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1. 发明授权

US07698896B2 Compact, light weight eductor oil cooler plenum and surge flow plenum design 有权
标题翻译：紧凑，重量轻的喷射器油冷却器集气室和浪涌气流通风设计
公开(公告)号：US07698896B2
公开(公告)日：2010-04-20
申请号：US11303180
申请日：2005-12-15
申请人： Yogendra Y. Sheoran , Cristopher Frost
发明人： Yogendra Y. Sheoran , Cristopher Frost
IPC分类号： F02K1/00
CPC分类号： F02C7/32 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F01D25/18 , Y02T50/671
摘要： An eductor assembly is provided that includes a primary nozzle, a cooler plenum, and a surge plenum. In one embodiment, and by way of example only, the primary nozzle is configured to accelerate and discharge turbine exhaust gas therefrom and the cooler plenum surrounds the primary nozzle and includes at least a fluid inlet and a fluid outlet. The surge plenum partially surrounds the primary nozzle and the cooler plenum and includes at least a fluid inlet and a fluid outlet. The surge plenum fluid outlet axially aligns and is coterminous with the cooler plenum fluid outlet.
摘要翻译：提供了一种喷射器组件，其包括主喷嘴，较冷气室和浪涌气室。在一个实施例中，仅作为示例，主喷嘴构造成从其中加速和排放涡轮废气，并且冷却器压力室围绕主喷嘴并且至少包括流体入口和流体出口。浪涌气室部分地围绕主喷嘴和冷却器气室，并且至少包括流体入口和流体出口。浪涌增压室流体出口轴向对准并与冷却器增压室流体出口相连。

2. 发明授权

US07665694B2 Dual action inlet door and method for use thereof 失效
标题翻译：双作用入口门及其使用方法
公开(公告)号：US07665694B2
公开(公告)日：2010-02-23
申请号：US11691679
申请日：2007-03-27
申请人： Jeffrey M. Hein , Nicholas A. Williams , Yogendra Y. Sheoran , Cecilia S. Lam , Ora Morency Cowans , Benjamen Kurt Higuera , Andrew Stephen Peduchi , Ravisha Pramod Sellahewa , Daniel Brown
发明人： Jeffrey M. Hein , Nicholas A. Williams , Yogendra Y. Sheoran , Cecilia S. Lam , Ora Morency Cowans , Benjamen Kurt Higuera , Andrew Stephen Peduchi , Ravisha Pramod Sellahewa , Daniel Brown
IPC分类号： B64D33/02 , B64C1/14
CPC分类号： F02C7/04 , B64D33/02 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F02C7/045 , F02C7/32 , F05D2220/50 , F05D2260/96
摘要： An inlet door assembly and method for reducing noise from an auxiliary power unit (APU) contained within an aircraft housing is provided. The inlet assembly includes an inlet duct, an actuator, and a door. The inlet duct is configured to extend from the auxiliary power unit to the aircraft housing and has a sidewall that defines a flow passage through which APU noise propagates. The actuator is disposed at least partially within the inlet duct. The door coupled to the actuator. The actuator is also configured to selectively rotate the door between at least a first position, in which at least a portion of the door deflects APU noise in a first direction, and a second position, in which at least a portion of the door deflects the APU noise in a second direction.
摘要翻译：提供了一种用于降低包含在飞行器壳体内的辅助动力单元（APU）的噪声的入口门组件和方法。入口组件包括入口管道，致动器和门。入口管道被构造成从辅助动力单元延伸到飞行器壳体，并且具有限定APU噪声传播通过的流动通道的侧壁。致动器至少部分地设置在入口管道内。门连接到执行机构。致动器还构造成在至少第一位置之间选择性地旋转门，其中门的至少一部分在第一方向上偏转APU噪声和第二位置，其中门的至少一部分偏转 APU噪声在第二个方向。

