-
1.发明公开Pulse detonation/deflagration apparatus and method for enhancing the production of detonation to deflagration waves 有权脉动引爆Verpuffungssystem和程序，以方便生产爆炸爆燃波
公开(公告)号：EP2157306A3
公开(公告)日：2017-01-18
申请号：EP09168405.0
申请日：2009-08-21
发明人： Boespflug, Matthew Patrick , Steenburgh, Dennis , Saddoughi, Seyed Gholami , Bennett, Grover Andrew
CPC分类号： F02C5/02 , F02K1/002 , F02K1/28 , F02K7/075 , F05D2240/40 , F05D2250/311 , F05D2260/16 , F05D2270/18 , F23R7/00 , Y02T50/671
摘要： Pulse detonation/deflagration apparatus (30, 30') for providing enhanced pressure wave operating frequency and/or magnitude, and methods of increasing the frequency or the magnitude of deflagration to detonation waves (37), are provided. A pulse detonation/deflagration apparatus (30, 30') can include a main/outer pulse detonation/deflgration actuator/engine (31) with multiple smaller internal combustion chambers or tubes (33) positioned inside the cavity of the main/outer actuator/engine (31) with each performing the function of individual pulse detonation/deflagration actuator/engines (31), The output pressure waves (37) created by the internal combustion chambers or tubes (33) can be utilized for propulsion or for controlling large scale flows, where needed.
摘要翻译： 提供脉冲爆震/用于提供增强的压力波的工作频率和/或幅度爆燃装置（30，30“），和增加的频率或爆燃到爆轰波（37）的大小的方法。 脉冲爆震/爆燃装置（30，30“）可包括主/外脉冲爆震/ deflgration致动器/主/外致动器的腔体内部定位的多个较小内部燃烧腔或燃烧管（33）的发动机（31）/ 发动机（31）与每个执行个别脉冲爆震/爆燃致动器/发动机（31）（37）由内部燃烧腔或燃烧管（33）创建的函数的输出压力波可以用于推进或用于控制大规模 流动时，在需要的地方。
-
公开(公告)号：EP1375865A3
公开(公告)日：2005-08-17
申请号：EP03254021.3
申请日：2003-06-25
CPC分类号： F02K7/075 , F02C3/165 , Y02T50/671
摘要： An apparatus (100) for generating torque, the apparatus (100) comprising: a rotor hub (110) adapted for applying torque to a shaft; and a plurality of pulse detonation engines (120) adapted for impulsively detonating a plurality of fuel/air mixtures to generate thrust forces and applying the thrust forces to the rotor hub (110) to generate the torque.
-
3.发明公开Aircraft, particularly small aircraft, having a propulsion system including a plurality of pulse detonation engines (PDEs) 有权Flugzeug mit einem Antriebssystem bestehend aus mehreren pulsierten Detonationskraftmaschinen
公开(公告)号：EP1557356A1
公开(公告)日：2005-07-27
申请号：EP04425043.9
申请日：2004-01-26
发明人： Perlo, Piero , Golub, Victor , Kotelnikov, Andrei
摘要： A small aircraft is disclosed having a propulsion system including a plurality of Pulse Detonation Engines (PDEs). The engines are arranged within the wings (2a) of the aircraft. The discharge nozzles (8) of the detonation tubes (7) of the detonation engines are provided at different areas of the aircraft and are differently oriented, so as to provide extra manoeuvrability along the three directions. The arrangement of the detonation tubes (7) within the wings (2a) reduces drag and hence the fuel consumption.
摘要翻译： 公开了一种具有包括多个脉冲爆震引擎（PDE）的推进系统的小型飞机。 发动机布置在飞机的机翼（2a）内。 爆震发动机的引爆管（7）的排放喷嘴（8）设置在飞行器的不同区域，并且具有不同的定向，以便沿着三个方向提供额外的机动性。 在翼（2a）内的引爆管（7）的布置减少了阻力并因此降低了燃料消耗。
-
公开(公告)号：EP1473457A2
公开(公告)日：2004-11-03
申请号：EP04252362.1
申请日：2004-04-22
发明人： Lupkes, Kirk R.
摘要： A pulse combustion device has a number of combustors (22A-22E) with upstream bodies (28) and downstream nozzles (30). Coupling conduits (122A...) provide communication between the combustors (22A-22E). For each given combustor this includes a first communication between a first location upstream of the nozzle (30) thereof and a first location along the nozzle of another. There is second communication between a second location upstream of the nozzle (30) and a second communication between a second location upstream of the nozzle of a second other combustor and a second nozzle location along the nozzle (30) of the given combustor.
