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1. 发明申请

US20130160426A1 ROCKET ENGINE INJECTOR ASSEMBLY WITH CRYOGENIC CAVITY INSULATION 审中-公开
标题翻译： ROCKET发动机注射器组件与低温空气绝缘
公开(公告)号：US20130160426A1
公开(公告)日：2013-06-27
申请号：US13336604
申请日：2011-12-23
申请人： Bradley C. Johnson , John A. Harris, III , Michael J. Gehron
发明人： Bradley C. Johnson , John A. Harris, III , Michael J. Gehron
IPC分类号： F02K9/52 , B23P15/00 , B05B15/00
CPC分类号： F02K9/52 , Y10T29/49346
摘要： An injector assembly for a rocket engine includes a thermal insulating layer adjacent to an oxidizer cavity.
摘要翻译：用于火箭发动机的喷射器组件包括与氧化器腔相邻的绝热层。

2. 发明授权

US08522560B2 Fuel-cooled heat exchanger with thermoelectric device compression 有权
标题翻译：具有热电装置压缩的燃料冷却热交换器
公开(公告)号：US08522560B2
公开(公告)日：2013-09-03
申请号：US12550150
申请日：2009-08-28
申请人： David C. Jarmon , Jun Shi , Steve Lozyniak , Bradley C. Johnson
发明人： David C. Jarmon , Jun Shi , Steve Lozyniak , Bradley C. Johnson
IPC分类号： F02K7/08
CPC分类号： F02K7/10 , B64C1/38 , B64C30/00 , F02C7/224 , F02K1/822 , F05D2220/80 , H01L35/30 , Y02T50/672 , Y02T50/675
摘要： An apparatus includes an inlet conduit assembly surrounding a gas flow path and a combustor arranged downstream of the inlet conduit assembly. The inlet conduit assembly includes a thermoelectric (TE) device configured to convert heat into electrical energy, a gas flow conduit arranged between the gas flow path and the TE device, and a resilient member configured to bias the TE device into contact with the gas flow conduit.
摘要翻译：一种装置包括围绕气体流路的入口导管组件和布置在入口导管组件下游的燃烧器。入口管道组件包括被配置为将热量转换成电能的热电（TE）装置，布置在气体流动路径和TE装置之间的气体流动导管以及被配置为将TE装置偏置成与气体流接触的弹性构件导管。

3. 发明授权

US5683034A Engine exhaust nozzle seal 失效
标题翻译：发动机排气喷嘴密封
公开(公告)号：US5683034A
公开(公告)日：1997-11-04
申请号：US446361
申请日：1995-05-22
申请人： Bradley C. Johnson , Curtis W. Berger , Steven B. Johnson , William J. Miller
发明人： Bradley C. Johnson , Curtis W. Berger , Steven B. Johnson , William J. Miller
IPC分类号： F02K1/12 , F02K1/80 , B64C15/02
CPC分类号： F02K1/805 , F05D2250/324
摘要： A divergent flap seal for a gas turbine engine exhaust nozzle having a longitudinal axis is provided, having a body, a spine member, and a flap position guide. The flap position guide separates adjacent divergent flaps regardless of the angle the flaps are skewed relative to the longitudinal axis of the nozzle, thereby more evenly distributing the flaps about the circumference of the nozzle.
摘要翻译：提供具有纵向轴线的燃气涡轮发动机排气喷嘴的发散翼片密封件，其具有主体，脊柱构件和挡板位置导向件。襟翼位置导向件分离相邻的发散襟翼，而不管襟翼相对于喷嘴的纵向轴线倾斜的角度如何，从而更均匀地将襟翼分布在喷嘴的圆周上。

4. 发明申请

US20100242486A1 FUEL-COOLED HEAT EXCHANGER WITH THERMOELECTRIC DEVICE COMPRESSION 有权
标题翻译：具有热电装置压缩的燃料冷却热交换器
公开(公告)号：US20100242486A1
公开(公告)日：2010-09-30
申请号：US12550150
申请日：2009-08-28
申请人： David C. Jarmon , Jun Shi , Steve Lozyniak , Bradley C. Johnson
发明人： David C. Jarmon , Jun Shi , Steve Lozyniak , Bradley C. Johnson
IPC分类号： F02K7/14 , F28D15/00 , H01L35/30
CPC分类号： F02K7/10 , B64C1/38 , B64C30/00 , F02C7/224 , F02K1/822 , F05D2220/80 , H01L35/30 , Y02T50/672 , Y02T50/675
摘要： An apparatus includes an inlet conduit assembly surrounding a gas flow path and a combustor arranged downstream of the inlet conduit assembly. The inlet conduit assembly includes a thermoelectric (TE) device configured to convert heat into electrical energy, a gas flow conduit arranged between the gas flow path and the TE device, and a resilient member configured to bias the TE device into contact with the gas flow conduit.
摘要翻译：一种装置包括围绕气体流路的入口导管组件和布置在入口导管组件下游的燃烧器。入口管道组件包括被配置为将热量转换成电能的热电（TE）装置，布置在气体流动路径和TE装置之间的气体流动导管以及被配置为将TE装置偏置成与气体流接触的弹性构件导管。

