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    AUXILIARY POWER UNIT MOUNTING BRACKET
    2.
    发明申请
    AUXILIARY POWER UNIT MOUNTING BRACKET 审中-公开
    辅助电源安装支架

    公开(公告)号：WO2014175934A2

    公开(公告)日：2014-10-30

    申请号：PCT/US2014/013147

    申请日：2014-01-27

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JEWESS, Gordon F. ,  JONES, Anthony C.

    CPC classification number: B64D41/00 ,  B64D2041/002 ,  F01D25/28 ,  F02C7/20 ,  F05D2220/50 ,  F16M13/02

    Abstract: An auxiliary power unit bracket, according to an exemplary aspect of the present disclosure includes, among other things, a gearbox mounting face and a compartment mounting face, the gearbox mounting face configured to attach to an auxiliary power unit gearbox below a sump level line, the compartment mounting face configured to attach to a portion of an auxiliary power unit compartment above the sump level line.

    Abstract translation: 根据本公开的示例性方面的辅助动力单元支架包括齿轮箱安装面和舱室安装面，其中齿轮箱安装面被配置为附接到在贮槽水平线下方的辅助动力单元齿轮箱， 所述隔间安装面被配置为附接到所述贮槽水平线上方的辅助动力单元隔室的一部分。

    BIFURCATED AIR INLET HOUSING FOR A GAS TURBINE ENGINE
    3.
    发明申请
    BIFURCATED AIR INLET HOUSING FOR A GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的双向空气入口壳体

    公开(公告)号：WO2014165364A1

    公开(公告)日：2014-10-09

    申请号：PCT/US2014/031828

    申请日：2014-03-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JONES, Anthony C. ,  LYDON, Patrick M. ,  THAYALAKHANDAN, Nagamany ,  ALEXANDER, Eric J.

    IPC: F02C7/04 ,  F02C7/057 ,  F02C7/06 ,  F02C9/16

    CPC classification number: F02C7/04 ,  B64D33/02 ,  B64D2033/0273 ,  F02C3/04 ,  F02C7/06 ,  F05D2220/323 ,  F05D2250/51 ,  F05D2250/80 ,  F05D2250/82

    Abstract: A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes a mixing portion downstream of the housing upstream end which mixes airflow from the separate flow paths, such that the airflow is generally around 360 degrees of a rotational axis of the gas turbine engine. A rotor and a turbine drive a shaft to drive the rotor with the shaft including a bearing mounted at a location downstream of the nose cone upstream end.

    Abstract translation: 燃气涡轮发动机具有鼻锥体，其具有鼻锥上游端，并且入口壳体在壳体上游端处包括多个分离的流动路径，其在鼻锥上游端的下游。 入口壳体包括在壳体上游端下游的混合部分，其混合来自分离的流动路径的气流，使得气流通常大约为燃气涡轮发动机的旋转轴线的360度。 转子和涡轮机驱动轴以驱动转子，其中轴包括安装在鼻锥上游端下游位置的轴承。

    APU EXHAUST SYSTEM
    4.
    发明申请
    APU EXHAUST SYSTEM 审中-公开
    APU排气系统

    公开(公告)号：WO2014149604A1

    公开(公告)日：2014-09-25

    申请号：PCT/US2014/019824

    申请日：2014-03-03

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： NAGER, Eric Andrew ,  NAPIER, James C. ,  REHMAN, Farooq ,  JONES, Anthony C.

    IPC: F02K1/82 ,  F02C7/24 ,  F01D25/30

    CPC classification number: B64D33/06 ,  B64D41/00 ,  B64D2041/002 ,  F01D25/30 ,  F02C7/24 ,  F02C7/32 ,  F05D2220/50 ,  F05D2260/96 ,  Y02T50/44

    Abstract: An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.

