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1. 发明授权

US5129227A Low speed engine for supersonic and hypersonic vehicles 失效
标题翻译：用于超级和超级车辆的低速发动机
公开(公告)号：US5129227A
公开(公告)日：1992-07-14
申请号：US683350
申请日：1991-04-10
申请人： Garry W. Klees , Mark L. Sloan , Russel L. Thornock
发明人： Garry W. Klees , Mark L. Sloan , Russel L. Thornock
IPC分类号： F02K7/12
CPC分类号： F02K7/12 , Y02T50/671
摘要： A jet engine for use in a hypersonic aircraft. A fuel rich injectant is injected into the mixing zone of a duct at a substantial downstream angle to form an ejector. The temperature of the injectant is sufficiently low that spontaneous combustion of the injectant is delayed until the injectant reaches the combustion zone of the duct. In order to prevent combustion from propagating upstream from the combustion zone, the equivalence ratio of the mixture of injectant and ambient air flowing along the wall of the duct is maintained at a relatively high value, and the velocity profile of the flow along the wall of the duct is maintained at a relatively high value.

2. 发明授权

US4592508A Translating jet engine nozzle plug 失效
标题翻译：翻译喷气发动机喷嘴塞
公开(公告)号：US4592508A
公开(公告)日：1986-06-03
申请号：US563419
申请日：1983-10-27
申请人： Russel L. Thornock
发明人： Russel L. Thornock
IPC分类号： F02K1/08 , F02K1/72 , F02K1/50
CPC分类号： F02K1/08 , F02K1/72 , F05D2250/34
摘要： A plug (24) has a fixed portion (26, 28) and a sliding portion (34). A tapered outer surface of portion (34) is adjacent to the throat (22) of a jet engine nozzle (20). Portion (34) includes two expansible chambers (36, 38) which are both defined by wall portions of both the fixed and the sliding portions of plug (24). Chambers (36, 38) are separated by a bulkhead (48) carried by said fixed portion. Chambers (36, 38) are supplied with fluid pressure which acts against a pressure surface (40, 42) to move sliding portion (34) axially forwardly and aftwardly, respectively, to in turn vary the throat area. Bleed air from the engine compressor supplies the fluid pressure. Fluid pressure is continuously supplied to chamber (38). Controlled leakage out of chamber (36) provides gradual slowing of movement of portion (34) in either direction. Control apparatus is located remotely from the nozzle (20).
摘要翻译：插头（24）具有固定部分（26,28）和滑动部分（34）。部分（34）的锥形外表面与喷气发动机喷嘴（20）的喉部（22）相邻。部分（34）包括由插头（24）的固定和滑动部分的壁部分限定的两个可膨胀室（36,38）。室（36,38）由所述固定部分承载的舱壁（48）分开。腔室（36,38）被提供有流体压力，该压力作用在压力表面（40,42）上，以分别轴向地向前和向后移动滑动部分（34），从而改变喉部区域。发动机压缩机排出的空气提供流体压力。流体压力连续地供应到腔室（38）。从腔室（36）中控制的泄漏使得部分（34）在任一方向上的运动逐渐减慢。控制装置远离喷嘴（20）定位。

3. 发明授权

US07690190B2 Aircraft systems including cascade thrust reversers 有权
标题翻译：飞机系统包括级联推力反向器
公开(公告)号：US07690190B2
公开(公告)日：2010-04-06
申请号：US11127424
申请日：2005-05-11
申请人： Russel L. Thornock , Michael L. Sangwin , Entsung Hsiao
发明人： Russel L. Thornock , Michael L. Sangwin , Entsung Hsiao
IPC分类号： F02K3/02
CPC分类号： F02K1/64 , F02K1/72 , Y02T50/671
摘要： Aircraft systems including cascade thrust reversers are disclosed herein. An aircraft system in accordance with one embodiment includes a cascade thrust reverser having a fixed reverser ramp and a nozzle outer wall section at least partially aft of the fixed reverser ramp. The nozzle outer wall section is movable between a deployed position and a stowed position. The nozzle outer wall section includes a forward portion with a leading edge section. The fixed reverser ramp has a portion forward of and adjacent to the nozzle outer wall section when the nozzle outer wall section is in the stowed position. The portion of the fixed reverser ramp has a first slope. The forward portion of the nozzle outer wall section that is aft of the leading edge section has a second slope different than the first slope.
摘要翻译：本文公开了包括级联推力反向器的飞行器系统。根据一个实施例的飞行器系统包括级联推力反向器，其具有固定的反向斜面和至少部分地固定的反向斜面后部的喷嘴外壁部分。喷嘴外壁部分可在展开位置和收起位置之间移动。喷嘴外壁部分包括具有前缘部分的前部。当喷嘴外壁部分处于收起位置时，固定反向斜面具有在喷嘴外壁部分的前方和后方的部分。固定反向斜坡的部分具有第一斜坡。在前缘部的后方的喷嘴外壁部的前方部具有与第一斜面不同的第二斜率。