5. 发明申请

US20100034616A1 FASTENER ASSEMBLY FOR CONNECTING ROCKET ENGINE NOZZLES 有权
标题翻译：用于连接发动机喷嘴的紧固件总成
公开(公告)号：US20100034616A1
公开(公告)日：2010-02-11
申请号：US12189587
申请日：2008-08-11
申请人： Bradley C. Johnson
发明人： Bradley C. Johnson
IPC分类号： F16B35/00 , F02K9/00
CPC分类号： F16B5/0241 , F02K9/62 , F02K9/97 , F05B2260/301 , F05D2300/50212
摘要： A sliding connection between components of dissimilar materials includes a first mating surface formed on a first component and a second mating surface formed on a second component and configured to mate with the first mating surface. The first component is connected to the second component at the first and the second mating surfaces by a fastener including a shank, a sleeve received by the shank, and a resilient member received by the shank and contained by the sleeve. The resilient member is configured to press the first mating surface and the second mating surface against one another and to permit the first mating surface to slide against the second mating surface.
摘要翻译：不同材料的部件之间的滑动连接包括形成在第一部件上的第一配合表面和形成在第二部件上并被配置为与第一配合表面配合的第二配合表面。所述第一部件通过紧固件连接到所述第二部件，所述紧固件包括柄部，所述柄部容纳的套筒以及由所述柄部容纳并被所述套筒容纳的弹性部件。弹性构件构造成将第一配合表面和第二配合表面相互挤压并且允许第一配合表面抵靠第二配合表面滑动。

6. 发明授权

US5893518A Attachment means for flaps of variable exhaust nozzle 失效
标题翻译：可变排气喷嘴襟翼的安装装置
公开(公告)号：US5893518A
公开(公告)日：1999-04-13
申请号：US565599
申请日：1995-11-30
申请人： Raymond J. Bruchez, Jr. , M. Craig Lady , Gonzalo F. Martinez , Bradley C. Johnson
发明人： Raymond J. Bruchez, Jr. , M. Craig Lady , Gonzalo F. Martinez , Bradley C. Johnson
IPC分类号： F02K1/12 , B05B12/00
CPC分类号： F02K1/12 , Y02T50/672
摘要： The external flaps of a variable exhaust nozzle for a gas turbine engine are attached to the nozzle by a pair of pivotal rods attached to the nozzle's internal support structure and slidably fits into elongated spaced bushings extending along the longitudinal axis of the flaps formed in bosses extending orthogonally from the inner surface of the flaps. The attachment to the support structure includes a unison ball made from composite material that fits into a spherical track formed in a recess in the end of the rods. The method of installation is to insert one of the post into the first bushing that is offset from the second bushing. After the slight engagement of the first post, the second post is pivoted to align with its complementary bushing and the flap is positioned forward to fully engage the rods into the bushings. The aft end hinge of the flap is then attached, A limit pin that is attached to the post travels in a slot designed to limit the travel of the post. Another embodiment includes a damping function in the attachment.
摘要翻译：用于燃气涡轮发动机的可变排气喷嘴的外部翼片通过附接到喷嘴的内部支撑结构的一对枢转杆附接到喷嘴，并且可滑动地配合到沿着形成在凸起部分中的凸起的纵向轴线延伸的细长间隔的衬套中从襟翼的内表面正交。与支撑结构的连接包括由复合材料制成的协调球，其配合到形成在杆的端部中的凹部中的球形轨道。安装方法是将柱中的一个插入到与第二衬套偏移的第一衬套中。在第一柱的轻微接合之后，第二柱枢转以与其互补衬套对准，并且挡板向前定位以将杆完全接合到衬套中。然后安装翼片的后端铰链，附接到柱的限位销在设计成限制柱的行进的狭槽中行进。另一个实施例包括附件中的阻尼功能。

