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21. 发明授权

US07818956B2 Pulse detonation assembly and hybrid engine 有权
标题翻译：脉冲爆震装置和混合动力发动机
公开(公告)号：US07818956B2
公开(公告)日：2010-10-26
申请号：US11129686
申请日：2005-05-13
申请人： Adam Rasheed , Anthony John Dean , Christian Lee Vandervort
发明人： Adam Rasheed , Anthony John Dean , Christian Lee Vandervort
IPC分类号： F02C5/00 , F02C5/02 , F02K5/02
CPC分类号： F02K7/06 , F02C5/00 , F02K7/075 , F23C15/00 , F23R7/00 , Y02T50/67 , Y02T50/672
摘要： A pulse detonation (PD) assembly includes a number of PD chambers adapted to expel respective detonation product streams and a number of barriers disposed between respective pairs of PD chambers. The barriers define, at least in part, a number of sectors that contain at least one PD chamber. A hybrid engine includes a number of PD chambers and barriers. The hybrid engine further includes a turbine assembly having at least one turbine stage, being in flow communication with the PD chambers and being configured to be at least partially driven by the detonation product streams. A segmented hybrid engine includes a number of PD chambers and segments configured to receive and direct the detonation product streams from respective PD chambers. The segmented hybrid engine further includes a turbine assembly configured to be at least partially driven by the detonation product streams.
摘要翻译：脉冲爆震（PD）组件包括适于排出各个爆震产物流的多个PD室和设置在各对PD室之间的多个障碍物。这些障碍至少部分地限定了包含至少一个PD室的多个扇区。混合动力发动机包括多个PD室和障碍物。混合动力发动机还包括具有至少一个涡轮级的涡轮组件，其与PD室流体连通并被构造成至少部分地被爆轰产物流驱动。分段混合动力发动机包括多个PD室和构造成接收和引导来自相应PD室的爆轰产物流的段。分段式混合动力发动机还包括构造成至少部分地被引爆产物流驱动的涡轮组件。

22. 发明授权

US07634904B2 Methods and apparatus to facilitate generating power from a turbine engine 有权
标题翻译：用于从涡轮发动机产生动力的方法和装置
公开(公告)号：US07634904B2
公开(公告)日：2009-12-22
申请号：US11328394
申请日：2006-01-09
申请人： Adam Rasheed , Anthony John Dean , Venkat Eswarlu Tangirala , Pierre Francois Pinard , Christian Lee Vandervort
发明人： Adam Rasheed , Anthony John Dean , Venkat Eswarlu Tangirala , Pierre Francois Pinard , Christian Lee Vandervort
IPC分类号： F02K5/02
CPC分类号： F23R7/00
摘要： A turbine disk assembly including a rotatable cylindrical member rotatably coupled to a shaft and a plurality of turbine blades extend circumferentially outward from said cylindrical member. The turbine blades include at least two different geometrical shapes, a first of the geometrical shapes is configured to facilitate extracting power from a first pulsed detonation combustor product stream. A second of said geometrical shapes is configured to facilitate extracting power from a second pulsed detonation combustor product stream that is different from the first pulsed detonation combustor product stream.
摘要翻译：包括可旋转地联接到轴的可旋转圆柱形构件和多个涡轮机叶片的涡轮盘组件从所述圆柱形构件周向向外延伸。涡轮机叶片包括至少两个不同的几何形状，第一几何形状被配置为便于从第一脉冲爆炸燃烧器产物流提取动力。所述几何形状中的第二个被配置为便于从与第一脉冲爆炸燃烧器产物流不同的第二脉冲爆炸燃烧器产物流提取功率。

23. 发明授权

US07581383B2 Acoustic pulsejet helmet 有权
标题翻译：声脉冲头盔
公开(公告)号：US07581383B2
公开(公告)日：2009-09-01
申请号：US11190263
申请日：2005-07-27
申请人： Richard P Ouellette
发明人： Richard P Ouellette
IPC分类号： F02K5/02
CPC分类号： F02K7/075 , F02K7/02
摘要： A pulsejet is provided that includes an inlet, an exhaust nozzle, and a combustion chamber between the inlet and the exhaust nozzle. The pulsejet additionally includes a flow-turning device positioned over an end of the inlet. The flow turning device forms an air flow pathway (AFP) having a substantially 180° turn. The 180° turn aligns a direction of exhaust exiting the combustion chamber through the inlet along a positive axial thrust line and substantially parallel with exhaust exiting the combustion chamber through the nozzle.
摘要翻译：提供脉冲喷射器，其包括入口，排气喷嘴和入口和排气喷嘴之间的燃烧室。脉冲喷射还包括位于入口端部的流动转向装置。流动转向装置形成具有大致180°回转的空气流通路径（AFP）。 180°转角沿着正的轴向推力线，通过入口排出离开燃烧室的排气的方向，并且基本上平行于通过喷嘴离开燃烧室的排气。

