公开(公告)号：US09297333B2

公开(公告)日：2016-03-29

申请号：US14468406

申请日：2014-08-26

申请人： The Boeing Company

发明人： Evan J. Filter

IPC分类号： F02C7/04 ,  B64D33/02 ,  F02K1/06 ,  F01D25/24 ,  F01D25/00 ,  F02C7/042

CPC分类号： F02K1/06 ,  B64C11/001 ,  B64C2201/162 ,  B64D33/02 ,  B64D2033/0286 ,  F01D25/005 ,  F01D25/24 ,  F02C7/042

摘要： A variable geometry inlet for a ducted fan is selectively transitionable between a first and second mode. The inlet includes a retractable ring that extends circumferentially about the inlet and is selectively movable between an axially extended position in the first mode and an axially retracted position in the second mode. A tube extends circumferentially proximate the retractable ring, and is pressurizable to a relatively deflated state in the first mode and to a relatively inflated state in the second mode. A stretchable skin extends circumferentially proximate the retractable ring, and is elastically deformable in at least a circumferential direction about a longitudinal axis of the fan. A leading edge of the inlet in the first mode is defined by the stretchable skin disposed against a forward edge of the retractable ring, and in the second mode by the stretchable skin disposed against at least a portion of the tube.

摘要翻译： 用于管道风扇的可变几何入口可在第一和第二模式之间选择性地转换。 所述入口包括可围绕所述入口周向延伸的可伸缩环，并且可选择地在所述第一模式中的轴向延伸位置和所述第二模式中的轴向缩回位置之间移动。 管子周向地延伸靠近可伸缩环延伸，并且在第一模式中可加压到相对放气的状态，并且在第二模式中可以相对膨胀。 可拉伸的皮肤周向地延伸靠近可伸缩环延伸，并且可围绕风扇的纵向轴线在至少周向方向上弹性变形。 第一模式中的入口的前缘由抵靠可伸缩环的前边缘设置的可伸展皮肤限定，并且在第二模式中由靠在管的至少一部分上设置的可伸展皮肤限定。

公开(公告)号：US09027583B2

公开(公告)日：2015-05-12

申请号：US13705211

申请日：2012-12-05

申请人： Gulfstream Aerospace Corporation

发明人： Timothy R. Conners

IPC分类号： F02B27/00 ,  F02C7/042 ,  B64D33/02 ,  F02C7/045

CPC分类号： B64D33/02 ,  B64D29/00 ,  B64D33/06 ,  B64D2033/026 ,  B64D2033/0273 ,  F02C7/042 ,  F02C7/045 ,  F02K3/025 ,  F02K7/16 ,  F05D2220/80 ,  Y02T50/672 ,  Y10T137/0368 ,  Y10T137/0536

摘要： A supersonic inlet having a cowl lip configured to capture the conic shock and exhibit a zero or substantially zero cowl angle is disclosed herein. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine.

摘要翻译： 本文公开了一种超音速入口，其具有配置成捕获圆锥冲击并且呈现零或基本上零前角的整流罩。 入口可以被配置为采用松弛的等熵压缩表面和内部旁路。 机舱旁路可以防止由锥形冲击的捕获引入的流动变形到达涡轮机械，从而允许前导角减小到零或基本为零。 这样的前导角度可以减小入口对超音速飞行器的整体声波爆震特征的贡献，同时允许发动机压力恢复增加，并随后改善发动机产生的推力。

公开(公告)号：US20150050140A1

公开(公告)日：2015-02-19

申请号：US14444130

申请日：2014-07-28

申请人： ALSTOM Technology Ltd

发明人： Robin PAYNE ,  Eribert Benz

IPC分类号： F02C7/042

CPC分类号： F02C7/042 ,  F02C1/005 ,  F02C3/34 ,  F02C7/04 ,  F02C7/08

摘要： An improved intake arrangement, for a compressor having a compressor blading, includes a manifold divided by a barrier into two sections, to convey, from one section, a flue gas stream, and, from other section, an air stream. Further, the intake arrangement includes a converging section configured to the manifold and extends convergingly to the compressor defining an inlet to the compressor blading. The converging section includes inner and outer ring members disposed coaxially to each other, between which there extends, coaxially and convergingly, the barrier to at least up to a certain distance within the converging section, defining a converging nozzle therebetween. The converging nozzle includes a mixing feature adapted to enhance mixing of the flue gas and air streams.

摘要翻译： 对于具有压缩机叶片的压缩机，改进的进气装置包括由隔板分成两部分的歧管，以从一个部分输送烟道气流以及从其它部分输送气流。 此外，进气装置包括被配置到歧管并且会聚地延伸到限定了压缩机叶片的入口的压缩机的会聚部分。 会聚部分包括彼此同轴设置的内圈和外圈构件，它们在会聚部分之间至少在一定距离之间延伸，同轴并且会聚地形成阻挡件，在它们之间限定了会聚喷嘴。 会聚喷嘴包括适于增强烟气和空气流的混合的混合特征。

公开(公告)号：US20130098454A1

公开(公告)日：2013-04-25

申请号：US13629181

申请日：2012-09-27

申请人： Gulfstream Aerospace Corporation

发明人： Timothy R. Conners ,  Preston A. Henne ,  Donald C. Howe

IPC分类号： F02C7/042

CPC分类号： F02C7/04 ,  B64C30/00 ,  B64D27/16 ,  B64D29/00 ,  B64D33/02 ,  B64D2033/026 ,  F02C7/042 ,  F02K7/10 ,  F05D2210/33 ,  F05D2220/80 ,  F05D2250/70 ,  Y10T29/49323 ,  Y10T137/0318 ,  Y10T137/0536

摘要： A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining overall engine performance.

摘要翻译： 超音速入口包括松弛的等熵压缩表面，以通过使入口的压缩表面成形来改善净推进力，以将所得的冲击离开整流罩。 入口压缩表面的松弛等熵压缩成形功能可减少罩面表面角度，从而改善入口阻力特性和干涉阻力特性。 根据本发明的超音速进气口还显示了在保持总体发动机性能的同时降低了峰值声波悬臂超压。

公开(公告)号：US20050131616A1

公开(公告)日：2005-06-16

申请号：US10965150

申请日：2004-10-15

申请人： Fuminori Fujii

发明人： Fuminori Fujii

IPC分类号： F01D17/00 ,  F01D15/10 ,  F01D17/02 ,  F02C7/042 ,  F02C7/057 ,  F02C9/28 ,  G06F19/00

CPC分类号： F01D15/10 ,  F02C9/28 ,  F05D2220/76 ,  F05D2270/061 ,  F05D2270/081 ,  F05D2270/304 ,  Y02T50/677

摘要： A turbine mechanical output computation device computes a gas turbine mechanical output P from the following equation P = Pe + J × g × ( 2 ⁢ π 60 ) 2 × N × ⅆ N ⅆ t where Pe represents a generator effective power measured by a generator effective power wattmeter, N represents the rotational speed of a gas turbine measured by a gas turbine tachometer, J represents the moment of inertia of the gas turbine, and g represents gravitational acceleration. A combustion air amount controller controls the amount of combustion air based on the gas turbine mechanical output P.

摘要翻译： 涡轮机械输出计算装置从以下等式计算燃气涡轮机械输出P.