公开(公告)号：US20110036067A1

公开(公告)日：2011-02-17

申请号：US12539451

申请日：2009-08-11

申请人： George D. Rupp ,  Trajaen J. Troia

发明人： George D. Rupp ,  Trajaen J. Troia

IPC分类号： 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。

公开(公告)号：US08429893B2

公开(公告)日：2013-04-30

申请号：US12539451

申请日：2009-08-11

申请人： George D Rupp ,  Trajaen J. Troia

发明人： George D Rupp ,  Trajaen J. Troia

IPC分类号： F02K7/02 ,  F02K7/16

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。

公开(公告)号：US20110138814A1

公开(公告)日：2011-06-16

申请号：US12636579

申请日：2009-12-11

申请人： George D. Rupp ,  Trajaen J. Troia

发明人： George D. Rupp ,  Trajaen J. Troia

IPC分类号： F02C1/00 ,  F02C9/00

CPC分类号： F02C7/04 ,  F02C9/18 ,  F02K3/075 ,  F02K3/077 ,  Y02T50/672

摘要： The present invention relates to a system and method of LO airflow modulation for use with a DTSA engine. A DTSA engine is positioned within an aircraft fuselage and the second DTSA turbine fan includes it own dedicated decoupled air inlet duct that is formed co-centrically about the housing. An airflow modulator member is positioned in duct to form the duct wall when the modulator is in a closed position. The Modulator member is pivotally connected to the duct wall, and is movable by an actuator to a second open position that allows airflow to escape the third stream duct, and provide airflow to both the DTSA fan blades as well as engine bay for cooling. The method of the present invention provides airflow modulation to an aircraft employing a DTSA engine, said method including the receiving of airflow from a supersonic aircraft intake; sensing a number of parameters, including, but not limited to aircraft speed, temperature, engine load and/or altitude. Calculating an efficient amount of airflow to provide to the DTSA turbine blades thorough a decoupled airstream; and directing movement of a modulator vane located in the intake duct to vary airflow to the DTSA turbine.

摘要翻译： 本发明涉及一种与DTSA发动机一起使用的LO气流调节系统和方法。 DTSA发动机位于飞行器机身内，第二DTSA涡轮风扇包括它自己的专用去耦空气入口导管，该导管与壳体共同形成。 当调节器处于关闭位置时，气流调节器构件定位在管道中以形成管道壁。 调节器构件枢转地连接到管道壁，并且可由致动器移动到第二打开位置，其允许气流从第三流管道逸出，并且向DTSA风扇叶片以及用于冷却的发动机舱提供气流。 本发明的方法为使用DTSA发动机的飞机提供气流调节，所述方法包括从超音速飞机入口接收气流; 感测多个参数，包括但不限于飞机速度，温度，发动机负载和/或高度。 计算通过解耦气流向DTSA涡轮机叶片提供有效的气流量; 并且引导位于进气管道中的调节器叶片的运动来改变到DTSA涡轮机的气流。

公开(公告)号：US09353684B2

公开(公告)日：2016-05-31

申请号：US12636579

申请日：2009-12-11

申请人： George D. Rupp ,  Trajaen J. Troia

发明人： George D. Rupp ,  Trajaen J. Troia

IPC分类号： F02C7/04 ,  F02C9/18 ,  F02K3/075 ,  F02K3/077

CPC分类号： F02C7/04 ,  F02C9/18 ,  F02K3/075 ,  F02K3/077 ,  Y02T50/672

摘要： The present invention relates to a system and method of LO airflow modulation for use with a DTSA engine. A DTSA engine is positioned within an aircraft fuselage and the second DTSA turbine fan includes it own dedicated decoupled air inlet duct that is formed co-centrically about the housing. An airflow modulator member is positioned in duct to form the duct wall when the modulator is in a closed position. The Modulator member is pivotally connected to the duct wall, and is movable by an actuator to a second open position that allows airflow to escape the third stream duct, and provide airflow to both the DTSA fan blades as well as engine bay for cooling. The method of the present invention provides airflow modulation to an aircraft employing a DTSA engine, said method including the receiving of airflow from a supersonic aircraft intake; sensing a number of parameters, including, but not limited to aircraft speed, temperature, engine load and/or altitude. Calculating an efficient amount of airflow to provide to the DTSA turbine blades thorough a decoupled airstream; and directing movement of a modulator vane located in the intake duct to vary airflow to the DTSA turbine.

摘要翻译： 本发明涉及一种与DTSA发动机一起使用的LO气流调节系统和方法。 DTSA发动机位于飞行器机身内，第二DTSA涡轮风扇包括它自己的专用去耦空气入口导管，该导管与壳体共同形成。 当调节器处于关闭位置时，气流调节器构件定位在管道中以形成管道壁。 调节器构件枢转地连接到管道壁，并且可由致动器移动到第二打开位置，其允许气流从第三流管道逸出，并且向DTSA风扇叶片以及用于冷却的发动机舱提供气流。 本发明的方法为使用DTSA发动机的飞机提供气流调节，所述方法包括从超音速飞机入口接收气流; 感测多个参数，包括但不限于飞机速度，温度，发动机负载和/或高度。 计算通过解耦气流向DTSA涡轮机叶片提供有效的气流量; 并且引导位于进气管道中的调节器叶片的运动来改变到DTSA涡轮机的气流。