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1. 发明授权

US06666018B2 Combined cycle pulse detonation turbine engine 有权
标题翻译：联合循环脉冲爆震涡轮发动机
公开(公告)号：US06666018B2
公开(公告)日：2003-12-23
申请号：US10328679
申请日：2002-12-23
申请人： Lawrence Butler , James Edward Johnson , Lawrence Wayne Dunbar
发明人： Lawrence Butler , James Edward Johnson , Lawrence Wayne Dunbar
IPC分类号： F02K306
CPC分类号： F02K3/075 , F02K7/02 , F02K7/06 , F02K7/075
摘要： A pulse detonation system for a turbofan engine including a fan assembly and a turbine sub-system, which includes at least one turbine, is configured to create a temperature rise and a pressure rise within the turbofan engine and to generate thrust for the turbofan engine. The pulse detonation system includes a pulse detonation core assembly comprising at least one detonation chamber configured to detonate a fuel mixture. The pulse detonation core assembly is positioned between the fan assembly and the turbine sub-system.
摘要翻译：包括风扇组件和包括至少一个涡轮机的涡轮机子系统的涡轮风扇发动机的脉冲爆震系统构造成在涡轮风扇发动机内产生温度升高和压力上升，并产生用于涡轮风扇发动机的推力。脉冲爆震系统包括脉冲爆震核心组件，其包括至少一个被配置为引爆燃料混合物的爆震室。脉冲爆震芯组件位于风扇组件和涡轮机子系统之间。

2. 发明授权

US5680754A Compressor splitter for use with a forward variable area bypass injector 失效
标题翻译：用于前进可变区域旁路喷油器的压缩机分配器
公开(公告)号：US5680754A
公开(公告)日：1997-10-28
申请号：US478304
申请日：1990-02-12
申请人： Rollin George Giffin , John Joseph Ciokajlo , Lawrence Wayne Dunbar
发明人： Rollin George Giffin , John Joseph Ciokajlo , Lawrence Wayne Dunbar
IPC分类号： F02K3/02 , F02K3/06 , F02K3/075
CPC分类号： F02K3/075 , F02K3/02 , F02K3/06 , F04D27/0215 , F04D27/023 , F04D29/542
摘要： The present invention is a unique splitter of a core engine compressor in a double bypass, variable cycle engine. The splitter is extended forward to a second fan section. The extended splitter may divide the rotor blades into outer and inner portions to allow the flow past these portions to act essentially aerodynamically independent of each other in a single or double bypass mode of operation of the variable cycle engine.
摘要翻译：本发明是双旁路，可变循环发动机中的核心发动机压缩机的独特分离器。分流器向前延伸到第二风扇部分。扩展的分离器可以将转子叶片分成外部和内部部分，以允许流过这些部分的流动基本上在动力学上以可变循环发动机的单次或双重旁路操作模式彼此独立地起作用。

3. 发明授权

US5683225A Jet engine variable area turbine nozzle 失效
标题翻译：喷气发动机变区涡轮喷嘴
公开(公告)号：US5683225A
公开(公告)日：1997-11-04
申请号：US783668
申请日：1991-10-28
申请人： Robert Joseph Orlando , Lawrence Wayne Dunbar
发明人： Robert Joseph Orlando , Lawrence Wayne Dunbar
IPC分类号： F01D17/14 , F01D17/12 , F03B3/14
CPC分类号： F01D17/14
摘要： A turbine nozzle for a gas turbine engine subassembly having an axial turbine. The turbine nozzle airfoil-shaped vanes are fixedly attached to one or both of the annular inner and outer casings. Apparatus is provided to vary the vane airflow passage area between the casings and between the pressure side of one vane and the suction side of an adjacent vane. The apparatus varies the area near at least the pressure side of the one vane. Various embodiments of the apparatus include: a small pivotable flap pivotally attached to the outer casing and positioned near the pressure side of the one vane; a small movable flap attached to the outer casing to be movable along the pressure side of the one vane, and a plug member insertable into and withdrawable from the vane airflow passage through the outer casing near at least the pressure side of the one vane.
摘要翻译：一种用于具有轴向涡轮机的燃气涡轮发动机子组件的涡轮喷嘴。涡轮喷嘴翼型叶片固定地附接到环形内壳和外壳中的一个或两个。提供设备以改变壳体之间和一个叶片的压力侧与相邻叶片的吸力侧之间的叶片气流通道面积。该装置改变至少一个叶片的压力侧附近的区域。该装置的各种实施例包括：可枢转地附接到外壳并且定位在一个叶片的压力侧附近的小的可枢转翼片; 附接到所述外壳的小活动翼可以沿着所述一个叶片的压力侧移动;以及插塞构件，其可插入并可从所述叶片气流通道通过所述外壳至少靠近所述一个叶片的所述压力侧。

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