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1. 发明授权

US5906097A Engine flow control device 失效
标题翻译：发动机流量控制装置
公开(公告)号：US5906097A
公开(公告)日：1999-05-25
申请号：US825827
申请日：1997-03-29
申请人： Leonard J. Hebert , Jerry Piro , Michael W. Su , Ronald L. Balzer , Michael L. Sangwin , Jeff P. Lewis , Robert E. Moody
发明人： Leonard J. Hebert , Jerry Piro , Michael W. Su , Ronald L. Balzer , Michael L. Sangwin , Jeff P. Lewis , Robert E. Moody
IPC分类号： B64C23/00 , B64D33/04 , F02C7/20 , F02K3/02
CPC分类号： B64C23/00 , B64D29/02 , B64D33/04
摘要： A fencing assembly (66) for prohibiting circulation of primary and/or fan airflows (52), (54) into a bounded low pressure region of a jet engine installation. The fencing assembly includes one or more flow control fences. In an exemplary application, the fencing assembly includes a number of fences positioned around the sides of a batcave (48) bounded low pressure region that is located between a primary exhaust nozzle (20) and strut fairings (30). The fencing assembly includes five fences, each fence being connected to either the primary exhaust nozzle or the strut fairings. The five fences include single fences (70), (72) positioned along each lateral side of the batcave; two rear fences (74), (74') positioned circumferentially about rear regions of the batcave; and an arcuate fence (76) positioned near the two rear fences to form a half circle. The fences include a foot portion (78) and an upright portion (80).
摘要翻译：一种用于禁止将主风扇和/或风扇气流（52），（54）循环到喷气发动机装置的有界低压区域中的围栏组件（66）。围栏组件包括一个或多个流动控制栅栏。在示例性应用中，围栏组件包括围绕位于主排气喷嘴（20）和支柱整流罩（30）之间的限定低压区域的窖（48）的侧面周围的多个栅栏。围栏组件包括五个栅栏，每个围栏连接到主排气喷嘴或支柱整流罩。五个围栏包括沿着蝙蝠的每个侧面定位的单篱笆（70），（72）两个后围栏（74），（74'）围绕所述蝙蝠的后部区域周向定位; 以及位于两个后挡板附近的弓形围栏（76）以形成半圆形。围栏包括脚部（78）和直立部（80）。

2. 发明授权

US06983912B2 Hybrid exhaust heat shield for pylon mounted gas turbine engines 失效
公开(公告)号：US06983912B2
公开(公告)日：2006-01-10
申请号：US10136817
申请日：2002-04-30
申请人： Thomas J. Connelly , Michael L. Sangwin , Michael W. Su
发明人： Thomas J. Connelly , Michael L. Sangwin , Michael W. Su
IPC分类号： B64C1/00
CPC分类号： B64D33/04 , B64D29/02
摘要： The present invention is a hybrid engine exhaust heat shield assembly that includes a plurality of sections. The plurality of sections include one or more sections formed of titanium (or other high heat resistant material) by a casting process, and one or more sections formed of another heat resistant material produced in a manner other than a casting process. The plurality of sections are aerodynamically shaped for thermal protection of the aft pylon. The other heat resistant material is titanium (or other high heat resistant material) that is formed by a hot formed process, or by a super plastically-formed process. The one or more sections formed by the casting process includes heat (plume) deflector flanges.

3. 发明授权

US06178740B2 Turbo fan engine nacelle exhaust system with concave primary nozzle plug 有权
标题翻译：涡轮风扇发动机机舱排气系统带凹形主喷嘴塞
公开(公告)号：US06178740B2
公开(公告)日：2001-01-30
申请号：US09257408
申请日：1999-02-25
申请人： Michael W. Su , Steve D. Podleski , Thomas A. Gally , Sean A. Newsum
发明人： Michael W. Su , Steve D. Podleski , Thomas A. Gally , Sean A. Newsum
IPC分类号： F02K302
CPC分类号： F02K1/78 , B64D33/06 , F02K1/00 , F02K1/386 , F05D2250/712 , Y02T50/671
摘要： A turbo fan engine nacelle houses an engine which forces engine exhaust through a primary nozzle and a fan nozzle positioned along a common central axis. The primary nozzle is bordered interiorly by a primary nozzle plug and bordered exteriorly by a primary nozzle sleeve. The fan nozzle is bordered interiorly by a core cowl and bordered exteriorly by a fan nozzle sleeve. The primary nozzle plug includes a generally cone shaped outer surface which is concave when viewed in side elevation. The concave outer surface has a radius of curvature (Rc). The core cowl has a distal end which is radially spaced from the outer surface of the primary plug by a distance (&Dgr;H) in a direction perpendicular to the central axis. The primary nozzle plug and core cowl define a ratio Rc/&Dgr;H between approximately 14 and 18. The distal end of the core cowl has a core cowl radius Rp with respect to the central axis. A discharge end of the fan nozzle sleeve has a fan nozzle sleeve radius Rf, wherein a ratio Rp/Rf is between approximately 0.4 and 0.6. The outer surface of the primary plug forms a primary plug angle &phgr;p between approximately 13° and 19° with respect to the central axis at the primary nozzle exit. The proper scaling of these key dimensions thereby defines a primary nozzle which reduces the shock associated noise of the turbo fan engine.
摘要翻译：涡轮风扇发动机机舱容纳发动机，其通过主喷嘴和沿共同的中心轴定位的风扇喷嘴迫使发动机排气。主喷嘴在内部由主喷嘴塞接合并且由主喷嘴套筒外部边界。风扇喷嘴在内部由核心罩盖接合，并由风扇喷嘴套筒外部接合。主喷嘴塞包括大致锥形的外表面，当从侧视图观察时，该外表面是凹形的。凹面外表面具有曲率半径（Rc）。核心整流罩具有远离主体塞的外表面沿垂直于中心轴线的方向径向间隔距离（DELTAH）的远端。主喷嘴塞和芯总成在约14和18之间限定了比率Rc / DELTAH。核心整流罩的远端相对于中心轴线具有一个核心整流罩半径R p。风扇喷嘴套筒的排出端具有风扇喷嘴套筒半径Rf，其中比率Rp / Rf在大约0.4和0.6之间。主塞的外表面在主喷嘴出口处相对于中心轴形成大约13°和19°之间的主要插塞角度。这些关键尺寸的适当缩放因此限定了一个主喷嘴，其减少涡轮风扇发动机的冲击相关噪声。

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