4. 发明授权

US5887822A Segmented engine flow control device 失效
标题翻译：分段发动机流量控制装置
公开(公告)号：US5887822A
公开(公告)日：1999-03-30
申请号：US827523
申请日：1997-03-28
申请人： Russel L. Thornock , Russell S. Brinton , Joel E. Hansen , Leonard J. Hebert , Michael R. Holle , Jeffrey P. Kane , John G. Kladouris , Michael B. Scholey
发明人： Russel L. Thornock , Russell S. Brinton , Joel E. Hansen , Leonard J. Hebert , Michael R. Holle , Jeffrey P. Kane , John G. Kladouris , Michael B. Scholey
IPC分类号： B64D33/04 , F02K1/52 , B64D27/00
CPC分类号： B64D33/04 , B64D29/02 , F02K1/52
摘要： In a turbofan jet engine installation including a low pressure area (48) located between a primary exhaust nozzle (20) and strut fairings (30), an improvement including a fencing assembly (66) for reducing interaction of fan air (52) with air in the low pressure area. The fencing assembly (66) includes two pairs (70), (72) of opposed flow control fences (68) connected to the primary exhaust nozzle (20) at locations laterally outboard of the strut fairings (30). A first pair (70) includes fences formed of a single piece connected directly to the primary nozzle (20). A second pair (72) includes fences formed of a number of longitudinally spaced-apart segments (82). The segments (82) are connected to one face of an elongated attachment strap (84) with the opposite strap face being connected to the nozzle. Each fence includes a foot portion (78) and an upright portion (80) extending outwardly from the foot portion.
摘要翻译：在包括位于主排气喷嘴（20）和支柱整流罩（30）之间的低压区域（48）的涡轮风扇喷气发动机装置中，改进包括用于减少风扇空气（52）与空气的相互作用的围栏组件（66）在低压区域。围栏组件（66）包括在支柱整流罩（30）的横向外侧的位置处连接到主排气喷嘴（20）的两对（70），（72）的相对的流动控制栅栏（68）。第一对（70）包括由直接连接到主喷嘴（20）的单件形成的围栏。第二对（72）包括由多个纵向间隔开的段（82）形成的围栏。段（82）连接到细长的附接带（84）的一个面，相对的带面连接到喷嘴。每个围栏包括从脚部向外延伸的脚部部分（78）和直立部分（80）。

5. 发明授权

US4254620A Jet engine multiduct noise suppressor 失效
标题翻译：喷气发动机多管噪声抑制器
公开(公告)号：US4254620A
公开(公告)日：1981-03-10
申请号：US881681
申请日：1978-02-27
申请人： Charles P. Wright , Russel L. Thornock
发明人： Charles P. Wright , Russel L. Thornock
IPC分类号： B64C9/38 , F02K1/40 , F02K1/48
CPC分类号： F02K1/48 , B64C9/38 , F02K1/40 , B64C2700/625
摘要： Each duct of a plurality of generally cylindrical exhaust ducts disposed in approximately uniform annular arrangement about an axis is a tube, or a lobe of a radially-branched passage, having a discharge end canted so that the radially outer portion of such duct end projects rearward farther than any other portion of the duct end. The canted duct ends direct the major portion of the exhaust of a jet engine inward toward the axis of the annular exhaust duct arrangement in a plurality of exhaust jets, effecting a rearwardly convergent relationship of the jets.
摘要翻译：围绕轴线以大致均匀的环形布置设置的多个大致圆柱形的排气管道的每个管道是具有排出端的管或径向分支通道的突出部，其倾斜使得该管道端部的径向外部部分向后突出比管道末端的任何其他部分更远。倾斜的管道端部将喷气发动机的排气的主要部分向内引导到多个排气喷射器中的环形排气管道装置的轴线，从而实现射流的向后收敛关系。

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