中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

15 records (took 0.022 seconds)

    ENGINE
    1.
    发明专利
    ENGINE 审中-公开

    公开(公告)号：JP2003227412A

    公开(公告)日：2003-08-15

    申请号：JP2003007865

    申请日：2003-01-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GLAHN J AXEL ,  SAHM MICHAEL K

    IPC: B64D33/02 ,  B64D33/04 ,  B64D41/00 ,  F02C3/13 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F02K3/075 ,  F02K3/077

    Abstract: PROBLEM TO BE SOLVED: To provide an auxiliary power device integrally formed with an engine. SOLUTION: In the auxiliary power device integrally formed with an engine, the engine 10 has: a high pressure spool including a high pressure compressor 20 connected to a high pressure turbine 22; and a low pressure spool including a low pressure compressor 20 connected to a low pressure turbine 14. The engine 10 further has a system independently operating the high pressure spool, thereby, the high pressure spool functions as the auxiliary power device. COPYRIGHT: (C)2003,JPO

    SOLAR CELL SYSTEM WITH THERMAL MANAGEMENT
    4.
    发明申请
    SOLAR CELL SYSTEM WITH THERMAL MANAGEMENT 审中-公开
    具有热管理的太阳能电池系统

    公开(公告)号：WO2007108975A2

    公开(公告)日：2007-09-27

    申请号：PCT/US2007006150

    申请日：2007-03-12

    Applicant: UNITED TECHNOLOGIES CORP ,  JIANG YIRONG ,  CHEN YU ,  BENDAPUDI SATYAM ,  RADCLIFF THOMAS ,  SANGIOVANNI JOSEPH ,  KUANG YUHUI ,  WALKER CRAIG ,  RADHAKRISHNAN RAKESH ,  SAHM MICHAEL K

    Inventor： JIANG YIRONG ,  CHEN YU ,  BENDAPUDI SATYAM ,  RADCLIFF THOMAS ,  SANGIOVANNI JOSEPH ,  KUANG YUHUI ,  WALKER CRAIG ,  RADHAKRISHNAN RAKESH ,  SAHM MICHAEL K

    IPC: H02N6/00

    CPC classification number: H01L31/052 ,  H01L31/0521 ,  H01L31/0547 ,  H02S40/44 ,  Y02E10/52 ,  Y02E10/60

    Abstract: A thermally managed solar cell system (10a, 10b, 10c, 10d) includes a photovoltaic cell (12, 102a, 102b, 202a, 202b) for generating electricity and heat. The system (10a, 10b, 10c, 10d) includes a housing (16), a base (18), and a heat removal device (20, 36, 40, 44, 100, 200, 300). The housing (16) surrounds the solar cell system (10a, 10b, 10c, 10d) and has an open, rear portion. The base (18) is positionable in the open portion of the housing (16) and supports the photovoltaic cell (12). The base (18) is also thermally conductive and spreads heat generated from the photovoltaic cell (12, 102a, 102b, 202a, 202b). The heat removal device (20, 36, 40, 44, 100, 200, 300) and the base act as a single unit with the heat removal device device (20, 36, 40, 44, 100, 200, 300) being coupled to the base (18) to remove the heat from the base (18).

    Abstract translation: 热管理太阳能电池系统（10a，10b，10c，10d）包括用于发电和发热的光电池（12,102a，102b，202a，202b）。 系统（10a，10b，10c，10d）包括壳体（16），基座（18）和散热装置（20,36,40,44,100,200,300）。 壳体（16）围绕太阳能电池系统（10a，10b，10c，10d）并且具有开放的后部。 基座（18）可定位在壳体（16）的开口部分中并支撑光伏电池（12）。 基座（18）也是导热的并且散布从光伏电池（12,102a，102b，202a，202b）产生的热量。 所述除热装置（20,36,40,44,100,200,300）和所述基座用作具有所述除热装置装置（20,36,40,44,100,200,300）的单个装置， 到基部（18）以从基部（18）移除热量。

    Convergent-divergent film coolant passage
    5.
    发明授权
    Convergent-divergent film coolant passage 失效
    会聚发散薄膜冷却液通道

    公开(公告)号：US4705455A

    公开(公告)日：1987-11-10

    申请号：US81209285

    申请日：1985-12-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SAHM MICHAEL K ,  MILANO ROBERT

    IPC: F01D5/18 ,  F01D9/02

    CPC classification number: F01D5/186 ,  F05D2250/12 ,  F05D2250/121 ,  F05D2250/323 ,  F05D2250/324 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A coolant passage through a wall to be cooled, such as the wall of a hollow airfoil, is shaped and oriented to eject coolant fluid therefrom within the boundary layer of hot gases flowing over the surface to film cool the wall downstream of the outlet. The passage includes a metering portion near its inlet, followed by a diffusing portion and nozzle portion. The nozzle portion, adjacent the outlet, simultaneously diverges and converges in mutually perpendicular directions to produce a more uniform coolant velocity profile, which results in increased coolant area coverage and improved cooling effectiveness.