3. 发明申请

US20080118347A1 Turbine engine diffusing exhaust muffler 失效
标题翻译：涡轮发动机扩散排气消声器
公开(公告)号：US20080118347A1
公开(公告)日：2008-05-22
申请号：US11603424
申请日：2006-11-22
申请人： Jeffrey A. Turner , Yogendra Y. Sheoran , Bruce D. Bouldin
发明人： Jeffrey A. Turner , Yogendra Y. Sheoran , Bruce D. Bouldin
IPC分类号： F01D25/30
CPC分类号： F01D25/30 , F05D2250/191 , F05D2260/96
摘要： An exhaust muffler is provided for a turbine engine with at least first and second exhaust outlets. The exhaust muffler includes a first arm configured to be coupled to the first exhaust outlet of the turbine engine. The first arm includes an outer surface, and an inner surface that defines a first exhaust cavity. The first arm further includes a plurality of perforations extending between the inner and outer surfaces. The exhaust muffler further includes a second arm coupled to the first arm and configured to be coupled to the second exhaust outlet of the turbine engine. The second arm includes an outer surface, and an inner surface that defines a second exhaust cavity. The second arm also includes a plurality of perforations extending between the inner and outer surfaces.
摘要翻译：为具有至少第一和第二排气出口的涡轮发动机提供排气消音器。排气消声器包括构造成联接到涡轮发动机的第一排气出口的第一臂。第一臂包括外表面和限定第一排气腔的内表面。第一臂还包括在内表面和外表面之间延伸的多个穿孔。排气消声器还包括联接到第一臂并被配置为联接到涡轮发动机的第二排气出口的第二臂。第二臂包括外表面和限定第二排气腔的内表面。第二臂还包括在内表面和外表面之间延伸的多个穿孔。

4. 发明授权

US06520738B2 Plenum entry bulk swirl generator 有权
公开(公告)号：US06520738B2
公开(公告)日：2003-02-18
申请号：US09809588
申请日：2001-03-15
申请人： Yogendra Y. Sheoran , Bruce D. Bouldin
发明人： Yogendra Y. Sheoran , Bruce D. Bouldin
IPC分类号： F01D2500
CPC分类号： B64D41/00 , B64D33/02 , B64D2033/0213 , F02C7/04 , F05D2220/50 , F15D1/04
摘要： A swirl generator for creating bulk swirl in a compressor plenum in the opposite direction to the direction of rotation of the compressor rotor. The generator includes a continuous flow passageway formed by an inlet duct and a compressor forming an angle in the range of about 0°-180° to one another. A non-uniform velocity gradient is created by forming an area of non-uniform cross-sectional area within the flow passageway. The non-uniform area may comprise a ramp with a tapered end line, a rounded line of intersection, a fillet or by lengthening one side wall of the inlet duct relative to the opposite side wall. Preferably, the non-uniform cross sectional area uniformly tapers from ones sidewall of the flow passageway to the opposite sidewall.

5. 发明申请

US20080057848A1 Venturi gate valve assembly for an auxiliary power unit 审中-公开
标题翻译：用于辅助动力单元的文丘里闸阀组件
公开(公告)号：US20080057848A1
公开(公告)日：2008-03-06
申请号：US11515120
申请日：2006-08-31
申请人： Rick S. Gray , Eric J. Shepard , Cecilia S. Lam , Yogendra Y. Sheoran , Norman J. Hahn
发明人： Rick S. Gray , Eric J. Shepard , Cecilia S. Lam , Yogendra Y. Sheoran , Norman J. Hahn
IPC分类号： B60H1/00
CPC分类号： B64D41/00 , B64D2033/0213 , F01D17/145 , F05D2250/232 , Y02T50/671
摘要： A venturi gate valve assembly for extraction of bleed air flow from an auxiliary power unit (APU) and an APU compartment including the venturi gate valve assembly. The venturi gate valve assembly is configured to isolate and restrict bleed air flow from the APU via an extraction conduit. The venturi gate valve assembly includes an upstream valve flange, a throat area, a moveable valve gate, and a downstream valve flange, in fluid communication defining a bleed air flow path. A conical shaped diffuser is defined along the bleed air flow path from the throat area to the downstream flange.
摘要翻译：一种文丘里闸阀组件，用于从辅助动力单元（APU）和包括文丘里闸阀组件的APU隔室抽取出气流。文丘里闸阀组件被配置为隔离并限制经由抽出导管从APU排出的气流。文丘里闸阀组件包括限定出气流动路径的流体连通的上游阀法兰，喉部区域，可动阀门和下游阀法兰。沿着从喉部区域到下游凸缘的排气流动路径限定圆锥形扩散器。

