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1. 发明申请

WO2016167925A1 INLET GUIDE VANE CONTROL FOR AIRCRAFT SINGLE ENGINE OPERATION 审中-公开
标题翻译：用于飞机单发动机操作的入口导向挡板控制
公开(公告)号：WO2016167925A1
公开(公告)日：2016-10-20
申请号：PCT/US2016/023622
申请日：2016-03-22
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： SIMONETTI, Joseph Lawrence
IPC分类号： B64C27/04 , B64C27/18 , F02C9/22 , F02C9/54
CPC分类号： F02C7/042 , B64C27/04 , B64C27/06 , B64D27/10 , B64D33/02 , B64D35/08 , B64D2033/0273 , F02C7/26 , F02C9/22 , F02C9/42 , F02C9/54 , F05D2220/323 , F05D2220/329 , F05D2260/85
摘要： A method of operating a multi-engine, rotary wing aircraft in a single engine, in-flight mode, the method includes stopping a first engine while operating a second engine; closing variable inlet guide vanes on the first engine; and turning a gas generator of the first engine at a reference rotational speed.
摘要翻译：一种在单个发动机中运行多发动机旋转翼型飞行器的方法，所述方法包括：在操作第二发动机的同时停止第一发动机; 关闭第一引擎上的可变入口导叶; 并以参考旋转速度转动第一发动机的气体发生器。

2. 发明申请

WO2015160679A1 ENGINE INLET CONFIGURATION 审中-公开
标题翻译：发动机入口配置
公开(公告)号：WO2015160679A1
公开(公告)日：2015-10-22
申请号：PCT/US2015/025507
申请日：2015-04-13
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： BOFILL, Steven , CHASEN, Scott A. , SIMONETTI, Joseph Lawrence , LAMB, Donald William, Jr.
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0246 , B64D2033/0253
摘要： An engine inlet assembly includes an inlet duct having a first inlet duct leg and a second inlet duct leg, the first inlet duct leg and the second inlet duct leg extending toward a common inlet duct outlet located at an engine inlet. The first inlet duct leg and the second inlet duct leg are fixedly secured to an airframe of an aircraft at an air inlet. The duct outlet has a floating interface with the engine inlet.
摘要翻译：发动机入口组件包括具有第一入口管道腿部和第二入口管道腿部的入口管道，第一入口管道腿部和第二入口管道腿部朝向位于发动机入口处的公共入口管道出口延伸。第一入口管道腿和第二入口管道腿在空气入口处固定地固定到飞行器的机身上。管道出口具有与发动机入口的浮动接口。

3. 发明申请

WO2016140866A1 GAS TURBINE EXHAUST ASSEMBLY 审中-公开
标题翻译：气体涡轮排气装置
公开(公告)号：WO2016140866A1
公开(公告)日：2016-09-09
申请号：PCT/US2016/019627
申请日：2016-02-25
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： SIMONETTI, Joseph Lawrence , LAMB, JR., Donald William , NEERARAMBAM, Shyam
IPC分类号： F02K1/82
CPC分类号： F01D25/30 , F02K1/386 , F02K1/82 , F05D2220/329 , F05D2240/125
摘要： A gas turbine exhaust assembly includes an exhaust flow path configured to receive an exhaust flow from a gas turbine engine, the exhaust flow path defined by an inner hub and a radially outer wall. The gas turbine exhaust assembly also includes a plurality of vanes circumferentially spaced from each other and operatively coupled to the radially outer wall of the exhaust flow path, each of the plurality of vanes extending only partially toward the inner hub and terminating at an inner end of the vanes, the inner end defining an open portion.
摘要翻译：燃气轮机排气组件包括排气流动路径，其构造成接收来自燃气涡轮发动机的排气流，由内毂和径向外壁限定的排气流路。燃气轮机排气组件还包括彼此周向间隔开的并且可操作地联接到排气流动路径的径向外壁的多个叶片，所述多个叶片中的每一个叶片仅部分地朝内轮毂延伸并且终止于叶片，内端限定开口部分。

4. 发明申请

WO2015133994A1 ELECTRICAL AUGMENTATION OF A GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机的电气补充
公开(公告)号：WO2015133994A1
公开(公告)日：2015-09-11
申请号：PCT/US2014/020084
申请日：2014-03-04
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： BOURNE, Frederick L. , BYSTRY, Mark Denton, Jr. , SIMONETTI, Joseph Lawrence
IPC分类号： F01D15/10 , F02C6/14 , H02P9/00
CPC分类号： F02C6/14 , F01D15/10 , F01D21/003 , F01D21/14 , F02C3/04 , F02N11/08 , F05D2220/32 , F05D2240/35 , F05D2240/60 , F05D2270/04
摘要： One aspect is an electrical augmentation system for a gas turbine engine. The electrical augmentation system includes an electric motor operably coupled to a shaft of the gas turbine engine, and an energy storage device operable to provide a temporary increased current source to the electric motor. The electrical augmentation system includes a control system having a torque demand anticipation circuit operable to determine an anticipated torque increase condition for the gas turbine engine. Based on the anticipated torque increase condition, the torque demand anticipation circuit commands a temporary torque increase by the electric motor using the energy storage device.
摘要翻译：一个方面是用于燃气涡轮发动机的电增加系统。电增加系统包括可操作地联接到燃气涡轮发动机的轴的电动马达和可操作以向电动机提供临时增加的电流源的能量存储装置。电增加系统包括具有扭矩需求预期电路的控制系统，其可操作以确定燃气涡轮发动机的预期转矩增加条件。基于预期的转矩增加条件，转矩需求预期电路通过使用能量存储装置的电动机来指令暂时的转矩增加。

