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1. 发明授权

US09752453B2 Airflow modulation system and method 有权
公开(公告)号：US09752453B2
公开(公告)日：2017-09-05
申请号：US14793377
申请日：2015-07-07
申请人： Northrop Grumman Systems Corporation
发明人： George D. Rupp , Trajaen J. Troia
IPC分类号： F02C7/042 , F01D17/12 , F02K7/20 , F02K7/075 , F02K7/16 , F01D5/02 , F01D9/04 , F02K3/02
CPC分类号： F01D17/12 , F01D5/02 , F01D9/04 , F02C7/042 , F02K3/02 , F02K7/075 , F02K7/16 , F02K7/20 , F05D2220/10 , F05D2300/502 , Y02T50/672
摘要： The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.

2. 发明授权

US10006833B1 Method for vortex generator array sizing and placement within offset diffusers 有权
公开(公告)号：US10006833B1
公开(公告)日：2018-06-26
申请号：US15246010
申请日：2016-08-24
申请人： NORTHROP GRUMMAN SYSTEMS CORPORATION
发明人： Nicholas V. Caldwell , Trajaen J. Troia , Richard Crouse
IPC分类号： F03D1/06 , B64F5/00 , G01M15/14 , G01B21/02 , G01B21/16
CPC分类号： G01M15/14 , B64F5/60 , Y02E10/721
摘要： A method for optimizing size and position parameters of an array of vortex generator blades configured on an offset diffuser in an inlet of an aircraft engine. The method includes providing a computational fluid dynamic analysis of air flowing through the diffuser that identifies a height of a local boundary layer at a plurality of positions across the diffuser substantially parallel to the flow of air and a flow velocity vector at each of the plurality of positions at one half of a height of the local boundary layer. The method also includes determining an angle orientation of the blades using the boundary layer height and the flow vector, determining the length and height of the blades using the boundary layer height, and determining the number and spacing of the blades using the width of the diffuser.

3. 发明授权

US09758253B2 Swept gradient boundary layer diverter 有权
公开(公告)号：US09758253B2
公开(公告)日：2017-09-12
申请号：US14750718
申请日：2015-06-25
申请人： NORTHROP GRUMMAN SYSTEMS CORPORATION
发明人： Trajaen J. Troia , John F. Mangus
IPC分类号： B64D33/02 , B64C21/10 , B64C23/06 , B64C23/04 , B64D47/08
CPC分类号： B64D33/02 , B64C21/10 , B64C23/04 , B64C23/06 , B64D47/08 , B64D2033/0226 , B64D2033/026 , Y02T50/162 , Y02T50/166
摘要： A swept gradient air boundary layer diverter for an aircraft. The aircraft includes a fuselage and an air inlet for an engine of the aircraft, where the air inlet includes a cowl at a leading edge of the inlet. The diverter includes a V-shaped ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft. The diverter also includes a V-shaped trough portion formed into the fuselage and being positioned adjacent to and integral with the ramp portion between the ramp portion and the air inlet. Air flowing over the fuselage towards the cowl is expanded and compressed by the ramp portion and the trough portion so as to create pressure gradients that generate vortices to redirect boundary layer airflow around the air inlet.

4. 发明申请

US20150377060A1 Airflow Modulation System and Method 有权
标题翻译：气流调制系统及方法
公开(公告)号：US20150377060A1
公开(公告)日：2015-12-31
申请号：US14793377
申请日：2015-07-07
申请人： Northrop Grumman Systems Corporation
发明人： George D. Rupp , Trajaen J. Troia
IPC分类号： F01D17/12 , F01D5/02 , F01D9/04
CPC分类号： F01D17/12 , F01D5/02 , F01D9/04 , F02C7/042 , F02K3/02 , F02K7/075 , F02K7/16 , F02K7/20 , F05D2220/10 , F05D2300/502 , Y02T50/672
摘要： The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.
摘要翻译：本发明涉及一种机械系统，其调节飞行器入口漫射器中的气流，该飞行器入口漫射器与与中等涡轮发动机和诸如恒定体积燃烧器（CVC）布置或冲压喷气装置的高马赫发动机相结合的飞机发动机结合使用进气口与涡轮机共同形成。调制系统使用铰接锥。当处于缩回位置时，铰接锥体允许飞行器以低速模式操作，因为只有涡轮喷气机接收气流。在最广泛的地方，铰接锥完全覆盖涡轮喷气圆形进气面，排除了涡轮发动机的运行。