6. 发明授权

US06264137B1 Inlet vortex bustor and ice protector for auxiliary power units 失效
标题翻译：辅助动力装置的入口涡流破碎机和防冰器
公开(公告)号：US06264137B1
公开(公告)日：2001-07-24
申请号：US09514203
申请日：2000-02-25
申请人： Yogendra Y. Sheoran
发明人： Yogendra Y. Sheoran
IPC分类号： B64B124
CPC分类号： F02C3/32 , B64D33/02 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F05D2220/40 , F05D2260/601
摘要： An air inlet assembly for bringing air to an auxiliary power unit mounted in the compartment of an aircraft. The assembly includes a duct extending from an intake contoured to conform to the to the aircraft fuselage to an exit coupled to the inlet plenum of the auxiliary power unit. A first door hingeably mounted to the aft side of said intake and moveable from an open position to a closed position where said first door lies flush against intake, said first door having a closing wall and two side walls and a second door hingeably mounted to the forward end of said intake, said second door having a plate with two inwardly extending walls, each of said inwardly extending walls hinged to one of said side walls so that the second door rotates with said first door. During ground operation air that would have swirled around the side walls of the first door thus generating inlet corner vortices are now blocked by the side walls of the second door.
摘要翻译：用于将空气引导到安装在飞行器舱室中的辅助动力单元的空气入口组件。该组件包括一个从进气轮廓延伸到与飞机机身一致的导管，连接到辅助动力单元的入口气室。第一门铰接地安装在所述入口的后侧，并且可从打开位置运动到关闭位置，在所述关闭位置，所述第一门与入口齐平，所述第一门具有封闭壁和两个侧壁以及可铰接地安装在所述第二门上的第二门所述第二门的前端具有带有两个向内延伸的壁的板，每个所述向内延伸的壁铰接到所述侧壁中的一个，使得所述第二门与所述第一门旋转。在地面操作期间，将围绕第一门的侧壁旋转的空气因此产生入口角旋涡现在被第二门的侧壁阻挡。

7. 发明授权

US07210652B2 Dual action inlet door and method for use thereof 有权
标题翻译：双作用入口门及其使用方法
公开(公告)号：US07210652B2
公开(公告)日：2007-05-01
申请号：US11299116
申请日：2005-12-08
申请人： Jeffrey M. Hein , Nicholas A. Williams , Yogendra Y. Sheoran , Cecilia S. Lam , Ora Morency Cowans , Benjamen Kurt Higuera , Andrew Stephen Peduchi , Ravisha Pramod Sellahewa , Daniel Brown
发明人： Jeffrey M. Hein , Nicholas A. Williams , Yogendra Y. Sheoran , Cecilia S. Lam , Ora Morency Cowans , Benjamen Kurt Higuera , Andrew Stephen Peduchi , Ravisha Pramod Sellahewa , Daniel Brown
IPC分类号： B64D33/02
CPC分类号： F02C7/04 , B64D33/02 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F02C7/045 , F02C7/32 , F05D2220/50 , F05D2260/96
摘要： An inlet door assembly and method for reducing noise from an auxiliary power unit (APU) contained within an aircraft housing is provided. The inlet assembly includes an inlet duct, an actuator, and a door. The inlet duct is configured to extend from the auxiliary power unit to the aircraft housing and has a sidewall that defines a flow passage through which APU noise propagates. The actuator is disposed at least partially within the inlet duct. The door coupled to the actuator. The actuator is also configured to selectively rotate the door between at least a first position, in which at least a portion of the door deflects APU noise in a first direction, and a second position, in which at least a portion of the door deflects the APU noise in a second direction.
摘要翻译：提供了一种用于降低包含在飞行器壳体内的辅助动力单元（APU）的噪声的入口门组件和方法。入口组件包括入口管道，致动器和门。入口管道被构造成从辅助动力单元延伸到飞行器壳体，并且具有限定APU噪声传播通过的流动通道的侧壁。致动器至少部分地设置在入口管道内。门连接到执行机构。致动器还构造成在至少第一位置之间选择性地旋转门，其中门的至少一部分在第一方向上偏转APU噪声和第二位置，其中门的至少一部分偏转 APU噪声在第二个方向。