7. 发明授权

US08904752B2 Injector assembly for a rocket engine 有权
标题翻译：用于火箭发动机的喷射器组件
公开(公告)号：US08904752B2
公开(公告)日：2014-12-09
申请号：US13028779
申请日：2011-02-16
申请人： Bradley C. Johnson , Randolph T. Lyda , Ryan W. Brandt , Mark J. Ricciardo
发明人： Bradley C. Johnson , Randolph T. Lyda , Ryan W. Brandt , Mark J. Ricciardo
IPC分类号： F02K9/52 , B05B7/10
CPC分类号： F02K9/52 , B05B7/10 , F02K9/58
摘要： A cap for a liquid propellant injection assembly of a rocket engine includes a cap body and a valve assembly. The cap body extends between first and second ends. The cap body has a bore that fluidly connects one or more inlets to an outlet. The inlets are disposed in a tubular sidewall of the cap body. The outlet is disposed in the second end of the cap body. The valve assembly includes a valve cap disposed around the first end of the cap body. The valve assembly is adapted to selectively regulate flow of a propellant through the inlets in the cap body as a function of pressure exerted by the propellant against the valve assembly.
摘要翻译：用于火箭发动机的液体推进剂喷射组件的盖包括盖体和阀组件。帽体在第一和第二端之间延伸。盖体具有将一个或多个入口流体连接到出口的孔。入口设置在帽体的管状侧壁中。出口设置在帽体的第二端。阀组件包括围绕盖主体的第一端设置的阀盖。阀组件适于根据推进剂对阀组件施加的压力来选择性地调节推进剂通过盖体内的入口的流动。

8. 发明授权

US08281603B2 Fastener assembly for connecting rocket engine nozzles 有权
标题翻译：用于连接火箭发动机喷嘴的紧固件组件
公开(公告)号：US08281603B2
公开(公告)日：2012-10-09
申请号：US12189587
申请日：2008-08-11
申请人： Bradley C. Johnson
发明人： Bradley C. Johnson
IPC分类号： F02C7/20 , F02K1/00
CPC分类号： F16B5/0241 , F02K9/62 , F02K9/97 , F05B2260/301 , F05D2300/50212
摘要： A sliding connection between components of dissimilar materials includes a first mating surface formed on a first component and a second mating surface formed on a second component and configured to mate with the first mating surface. The first component is connected to the second component at the first and the second mating surfaces by a fastener including a shank, a sleeve received by the shank, and a resilient member received by the shank and contained by the sleeve. The resilient member is configured to press the first mating surface and the second mating surface against one another and to permit the first mating surface to slide against the second mating surface.
摘要翻译：不同材料的部件之间的滑动连接包括形成在第一部件上的第一配合表面和形成在第二部件上并被配置为与第一配合表面配合的第二配合表面。所述第一部件通过紧固件连接到所述第二部件，所述紧固件包括柄部，所述柄部容纳的套筒以及由所述柄部容纳并被所述套筒容纳的弹性部件。弹性构件构造成将第一配合表面和第二配合表面相互挤压并且允许第一配合表面抵靠第二配合表面滑动。

9. 发明申请

US20110219743A1 INJECTOR ASSEMBLY FOR A ROCKET ENGINE 有权
标题翻译：喷油器总成用于发动机
公开(公告)号：US20110219743A1
公开(公告)日：2011-09-15
申请号：US13028779
申请日：2011-02-16
申请人： Bradley C. Johnson , Randolph T. Lyda , Ryan W. Brandt , Mark J. Ricciardo
发明人： Bradley C. Johnson , Randolph T. Lyda , Ryan W. Brandt , Mark J. Ricciardo
IPC分类号： F02K9/52 , F02M61/00 , B05B15/00
CPC分类号： F02K9/52 , B05B7/10 , F02K9/58
摘要： A cap for a liquid propellant injection assembly of a rocket engine includes a cap body and a valve assembly. The cap body extends between first and second ends. The cap body has a bore that fluidly connects one or more inlets to an outlet. The inlets are disposed in a tubular sidewall of the cap body. The outlet is disposed in the second end of the cap body. The valve assembly includes a valve cap disposed around the first end of the cap body. The valve assembly is adapted to selectively regulate flow of a propellant through the inlets in the cap body as a function of pressure exerted by the propellant against the valve assembly.
摘要翻译：用于火箭发动机的液体推进剂喷射组件的盖包括盖体和阀组件。帽体在第一和第二端之间延伸。盖体具有将一个或多个入口流体连接到出口的孔。入口设置在帽体的管状侧壁中。出口设置在帽体的第二端。阀组件包括围绕盖主体的第一端设置的阀盖。阀组件适于根据推进剂对阀组件施加的压力来选择性地调节推进剂通过盖体内的入口的流动。

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