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公开(公告)号：US4864820A
公开(公告)日：1989-09-12
申请号：US111397
申请日：1987-10-22
CPC分类号： F02K1/78 , B64D33/04 , F02C6/206 , F02K3/062 , Y02T50/671
摘要： An exhaust nozzle extends from an engine nacelle and has an opening disposed at an acute angle such that the exhaust stream is blown over a length of the propeller blade. The opening has a plurality of guide vanes disposed therein to shape the exhaust stream most effectively. By spreading the exhaust stream over the length of a propeller, mixing of the exhaust stream with ambient air is maximized, thereby lowering the temperature of the exhaust stream to tolerable levels.
摘要翻译： 排气喷嘴从发动机舱延伸并且具有以锐角设置的开口，使得排气流在螺旋桨叶片的长度上吹动。 开口具有设置在其中的多个导向叶片以最有效地形成排气流。 通过将排气流散布在螺旋桨的长度上，排气流与环境空气的混合最大化，从而将排气流的温度降低到可承受水平。
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公开(公告)号：US08726632B2
公开(公告)日：2014-05-20
申请号：US12832280
申请日：2010-07-08
IPC分类号： B63H11/00
CPC分类号： F02K1/165 , F02K1/06 , F02K1/15 , F02K3/06 , F05D2260/80 , F05D2270/09 , F05D2270/092 , Y02T50/671 , Y10T29/4932 , Y10T137/0536
摘要： A method of providing a slim-line nacelle for a gas turbine engine includes the steps of detecting a windmilling condition and increasing a discharge airflow area of a variable area fan nozzle in response to the detection of the windmilling condition.
摘要翻译： 为燃气涡轮发动机提供细线机舱的方法包括响应于风车状况的检测来检测风车状况和增加可变区域风扇喷嘴的排放气流面积的步骤。
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公开(公告)号：US20100269512A1
公开(公告)日：2010-10-28
申请号：US12832254
申请日：2010-07-08
IPC分类号： F02K1/18
CPC分类号： F02K1/165 , F02K1/06 , F02K1/15 , F02K3/06 , F05D2260/80 , F05D2270/09 , F05D2270/092 , Y02T50/671 , Y10T29/4932 , Y10T137/0536
摘要： A gas turbine engine system includes nacelle, a first boundary layer control device, a second boundary layer control device, at least one sensor, and a controller. The nacelle is defined about an axis and includes an inlet lip section, an inlet internal diffuser section, and a variable area fan nozzle moveable to influence a discharge airflow area of the nacelle. The first boundary layer control device is positioned near the inlet lip section and is actuable to introduce a first airflow at the inlet lip section. The second boundary layer control device is positioned near the inlet internal diffuser section and is actuable to introduce a second airflow at the inlet internal diffuser section. The sensor produces a signal that represents an operability condition. The controller receives the signal and simultaneously moves the variable area fan nozzle and actuates the first boundary layer control device and the second boundary layer control device in response to receiving the signal to achieve a slim-line nacelle.
摘要翻译： 燃气涡轮发动机系统包括机舱，第一边界层控制装置，第二边界层控制装置，至少一个传感器和控制器。 机舱围绕轴限定，包括入口唇部，入口内部扩散器部分和可移动以影响机舱的排放气流区域的可变区域风扇喷嘴。 第一边界层控制装置位于入口唇部附近，并且可致动以在入口唇部引入第一气流。 第二边界层控制装置位于入口内部扩散器部分附近并且可致动以在入口内部扩散器部分处引入第二气流。 传感器产生表示可操作性条件的信号。 控制器接收信号，同时移动可变区域风扇喷嘴，响应于接收到信号而致动第一边界层控制装置和第二边界层控制装置，以实现细长的机舱。
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公开(公告)号：US06837038B2
公开(公告)日：2005-01-04
申请号：US10271695
申请日：2002-10-15
申请人： Donald C. Eiler , Michael J. Larkin
发明人： Donald C. Eiler , Michael J. Larkin
IPC分类号： F02C3/10 , B64D27/02 , B64D41/00 , F01D5/02 , F02C3/073 , F02C3/13 , F02C6/08 , F02C7/042 , F02C7/32 , F02K1/08 , F02K1/78 , F02K3/062 , F02K3/075 , F02K3/02
CPC分类号： B64D41/00 , B64D27/02 , B64D2033/0213 , F01D5/022 , F02C3/073 , F02C3/13 , F02C7/32 , F02K3/075 , F05D2220/50
摘要： The present invention relates to a variable cycle boost propulsor system for use on an aircraft. The variable cycle boost propulsor system includes an engine, a turbine, a fan connected to the turbine, and a valve system for delivering the fluid output from the engine to the turbine for driving the turbine and the fan and thereby generating additional thrust for the aircraft. The engine is also used to provide power to one or more systems onboard the aircraft.