    Abstract translation: 一种用于燃气涡轮发动机飞行器中的APU的排气系统，其具有减少排气噪声的尾锥。 APU排气衬套连接到APU并延伸到尾锥处的椭圆形切口。衬套具有从APU到靠近尾锥的点的第一恒定横截面，以及从接近尾部点的第二个增加的横截面 尾锥到衬里切口。 衬里转向尾部侧面。 衬套切口进一步放大至少一个更大的切口。

    OPERATING AUXILIARY POWER UNIT DURING OFF-NOMINAL PROPULSION SYSTEM OPERATION
    9.
    发明公开
    OPERATING AUXILIARY POWER UNIT DURING OFF-NOMINAL PROPULSION SYSTEM OPERATION 审中-公开
    在非正常推进系统运行期间操作辅助动力装置

    公开(公告)号：EP3260376A1

    公开(公告)日：2017-12-27

    申请号：EP17177528.1

    申请日：2017-06-22

    Applicant: United Technologies Corporation

    Inventor： JONES, Anthony C. ,  HAGSHENAS, Behzad

    IPC: B64D41/00

    CPC classification number: B64D41/00 ,  B64C13/38 ,  B64D2221/00 ,  F01D15/08 ,  F01D15/10 ,  F02C6/00 ,  F02C7/262 ,  F02C7/277 ,  F02C9/42 ,  F05D2220/323 ,  F05D2220/50 ,  Y02T50/44

    Abstract: An aircraft system (10) includes a component (62) configured to operate with a minimum power demand. The aircraft system (10) also includes an auxiliary power unit (14) including an engine (42). The auxiliary power unit (14) is configured to power the component (62) and to operate the engine (42) in a plurality of operating modes including a power mode and a standby mode. The auxiliary power unit (14) generates a first power output at least equal to the minimum power demand during the power mode. The auxiliary power unit (14) generates a second power output less than the minimum power demand during the standby mode.

    Abstract translation: 飞行器系统（10）包括被配置为以最小功率需求运行的部件（62）。 飞机系统（10）还包括包括发动机（42）的辅助动力单元（14）。 辅助动力单元（14）被配置为以包括动力模式和待机模式的多种操作模式给部件（62）供电并且操作发动机（42）。 辅助功率单元（14）在功率模式期间产生至少等于最小功率需求的第一功率输出。 辅助电力单元（14）在待机模式期间产生小于最小电力需求的第二电力输出。

    METHODS AND SYSTEMS FOR A MODULATED BLEED VALVE
    10.
    发明公开
    METHODS AND SYSTEMS FOR A MODULATED BLEED VALVE 审中-公开
    用于调节排气阀的方法和系统

    公开(公告)号：EP3181870A1

    公开(公告)日：2017-06-21

    申请号：EP16204844.1

    申请日：2016-12-16

    Applicant: United Technologies Corporation

    Inventor： PASCU, Victor ,  JONES, Anthony C.

    IPC: F02C9/18 ,  F04D27/02

    Abstract: Methods and systems for a gas turbine engine (100; 200) comprising a modulated bleed valve (360) are provided. The gas turbine engine (100; 200; 400) may comprise a turbine nozzle (285) coupled to a controller (350), a modulated bleed valve (360) in communication with the controller (350), and a tangible, non-transitory memory providing instructions to the controller (350) to perform operations. The operations may include receiving parameter values (371, 372, 373) from the parameter sensor (370) at various times, determining desired bleed airflows to flow through the modulated bleed valve (360) at various times, and/or commanding the modulated bleed valve (360) to assume an open configuration or a closed configuration at various times. The modulated bleed valve (360) may be configured to allow bleed airflow (340) to bypass a nozzle choke area (286; 386) of the turbine nozzle (285) and join a nozzle airflow (225; 325).

    Abstract translation: 提供了用于包括调制排气阀（360）的燃气涡轮发动机（100; 200）的方法和系统。 燃气涡轮发动机（100; 200; 400）可以包括联接到控制器（350）的涡轮喷嘴（285），与控制器（350）连通的调制泄放阀（360），以及有形非瞬态 存储器向控制器（350）提供指令以执行操作。 操作可以包括在各种时间从参数传感器（370）接收参数值（371,372,373），确定期望的放气气流在各种时间流过调制的放气阀（360），和/或命令调制的放气 阀360在各种时间呈现打开构型或闭合构型。 调节泄放阀（360）可以构造成允许泄放气流（340）绕过涡轮喷嘴（285）的喷嘴阻塞区域（286; 386）并且接合喷嘴气流（225; 325）。

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