24. 发明申请

US20090126343A1 Internal Detonation Reciprocating Engine 审中-公开
标题翻译：内爆式往复式发动机
公开(公告)号：US20090126343A1
公开(公告)日：2009-05-21
申请号：US11941741
申请日：2007-11-16
申请人： Frank K. Lu , Philip K. Panicker , Donald R. Wilson , Wei-Hsiang Lai , Jiun-Ming Li
发明人： Frank K. Lu , Philip K. Panicker , Donald R. Wilson , Wei-Hsiang Lai , Jiun-Ming Li
IPC分类号： F02K5/02
CPC分类号： F02B23/08 , Y02T10/125
摘要： A method of rotating a crank shaft and in internal detonation engine are provided. The internal detonation engine comprises a deflagration to detonation transition section. The deflagration to detonation transition section is connected to a main cylinder, which houses a piston. Inducing a detonation wave from the deflagration wave and passing the detonation wave through a fluid, gives rise to high pressure and temperature in a cylinder and pushes a piston towards bottom dead center. An internal detonation reciprocating engine may be a single cylinder and may be either a two or four stroke engine. A two-stroke internal detonation reciprocating engine is similar to a four-stroke internal detonation reciprocating engine but has different valve placements. Detonations produce a more thorough combustion of the fuel and may, thereby, yield reduced emissions of carbon monoxide as compared to internal combustion engines.
摘要翻译：提供了一种旋转曲柄轴和内部爆震引擎的方法。内爆式发动机包括爆燃过渡段。爆燃过渡段的爆燃与主缸相连，主缸装有活塞。从爆燃波引起爆震波并将爆震波通过流体，引起气缸中的高压和温度，并将活塞推向下死点。内部爆震往复发动机可以是单缸，并且可以是二冲程发动机或四冲程发动机。二冲程内爆炸往复式发动机类似于四冲程内爆炸往复式发动机，但具有不同的阀门布置。爆炸产生燃料的更彻底的燃烧，从而与内燃机相比可减少一氧化碳的排放。

25. 发明申请

US20050279077A1 Off-axis pulse detonation configuration for gas turbine engine 有权
标题翻译：燃气涡轮发动机的离轴脉冲爆震配置
公开(公告)号：US20050279077A1
公开(公告)日：2005-12-22
申请号：US10870876
申请日：2004-06-18
申请人： Edward Hall , Adam Rasheed , Anthony Dean
发明人： Edward Hall , Adam Rasheed , Anthony Dean
IPC分类号： F02C5/00 , F02C5/02 , F02K5/02 , F02K7/02 , F02K9/78
CPC分类号： F02C5/00 , F02K7/02 , F02K9/78
摘要： The present invention is a gas turbine engine system containing a compressor stage, a pulse detonation stage, and a turbine stage. During operation of the engine system, compressed flow from the compressor stage is directed to at least one off-axis pulse detonation tube in the pulse detonation stage. The off-axis pulse detonation tube detonates a mixture containing the compressed flow and a fuel to create a detonation wave, which is routed to an inlet portion of a reverse flow turbine. The exhaust flow from the reverse flow turbine is then directed away from the engine through ducting.
摘要翻译：本发明是一种包含压缩机级，脉冲爆震级和涡轮级的燃气轮机发动机系统。在发动机系统运行期间，来自压缩机级的压缩流被引导到脉冲爆震级中的至少一个离轴脉冲爆管。离轴脉冲爆震管引爆包含压缩流和燃料的混合物以产生爆震波，该爆震波被引导到逆流涡轮机的入口部分。然后，来自逆流涡轮机的废气流通过管道被引导离开发动机。

26. 发明授权

US3748854A Lift engine 失效
标题翻译：发动机
公开(公告)号：US3748854A
公开(公告)日：1973-07-31
申请号：US3748854D
申请日：1971-09-24
申请人： MOTOREN TURBINEN UNION
发明人： VEDOVA R
IPC分类号： B64C29/00 , F02K5/02 , F02K3/04
CPC分类号： B64C29/0016 , F02K5/02 , Y02T50/671
摘要： A lift engine assembly for aircraft capable of producing lift and/or thrust having a tip turbine operated lift fan with at least one gas turbine engine being arranged about the circumference of the lift fan.
摘要翻译：一种用于能够产生提升和/或推力的飞机的升降机发动机组件，其具有尖端涡轮机操作的升降风扇，其中至少一个燃气涡轮发动机围绕提升风扇的圆周布置。

27. 发明授权

US3212733A Cruise fan coupling system 失效
标题翻译：巡航风扇联轴器系统
公开(公告)号：US3212733A
公开(公告)日：1965-10-19
申请号：US38629464
申请日：1964-07-30
申请人： GEN ELECTRIC
发明人： KUTNEY JOHN T
IPC分类号： B64C11/00 , B64C29/00 , F02K5/02 , F04D25/04
CPC分类号： F04D25/045 , B64C11/001 , B64C29/0033 , F02K5/02

28. 发明授权

US3188805A Internal combustion engine 失效
公开(公告)号：US3188805A
公开(公告)日：1965-06-15
申请号：US25839363
申请日：1963-02-14
申请人： GAHAGAN CHARLES L
发明人： GAHAGAN CHARLES L
IPC分类号： F02B71/06 , F02K5/02
CPC分类号： F02B71/06 , F02K5/023 , Y02T50/671

29. 发明授权

US3112613A Positive power jet engine 失效
标题翻译：正功率喷气发动机
公开(公告)号：US3112613A
公开(公告)日：1963-12-03
申请号：US1671860
申请日：1960-03-22
申请人： NELSON DANIEL E
发明人： NELSON DANIEL E
IPC分类号： F02K5/02
CPC分类号： F02K5/023

30. 发明授权

US2925072A Power plant with one cylinder and airborne piston 失效
标题翻译：具有一个气缸和机载活塞的发电厂
公开(公告)号：US2925072A
公开(公告)日：1960-02-16
申请号：US39937153
申请日：1953-12-21
申请人： PAUL SCHMIDT
发明人： PAUL SCHMIDT
IPC分类号： F02K5/02
CPC分类号： F02K5/026 , Y02T50/671

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