摘要翻译： 本发明涉及一种用于飞机上的可变循环升压推进系统。 可变循环增压推进系统包括发动机，涡轮机，连接到涡轮机的风扇和用于将来自发动机的流体输出传递到涡轮机以用于驱动涡轮机和风扇并由此产生用于飞行器的附加推力的阀系统 。 发动机还用于向飞机上的一个或多个系统提供动力。
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公开(公告)号：US08353164B2
公开(公告)日：2013-01-15
申请号：US12832254
申请日：2010-07-08
IPC分类号： F02K1/00
CPC分类号： F02K1/165 , F02K1/06 , F02K1/15 , F02K3/06 , F05D2260/80 , F05D2270/09 , F05D2270/092 , Y02T50/671 , Y10T29/4932 , Y10T137/0536
摘要： A gas turbine engine system includes nacelle, a first boundary layer control device, a second boundary layer control device, at least one sensor, and a controller. The nacelle is defined about an axis and includes an inlet lip section, an inlet internal diffuser section, and a variable area fan nozzle moveable to influence a discharge airflow area of the nacelle. The first boundary layer control device is positioned near the inlet lip section and is actuable to introduce a first airflow at the inlet lip section. The second boundary layer control device is positioned near the inlet internal diffuser section and is actuable to introduce a second airflow at the inlet internal diffuser section. The sensor produces a signal that represents an operability condition. The controller receives the signal and simultaneously moves the variable area fan nozzle and actuates the first boundary layer control device and the second boundary layer control device in response to receiving the signal to achieve a slim-line nacelle.
摘要翻译： 燃气涡轮发动机系统包括机舱，第一边界层控制装置，第二边界层控制装置，至少一个传感器和控制器。 机舱围绕轴限定，包括入口唇部，入口内部扩散器部分和可移动以影响机舱的排放气流区域的可变区域风扇喷嘴。 第一边界层控制装置位于入口唇部附近，并且可致动以在入口唇部引入第一气流。 第二边界层控制装置位于入口内部扩散器部分附近并且可致动以在入口内部扩散器部分处引入第二气流。 传感器产生表示可操作性条件的信号。 控制器接收信号，同时移动可变区域风扇喷嘴，响应于接收到信号而致动第一边界层控制装置和第二边界层控制装置，以实现细长的机舱。
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公开(公告)号：US20100269486A1
公开(公告)日：2010-10-28
申请号：US12832280
申请日：2010-07-08
IPC分类号： F02K1/18
CPC分类号： F02K1/165 , F02K1/06 , F02K1/15 , F02K3/06 , F05D2260/80 , F05D2270/09 , F05D2270/092 , Y02T50/671 , Y10T29/4932 , Y10T137/0536
摘要： A method of providing a slim-line nacelle for a gas turbine engine includes the steps of detecting a windmilling condition and increasing a discharge airflow area of a variable area fan nozzle in response to the detection of the windmilling condition.
摘要翻译： 为燃气涡轮发动机提供细线机舱的方法包括响应于风车状况的检测来检测风车状况和增加可变区域风扇喷嘴的排放气流面积的步骤。
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公开(公告)号：US07454894B2
公开(公告)日：2008-11-25
申请号：US11006306
申请日：2004-12-07
申请人： Michael J. Larkin , Donald C. Eiler
发明人： Michael J. Larkin , Donald C. Eiler
摘要： A gas turbine engine is provided with an oil cooler which receives cooling air from a turbo fan. At times when the turbo fan is operating at lower speeds, the volume of cooling air is also lowered. At such times, a supplemental airflow is provided over heat exchangers in the oil cooler. The supplemental airflow includes a supplemental airflow fan and valve for selectively controlling the supplemental airflow over the heat exchangers.