5. 发明申请

WO2017015341A1 CONTROL SYSTEM FOR ROTORCRAFT IN-FLIGHT ENGINE RESTARTING 审中-公开
标题翻译：旋转发动机起重机的控制系统
公开(公告)号：WO2017015341A1
公开(公告)日：2017-01-26
申请号：PCT/US2016/043094
申请日：2016-07-20
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： STRAUSS, Michael Peter , DEVITA, Michael Joseph , BYSTRY, JR., Mark Denton , SIMONETTI, Joseph Lawrence , PALMER, Carl A.
IPC分类号： B64C27/12 , B64D31/00 , B64D31/06 , B64D31/14 , F02C7/26
CPC分类号： B64D31/06 , B64C27/12 , B64D27/14 , B64D31/00 , B64D31/14 , B64D45/00 , B64D2045/0085 , F02C7/262 , F02C7/268 , F05D2220/329 , F05D2260/40311 , F05D2260/80 , F05D2260/85 , F05D2270/093
摘要： A control system for an in-flight engine restart system of a rotorcraft includes an engine control unit that controls and detects status of an engine. The control system also includes a flight control computer that communicates with the engine control unit, an engine operation control system, and a pilot interface including pilot controls. The engine operation control system includes a processor that initiates a health check of the in-flight engine restart system to determine an in-flight engine restart system status. The engine operation control system processes engine mode of operation commands to establish an engine mode of operation, and delivers commands to aspects of the in-flight engine restart system including the engine control unit based on processing of the engine mode of operation commands. The engine operation control system reports the in-flight engine restart system status and results of the engine mode of operation commands to the flight control computer.
摘要翻译：用于旋翼航空器的飞行中发动机重起系统的控制系统包括控制和检测发动机状态的发动机控制单元。控制系统还包括与发动机控制单元进行通信的飞行控制计算机，发动机操作控制系统和包括先导控制的导频接口。发动机操作控制系统包括处理器，其启动飞行中发动机重起系统的健康检查以确定飞行中发动机重起系统状态。发动机操作控制系统处理发动机操作模式命令以建立发动机操作模式，并且基于处理发动机操作命令的处理，向包括发动机控制单元的飞行中发动机重起系统的各个方面提供命令。发动机运行控制系统向飞行控制计算机报告飞行中的发动机重起系统状态和发动机操作模式的结果。

6. 发明申请

WO2014182616A3 SUPPLEMENTAL POWER FOR REDUCTION OF PRIME MOVER 审中-公开
公开(公告)号：WO2014182616A3
公开(公告)日：2014-11-13
申请号：PCT/US2014/036791
申请日：2014-05-05
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： SIMONETTI, Joseph Lawrence , BYSTRY, Mark Denton , DEVITA, Michael Joseph , TARASCIO, Matthew J. , STRAUSS, Michael Peter , REEVE, Hayden M. , DESAI, Niranjan , ST. ROCK, Brian , LENTS, Charles E. , ZEIDNER, Lawrence E. , SMILEY, Alfred Russell
IPC分类号： B64D41/00
摘要： Embodiments are directed to selecting, by a computing device comprising a processor, the size of at least one prime mover associated with an aircraft to satisfy a baseline power requirement for operation of the aircraft during a steady state load condition, selecting at least one power source configuration to supplement power provided by the at least one prime mover during a transient load condition associated with the operation of the aircraft, and selecting, by the computing device, a parameter of the at least one power source configuration to provide a total power in an amount that is greater than a threshold during the transient condition.

7. 发明申请

WO2013177263A1 ENGINE INLET 审中-公开
标题翻译：发动机进线
公开(公告)号：WO2013177263A1
公开(公告)日：2013-11-28
申请号：PCT/US2013/042195
申请日：2013-05-22
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： LAMB, Donald William Jr. , SIMONETTI, Joseph Lawrence
IPC分类号： F02C7/04 , B64D33/02
CPC分类号： F02C7/04 , B64D33/02 , B64D2033/0246 , F05D2260/606
摘要： An inlet duct for an engine or multiple engines includes two or more joining duct legs and a pressure relief pathway located at each duct leg to condition inlet airflow from the duct legs. A method of operating an aircraft includes urging an inlet airflow into two or more duct openings disposed at a fuselage of the aircraft. The inlet airflow is urged through two or more converging inlet duct legs extending from the two or more duct openings toward an engine inlet. A portion of the inlet airflow is flowed from at least one inlet duct leg of the two or more inlet duct legs into a pressure relief pathway. An inlet duct for an engine or multiple engines includes one or more inlet duct legs and a bypass leg extending from an inlet duct leg of the one or more inlet duct legs through a bypass opening.
摘要翻译：用于发动机或多个发动机的入口管道包括两个或更多个连接管道腿和位于每个管道腿部处以调节来自管道腿的入口气流的压力释放通路。一种操作飞行器的方法包括将入口气流推到布置在飞行器的机身上的两个或更多个管道开口中。入口气流通过从两个或更多个管道开口延伸到发动机入口的两个或更多个会聚的入口管道支柱被推动。入口气流的一部分从两个或更多个入口管道腿的至少一个入口管道腿流入压力释放通路。用于发动机或多个发动机的入口管道包括一个或多个入口管道腿和从一个或多个入口管道腿的入口管道腿通过旁路开口延伸的旁路腿。

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