    Abstract translation: 通过待冷却的壁（例如中空翼片的壁）的冷却剂通道被成形并定向成在其流过表面的热气体的边界层内从其中排出冷却剂流体，以将出口下游的壁冷却。 通道包括在其入口附近的计量部分，随后是扩散部分和喷嘴部分。 邻近出口的喷嘴部分同时沿相互垂直的方向发散并收敛，以产生更均匀的冷却剂速度分布，这导致冷却剂面积的增加和冷却效率的提高。

    MAIN PROPULSION ENGINE SYSTEM INTEGRATED WITH SECONDARY POWER UNIT
    7.
    发明申请
    MAIN PROPULSION ENGINE SYSTEM INTEGRATED WITH SECONDARY POWER UNIT 审中-公开
    主推动发动机系统与二次发电机组合

    公开(公告)号：WO02052136A3

    公开(公告)日：2003-04-10

    申请号：PCT/US0147827

    申请日：2001-12-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALBERO JOSE ,  DUSSAULT RICHARD ,  THOMPSON ROBERT G ,  GERMAIN PATRICK ,  SAHM MICHAEL K ,  TREMAINE ERIC

    IPC: F02C7/277 ,  F02C7/32 ,  F02K3/06 ,  F02K3/12 ,  B64C31/00

    CPC classification number: F02K3/12 ,  F02C7/277 ,  F02C7/32 ,  F02K3/06 ,  F05D2220/50 ,  Y02T50/671

    Abstract: A main engine (14) mounted auxiliary power unit (30) comprises an auxiliary power unit (31) integrated with a primary gas turbine engine (14) into a single power plant suited for aircraft applications. The auxiliary power unit (30) can be mounted within an engine core compartment of the main engine or at the main engine aft center body. The integration of the auxiliary power unit (30) provides for installation and certification cost savings to the airframer by eliminating the need for mounting an auxiliary power unit (30) to the tail section of the aircraft.

    Abstract translation: 安装有辅助动力单元（30）的主发动机（14）包括与主要燃气涡轮发动机（14）整合成适用于飞行器应用的单个动力装置的辅助动力单元（31）。 辅助动力单元（30）可以安装在主发动机的发动机核心舱内或主发动机尾部中心体上。 辅助动力单元（30）的集成通过消除将辅助动力单元（30）安装到飞行器尾部的需要来为空中装置提供安装和认证成本节省。

    IMPROVED AIRCRAFT ARCHITECTURE WITH A REDUCED BLEED AIRCRAFT SECONDARY POWER SYSTEM
    8.
    发明申请
    IMPROVED AIRCRAFT ARCHITECTURE WITH A REDUCED BLEED AIRCRAFT SECONDARY POWER SYSTEM 审中-公开
    改进的飞机架构与减少的飞机二次电源系统

    公开(公告)号：WO02066323A2

    公开(公告)日：2002-08-29

    申请号：PCT/US0204734

    申请日：2002-02-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALBERO JOSE ,  LENTS CHARLES E ,  SAHM MICHAEL K ,  WELCH RICHARD C

    IPC: B64D13/06 ,  F02C7/32 ,  B64D

    CPC classification number: F02C7/32 ,  B64D13/06 ,  B64D2013/0611 ,  B64D2013/0618 ,  B64D2013/064 ,  B64D2013/0644 ,  Y02T50/54 ,  Y02T50/545 ,  Y02T50/56

    Abstract: The present invention relates to an improved architecture for an aircraft. The aircraft has a first engine, a first gearbox associated with the first engine, a first starter/generator associated with the gearbox, and a first motor drive connected to the first starter/generator for providing the starter/generator with electric power to start the first engine and to receive electric power from the starter/generator after the engine has been started to operate electrically driven systems onboard the aircraft. The aircraft preferably further has at least one other engine which has a gearbox and a starter/generator associated with it and at least a second motor drive connected to the starter/generator. The electrically driven systems operated by the motor drive(s) include an environmental control system, a wing anti-icing system, an aircraft control system, and the aircraft fuel system. The aircraft also includes an auxiliary power unit for supplying electrical power to at least the first motor drive for initiating operation of the first engine.

    Abstract translation: 本发明涉及一种用于飞机的改进的架构。 飞机具有第一发动机，与第一发动机相关联的第一变速箱，与变速箱相关联的第一起动/发电机，以及连接到第一起动器/发电机的第一电动机驱动器，用于向起动器/发电机提供电力以启动 第一发动机，并且在发动机起动之后从起动器/发电机接收电力来操作飞机上的电驱动系统。 飞机优选地还具有至少一个其它发动机，其具有齿轮箱和与其相关联的起动器/发电机以及连接到起动器/发电机的至少第二马达驱动器。 由电动机驱动器操作的电驱动系统包括环境控制系统，机翼防冰系统，飞机控制系统和飞机燃料系统。 该飞机还包括辅助动力单元，用于向至少第一马达驱动器提供电力以启动第一发动机的操作。

    10.
    发明专利
    未知

    公开(公告)号：DE60317118D1

    公开(公告)日：2007-12-13

    申请号：DE60317118

    申请日：2003-01-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GLAHN J AXEL ,  SAHM MICHAEL K

    IPC: B64D41/00 ,  B64D33/02 ,  B64D33/04 ,  F02C3/13 ,  F02C7/27 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F02K3/075 ,  F02K3/077

    Abstract: The present invention relates to an engine integrated auxiliary power unit. The engine (10) comprises a high pressure spool which includes a high pressure compressor (20) connected to a high pressure turbine (22) and a low pressure spool which includes a low pressure compressor (12) connected to a low pressure turbine (14). The engine further has a system for independently operating the high pressure spool and thus allowing the high pressure spool to function as an auxiliary power unit.

Patent Agency Ranking