摘要翻译： 燃气涡轮发动机设置有从涡轮风扇接收冷却空气的油冷却器。 有时涡轮风扇以较低的速度工作时，冷却空气的体积也会降低。 在这种时候，在油冷却器中的热交换器上提供补充气流。 补充气流包括补充气流风扇和阀，用于选择性地控制热交换器上的补充气流。
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公开(公告)号：US5689999A
公开(公告)日：1997-11-25
申请号：US516749
申请日：1995-08-18
CPC分类号： A61G5/12 , A61G5/1054 , A61G5/125 , A61G5/128 , F16C11/10 , B60N2/0806 , Y10T403/32352 , Y10T403/32451 , Y10T74/20636
摘要： Apparatus for enabling and disabling relative rotary movements between two members rotatable about a common axis comprises a plurality of circumferentially spaced locking pins carried by one of the members and a plurality of circumferentially spaced sockets in the other of the members, the pins and sockets being uniformly spaced from the axis of rotation and each of the sockets being of such size as to accommodate any one of the pins. The number of pins is different from the number of sockets. The angular spacing between adjacent pins is uniform, and the angular spacing between adjacent sockets is uniform, but different from the angular spacing between adjacent pins. The angular spacing between the pins and the sockets defines a ratio which is not a whole integer.
摘要翻译： 用于启用和禁用可围绕公共轴线旋转的两个构件之间的相对旋转运动的装置包括多个周向间隔开的锁定销，所述锁定销由所述构件之一承载并且在所述构件的另一个中具有多个周向间隔开的插座，所述销和插座均匀地 与旋转轴线间隔开，并且每个插座具有适于任何一个销的尺寸。 引脚数量与插座数量不同。 相邻引脚之间的角度间隔是均匀的，并且相邻插座之间的角度间隔是均匀的，但不同于相邻引脚之间的角度间隔。 引脚和插座之间的角度间隔定义了一个不是整数的比例。
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公开(公告)号：US07797944B2
公开(公告)日：2010-09-21
申请号：US11584030
申请日：2006-10-20
IPC分类号： F02K1/00
CPC分类号： F02K1/165 , F02K1/06 , F02K1/15 , F02K3/06 , F05D2260/80 , F05D2270/09 , F05D2270/092 , Y02T50/671 , Y10T29/4932 , Y10T137/0536
摘要： A nacelle assembly for a gas turbine engine includes a nacelle, a variable area fan nozzle, a sensor that detects a windmilling condition and a controller that communicates with the sensor. The variable area fan nozzle is moveable between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than the first discharge airflow area in response to detecting the windmilling condition.
摘要翻译： 用于燃气涡轮发动机的机舱组件包括机舱，可变区域风扇喷嘴，检测风车状态的传感器和与传感器通信的控制器。 可变区域风扇喷嘴可响应于检测到风切割状态而在具有第一排出气流区域的第一位置和具有大于第一排出气流区域的第二排放气流区域的第二位置之间移动。
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公开(公告)号：US20080092548A1
公开(公告)日：2008-04-24
申请号：US11584030
申请日：2006-10-20
IPC分类号： F02K1/00
CPC分类号： F02K1/165 , F02K1/06 , F02K1/15 , F02K3/06 , F05D2260/80 , F05D2270/09 , F05D2270/092 , Y02T50/671 , Y10T29/4932 , Y10T137/0536
摘要： A nacelle assembly for a gas turbine engine includes a nacelle, a variable area fan nozzle, a sensor that detects a windmilling condition and a controller that communicates with the sensor. The variable area fan nozzle is moveable between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than the first discharge airflow area in response to detecting the windmilling condition.
摘要翻译： 用于燃气涡轮发动机的机舱组件包括机舱，可变区域风扇喷嘴，检测风车状态的传感器和与传感器通信的控制器。 可变区域风扇喷嘴可响应于检测到风切割状态而在具有第一排出气流区域的第一位置和具有大于第一排出气流区域的第二排放气流区域的第二位置之间移动。
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