8. 发明授权

US06615576B2 Tortuous path quiet exhaust eductor system 失效
公开(公告)号：US06615576B2
公开(公告)日：2003-09-09
申请号：US10054003
申请日：2002-01-21
申请人： Yogendra Y. Sheoran , Daniel V. Brown , David H. Edmonds
发明人： Yogendra Y. Sheoran , Daniel V. Brown , David H. Edmonds
IPC分类号： F02C708
CPC分类号： B64D33/06 , B64D41/00 , B64D2041/002 , F02C7/14 , F02K1/36 , F02K1/827 , F05D2220/50 , F05D2250/314 , F05D2260/601 , F05D2260/96 , Y02T50/44 , Y02T50/671 , Y02T50/675
摘要： A tortuous path quiet exhaust eductor system may be mounted to a gas turbine engine, such as commercial aircraft APU. The system includes an oil cooler, eductor primary nozzle, oil cooler air nozzle, and surge air dump nozzle. The primary nozzle, oil cooler air nozzle, and surge air dump nozzle direct exhaust flow to entrain APU compartment cooling air, oil cooling air and surge air in a direction having both radial and axial components with respect to the APU centerline axis. The exhaust flow is directed into an eductor mixing duct angled away from the centerline axis and then is turned to enter an exit duct angled toward the centerline axis so that direct line of sight acoustic paths from the tail pipe exit to the turbine exit are blocked, suppressing core noise. The tail pipe ducts may be acoustically treated, further enhancing noise suppression.

9. 发明授权

US5265408A Exhaust eductor cooling system 失效
标题翻译：排气冷却系统
公开(公告)号：US5265408A
公开(公告)日：1993-11-30
申请号：US835633
申请日：1992-02-13
申请人： Yogendra Y. Sheoran , Marc Schmittenberg , Craig A. Lyon , Charles M. Royalty , Kurt T. Kenzler , Thomas W. Davis
发明人： Yogendra Y. Sheoran , Marc Schmittenberg , Craig A. Lyon , Charles M. Royalty , Kurt T. Kenzler , Thomas W. Davis
IPC分类号： B64D33/08 , B64D41/00 , F02K1/36 , F02G3/00
CPC分类号： B64D41/00 , B64D33/08 , F02K1/36 , B64D2033/0213 , B64D2041/002 , F05D2220/50
摘要： A method and apparatus for cooling the heat generated by a gas turbine engine mounted in a compartment is provided. The apparatus comprises a novel eductor that incorporates a mixer nozzle to entrain sufficient air flow through the compartment to provide all the necessary cooling. The engine's oil cooler is mounted to the eductor so that the entrained air flow passes through it and cools the engine's oil. The novel eductor also has means for receiving a flow of high velocity air from the engine and injecting this air downstream of the mixer nozzle to enhance the entraining of the cooling flow.
摘要翻译：提供了一种用于冷却由安装在隔室中的燃气涡轮发动机产生的热的方法和装置。该装置包括新颖的喷射器，其包括混合器喷嘴以夹带足够的气流通过隔室以提供所有必要的冷却。发动机的油冷却器安装在喷射器上，使得夹带的气流通过它并冷却发动机的油。新型喷射器还具有用于从发动机接收高速空气流并将该空气喷射到混合器喷嘴下游以增强冷却流的夹带的装置。

10. 发明授权

US08162256B2 Launch and capture systems for vertical take-off and landing (VTOL) vehicles 有权
标题翻译：用于垂直起飞和着陆（VTOL）车辆的启动和捕获系统
公开(公告)号：US08162256B2
公开(公告)日：2012-04-24
申请号：US12051552
申请日：2008-03-19
申请人： Emray R. Goossen , Yogendra Y. Sheoran
发明人： Emray R. Goossen , Yogendra Y. Sheoran
IPC分类号： B64F1/00
CPC分类号： B64C39/024 , B64C2201/027 , B64C2201/088 , B64C2201/182 , B64C2201/201 , B64C2201/205 , B64C2201/208 , B64F1/04
摘要： A launch and capture system for capturing a vertical take-off and landing (VTOL) vehicle having a thruster and a duct configured to direct airflow generated by the thruster includes a capture plate and an extension. The capture plate is configured to alter the airflow and generate a force attracting the duct to the capture plate. The extension is coupled to the capture plate, and is configured to at least facilitate holding the VTOL vehicle against the capture plate.
摘要翻译：用于捕获具有推进器和构造成引导由推进器产生的气流的管道的垂直起飞和着陆（VTOL）车辆的发射和捕获系统包括捕获板和延伸部。捕获板被配置为改变气流并产生吸引到捕获板的管道的力。延伸部联接到捕获板，并且被构造成至少有利于将VTOL车辆保持抵靠捕获板。

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