5. 发明授权

US09103280B2 Aircraft airflow modulation system and method 有权
标题翻译：飞机气流调节系统及方法
公开(公告)号：US09103280B2
公开(公告)日：2015-08-11
申请号：US13781584
申请日：2013-02-28
申请人： Northrop Grumman Systems Corporation
发明人： George D. Rupp , Trajaen J. Troia
IPC分类号： F02C7/04 , F02C7/042 , F02K7/20 , F02K7/075 , F02K7/16 , F02K3/02
CPC分类号： F01D17/12 , F01D5/02 , F01D9/04 , F02C7/042 , F02K3/02 , F02K7/075 , F02K7/16 , F02K7/20 , F05D2220/10 , F05D2300/502 , Y02T50/672
摘要： The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face directing air solely to the high Mach aircraft engine to allow the aircraft to operate in high speed mode.
摘要翻译：本发明涉及一种机械系统和方法，其调节与整合中等涡轮发动机和诸如恒定体积燃烧室（CVC）排列的高马赫发动机的飞机发动机结合使用的飞行器入口扩散器中的气流，或冲压喷气式排气装置，与涡轮机共同形成进气口。调制系统使用两个铰接部件，一个可移动的空气流动管道和一个铰接锥体。处于第一位置的空气流动管道处于与来自涡轮机的圆形进气面的第一位置专用气流连通，以从进气扩散器接收空气。在该配置中，可膨胀锥体处于缩回位置，并且不会使气流重定向，并允许飞行器以低速模式操作，因为只有涡轮喷气机接收气流。在过渡速度模式中，空气流动管道缩回以允许空气流动到涡轮喷气机和CVC。铰链锥体完全覆盖涡轮喷气圆形进气面，将空气仅引导到高马赫飞机发动机，以使飞机能够以高速运行。

6. 发明授权

US09009966B2 Internal/external single expansion ramp nozzle with integrated third stream 有权
标题翻译：内部/外部单个扩展斜坡喷嘴具有集成的第三个流
公开(公告)号：US09009966B2
公开(公告)日：2015-04-21
申请号：US13842567
申请日：2013-03-15
申请人： Northrop Grumman Systems Corporation
发明人： Shane Bunnag , Gordon Hall , Kelly Strominger , John Tapee , Trajaen J. Troia
IPC分类号： B21K25/00 , F02K1/00 , F02K1/78
CPC分类号： F02K1/00 , F02K1/78 , Y10T29/49 , Y10T29/49323 , Y10T29/49346
摘要： The construction of an internal/external single expansion ramp nozzle (nxSERN), and method of designing the same, is provided. Initial design parameters for primary stream construction are selected and additional parameters are determined by isentropic relations using the selected design parameters and Prandtl-Meyer function. The nozzle throat input and output angles are determined and used to define an initial portion of the nozzle primary stream lower expansion surface. The nozzle primary stream upper expansion surface and an aft portion of the primary stream lower expansion surface are defined using a method of characteristics. Initial and aft portions of the primary stream lower expansion surface are then connected by a straight line to define the primary stream nozzle.
摘要翻译：提供内部/外部单个膨胀斜面喷嘴（nxSERN）的结构及其设计方法。选择初级流构造的初始设计参数，并使用所选设计参数和Prandtl-Meyer函数通过等熵关系确定附加参数。喷嘴喉部输入和输出角度被确定并用于限定喷嘴主流下部膨胀表面的初始部分。使用特征的方法来限定喷嘴主流上部膨胀表面和主流下部膨胀表面的后部。然后通过直线连接主流下扩展表面的初始和后部以限定主流喷嘴。

7. 发明申请

US20140259631A1 INTERNAL/EXTERNAL SINGLE EXPANSION RAMP NOZZLE WITH INTEGRATED THIRD STREAM 有权
标题翻译：内部/外部单个扩展RAMP喷嘴与集成的第三个流
公开(公告)号：US20140259631A1
公开(公告)日：2014-09-18
申请号：US13842567
申请日：2013-03-15
申请人： NORTHROP GRUMMAN SYSTEMS CORPORATION
发明人： Shane Bunnag , Gordon Hall , Kelly Strominger , John Tapee , Trajaen J. Troia
IPC分类号： F02K1/00
CPC分类号： F02K1/00 , F02K1/78 , Y10T29/49 , Y10T29/49323 , Y10T29/49346
摘要： The construction of an internal/external single expansion ramp nozzle (nxSERN), and method of designing the same, is provided. Initial design parameters for primary stream construction are selected and additional parameters are determined by isentropic relations using the selected design parameters and Prandtl-Meyer function. The nozzle throat input and output angles are determined and used to define an initial portion of the nozzle primary stream lower expansion surface. The nozzle primary stream upper expansion surface and an aft portion of the primary stream lower expansion surface are defined using a method of characteristics. Initial and aft portions of the primary stream lower expansion surface are then connected by a straight line to define the primary stream nozzle.
摘要翻译：提供内部/外部单个膨胀斜面喷嘴（nxSERN）的结构及其设计方法。选择初级流构造的初始设计参数，并使用所选设计参数和Prandtl-Meyer函数通过等熵关系确定附加参数。喷嘴喉部输入和输出角度被确定并用于限定喷嘴主流下部膨胀表面的初始部分。使用特征的方法来限定喷嘴主流上部膨胀表面和主流下部膨胀表面的后部。然后通过直线连接主流下扩展表面的初始和后部以限定主流喷嘴。

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