may be mounted to the shaft of the additional turbine of the adaptive module.

    摘要翻译： 提供了一种电力和冷却管理系统，其被配置为将各种自适应模块灵活地耦​​合到集成的电力和冷却单元以适合任何飞机平台。 集成的动力和冷却单元具有压缩机，动力涡轮机，冷却涡轮机和安装在功率和冷却​​涡轮机的轴上的整体起动发电机。 集成的动力和冷却单元可以气动地和/或气动耦合到自适应模块，该自适应模块包括额外的压缩机和额外的涡轮机，或者电耦合到在进入完全运行模式之后提供主电力的燃料电池。 当发动机包括安装在其上的整体起动发电机时，集成动力和冷却单元的整体起动发电机可操作以从发动机安装的发电机接收电力。 或者，马达/发电机可以安装到自适应模块的附加涡轮机的轴上。

    Integrated bleed air and engine starting system
    6.
    发明授权
    Integrated bleed air and engine starting system 失效
    集成放气和发动机启动系统

    公开(公告)号：US06305156B1

    公开(公告)日：2001-10-23

    申请号：US09390412

    申请日：1999-09-03

    申请人： Clarence Lui

    发明人： Clarence Lui

    IPC分类号： F02C608

    CPC分类号： F02C6/08 ,  B64D13/06 ,  B64D2013/0696 ,  F02C7/277 ,  F02C7/32 ,  F05D2220/50 ,  Y02T50/44 ,  Y02T50/56 ,  Y02T50/671

    摘要： An integrated bleed air and engine starting system for an engine utilizes an innovative flow multiplier air turbine starter to provide bleed air supply to an ECS as well as starting an engine. The technique reduces bleed air consumption by mixing fan stage air and high stage air for ECS fresh air usage. It also can eliminate or reduce the size of the precooler heat exchanger. The system includes an air turbine starter subsystem and an air flow subsystem. The air turbine starter subsystem includes a compressor, a turbine, and a common shaft fixed between the compressor and turbine. Also provided is a gear coupled to a gearbox which links the engine with a shaft, as well as a variable nozzle valve intermediate the turbine and engine. The air flow subsystem comprises a diverter valve downstream of the turbine, an isolation valve intermediate the turbine and an auxiliary power unit, and a check valve downstream of the compressor and turbine. A fan is in air flow communication with the compressor and engine.

    摘要翻译： 用于发动机的集成放气和发动机起动系统利用创新的流量倍增器空气涡轮起动器来向ECS提供排放空气以及启动发动机。 该技术通过混合风扇级空气和高级空气来减少排放空气的消耗，用于ECS新鲜空气使用。 它也可以消除或减小预冷器热交换器的尺寸。 该系统包括一个空气涡轮起动器子系统和一个气流子系统。 空气涡轮起动器子系统包括压缩机，涡轮机和固定在压缩机和涡轮机之间的公共轴。 还提供了一种联接到齿轮箱的齿轮，其将发动机与轴连接，以及在涡轮机和发动机之间的可变喷嘴阀。 气流子系统包括在涡轮下游的分流阀，在涡轮机和辅助动力单元之间的隔离阀，以及在压缩机和涡轮机下游的止回阀。 风扇与压缩机和发动机进行空气流通。

    Multi role primary/auxiliary power system with engine start capability for aircraft
    7.
    发明授权
    Multi role primary/auxiliary power system with engine start capability for aircraft 失效

    公开(公告)号：US4494372A

    公开(公告)日：1985-01-22

    申请号：US502902

    申请日：1983-06-10

    申请人： Michael J. Cronin

    发明人： Michael J. Cronin

    IPC分类号： B64D13/06 ,  F02C7/268 ,  F02C7/32

    CPC分类号： F02C7/32 ,  B64D13/06 ,  F02C7/268 ,  B64D2013/0659 ,  B64D2013/0696 ,  F05D2220/50 ,  F05D2260/404 ,  Y02T50/56

    摘要： The invention is a multi role primary/auxiliary power system with engine start capability for aircraft that provides electric, mechanical and air conditioning power as well as engine starting functions. The compressor (20), turbine (26) and motor/generator (24) are coupled to a drive shaft (14) of the aircraft's engine (12) with the motor/generator (24) mounted between the compressor (20) and turbine (26). A first clutch (28) is mounted on the drive shaft (14) between the motor/generator (24) and the turbine (26). Coupled to the outlet (29) of the compressor (20) is a two-way valve (34) adapted to couple the compressor (20) to either a first duct (36) or second duct (37). Both of these ducts (36), (37) are coupled at their opposite ends to the turbine (26). Mounted in the first duct (36) is a combustor (40) and in the second duct (37) a first heat exchanger (42). A third duct (44) is also coupled between the compressor (20) and the turbine (26) and which incorporates a valve (50). Mounted between the turbine (26) and the engine (12) is a gear reduction assembly (58). Coupled to the output of the turbine (26) is a fourth duct (100) which is coupled to a second two-way valve. The second two-way valve (102) either couples the fourth duct (100) to an overboard vent (104) or a fifth duct (106), having a heat exchanger (108) mounted therein to the cabin of the aircraft. Coupling the first, second and third ducts (36), (37), and (44) together is a bypass duct (110) (sixth duct) which bypasses the turbine (26) and connects to the fourth duct (100). The sixth duct (110) also incorporates a simple open/close valve (112). Finally, a control circuit (115) for the motor/generator is provided which can couple either onboard battery power or ground supply AC power to the motor/generator.