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    MAIN PROPULSION ENGINE SYSTEM INTEGRATED WITH SECONDARY POWER UNIT
    2.
    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
    3.
    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。

    Improved aircraft architecture with a reduced bleed aircraft secondary power system
    4.
    发明专利
    Improved aircraft architecture with a reduced bleed aircraft secondary power system 未知

    公开(公告)号：AU2002242188A1

    公开(公告)日：2002-09-04

    申请号：AU2002242188

    申请日：2002-02-14

    Applicant: UNITED TECHNOLOGIES CORP

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

    IPC: B64D13/06 ,  F02C7/32 ,  F02D41/22

    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.

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