摘要翻译： 脉冲燃烧装置具有多个具有上游体（28）和下游喷嘴（30）的燃烧器（22A-22E）。 联接管道（122A ...）提供燃烧器（22A-22E）之间的连通。 对于每个给定的燃烧器，其包括在其喷嘴（30）上游的第一位置和沿着另一个的喷嘴的第一位置之间的第一连通。 在喷嘴（30）上游的第二位置与第二另一个燃烧器的喷嘴上游的第二位置和沿着给定燃烧器的喷嘴（30）的第二喷嘴位置之间的第二连通处是第二连通。
-
公开(公告)号：EP1433946A1
公开(公告)日：2004-06-30
申请号：EP03258066.4
申请日：2003-12-19
摘要： A pulse detonation system (202) for a turbofan engine (200) including a fan assembly (212) and a turbine sub-system (230), which includes at least one turbine (232), 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 replacement assembly (242) comprising at least one detonation chamber configured to detonate a fuel mixture. The pulse detonation core replacement assembly is positioned between the fan assembly and the turbine sub-system.
摘要翻译： 包括风扇组件（212）和包括至少一个涡轮机（232）的涡轮机子系统（230））的涡轮风扇发动机（200）的脉冲爆震系统（202）被配置成产生温度升高和 涡轮风扇发动机内的压力上升，并为涡轮风扇发动机产生推力。 脉冲爆震系统包括脉冲爆震核心替换组件（242），其包括配置成引爆燃料混合物的至少一个爆震室。 脉冲爆震芯更换组件位于风扇组件和涡轮机子系统之间。
-
公开(公告)号：EP2157306B1
公开(公告)日：2018-07-18
申请号：EP09168405.0
申请日：2009-08-21
发明人： Boespflug, Matthew Patrick , Steenburgh, Dennis , Saddoughi, Seyed Gholami , Bennett, Grover Andrew
CPC分类号： F02C5/02 , F02K1/002 , F02K1/28 , F02K7/075 , F05D2240/40 , F05D2250/311 , F05D2260/16 , F05D2270/18 , F23R7/00 , Y02T50/671
摘要： Pulse detonation/deflagration apparatus (30, 30') for providing enhanced pressure wave operating frequency and/or magnitude, and methods of increasing the frequency or the magnitude of deflagration to detonation waves (37), are provided. A pulse detonation/deflagration apparatus (30, 30') can include a main/outer pulse detonation/deflgration actuator/engine (31) with multiple smaller internal combustion chambers or tubes (33) positioned inside the cavity of the main/outer actuator/engine (31) with each performing the function of individual pulse detonation/deflagration actuator/engines (31), The output pressure waves (37) created by the internal combustion chambers or tubes (33) can be utilized for propulsion or for controlling large scale flows, where needed.
-
公开(公告)号：EP2112351B1
公开(公告)日：2011-03-30
申请号：EP09290278.2
申请日：2009-04-16
申请人： MBDA France
CPC分类号： F02B71/06 , F02K7/02 , F02K7/06 , F02K7/075 , Y02T50/672
-
8.发明授权
公开(公告)号：EP1557356B1
公开(公告)日：2005-12-14
申请号：EP04425043.9
申请日：2004-01-26
发明人： Perlo, Piero , Golub, Victor , Kotelnikov, Andrei
-
公开(公告)号：EP1473457A3
公开(公告)日：2005-01-05
申请号：EP04252362.1
申请日：2004-04-22
发明人： Lupkes, Kirk R.
摘要： A pulse combustion device has a number of combustors (22A-22E) with upstream bodies (28) and downstream nozzles (30). Coupling conduits (122A...) provide communication between the combustors (22A-22E). For each given combustor this includes a first communication between a first location upstream of the nozzle (30) thereof and a first location along the nozzle of another. There is second communication between a second location upstream of the nozzle (30) and a second communication between a second location upstream of the nozzle of a second other combustor and a second nozzle location along the nozzle (30) of the given combustor.
-
10.发明公开Methods and apparatus for generating gas turbine engine thrust 有权Apparat um Gasturbinenschub zu erzeugen
公开(公告)号：EP1431563A1
公开(公告)日：2004-06-23
申请号：EP03257930.2
申请日：2003-12-16
摘要： A pulse detonation system (12) for a gas turbine engine (10) includes a core engine (30). The pulse detonation system is downstream from the core engine and is configured to create a temperature rise and a pressure rise within the gas turbine engine and to increase engine thrust. The pulse detonation system comprises a multi-staged pulse detonation augmentor (60) that comprises a predetonator (48) operable with at least a first operating stage wherein a less-than-stoichiometric fuel-air mixture is provided to the predetonator.
摘要翻译： 用于燃气涡轮发动机（10）的脉冲爆震系统（12）包括核心发动机（30）。 脉冲爆震系统在核心发动机的下游，并被配置成在燃气涡轮发动机内产生升温和升压并增加发动机推力。 脉冲爆炸系统包括多级脉冲爆炸增强器（60），其包括可在至少第一操作阶段操作的预调节器（48），其中向预灭火器提供小于化学计量的燃料 - 空气混合物。
-
-
-
-
-
-
-
-
-
搜索结果
34 条记录 (耗时 0.009 秒)
