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1. 发明授权

US09714084B2 Supersonic aircraft with spike for controlling and reducing sonic boom 有权
公开(公告)号：US09714084B2
公开(公告)日：2017-07-25
申请号：US14074913
申请日：2013-11-08
申请人： Gulfstream Aerospace Corporation
发明人： Preston A. Henne , Donald C. Howe
IPC分类号： B64C30/00 , B64C23/04
CPC分类号： B64C23/04 , B64C30/00
摘要： Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when the vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region there between and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.

2. 发明授权

US09482155B2 Isentropic compression inlet for supersonic aircraft 有权
标题翻译：超音速飞机的等熵压缩入口
公开(公告)号：US09482155B2
公开(公告)日：2016-11-01
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： F02C7/04 , B64D33/02 , B64C30/00 , F02K7/10
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。

3. 发明授权

US10731556B2 Isentropic compression inlet for supersonic aircraft 有权
公开(公告)号：US10731556B2
公开(公告)日：2020-08-04
申请号：US15164557
申请日：2016-05-25
申请人： Gulfstream Aerospace Corporation
发明人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
IPC分类号： F02C7/04 , B64C30/00 , F02K7/10 , B64D33/02 , F02C7/042 , B64D27/16 , B64D29/00
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.

4. 发明申请

US20160076448A1 AIR INLET ARRANGEMENT AND METHOD OF MAKING THE SAME 审中-公开
公开(公告)号：US20160076448A1
公开(公告)日：2016-03-17
申请号：US14952309
申请日：2015-11-25
申请人： Gulfstream Aerospace Corporation
发明人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
IPC分类号： F02C7/04 , F02K3/02 , F02K1/46
CPC分类号： F02K1/46 , B64D33/02 , B64D2033/026 , B64D2033/0273 , B64D2033/0286 , F02C7/00 , F02C7/04 , F02C7/045 , F02K1/04 , F02K1/34 , F02K3/02 , F02K7/00 , F02K7/10 , F02K7/16 , F02K7/20 , F05D2210/12 , F05D2220/323 , F05D2220/80 , F05D2230/60 , F05D2250/70 , F05D2260/96 , Y10T29/49346 , Y10T137/0536
摘要： An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.

5. 发明授权

US11208969B2 Air inlet arrangement and method of making the same 有权
公开(公告)号：US11208969B2
公开(公告)日：2021-12-28
申请号：US14952309
申请日：2015-11-25
申请人： Gulfstream Aerospace Corporation
发明人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
IPC分类号： F02K1/46 , F02K1/04 , F02C7/00 , F02K7/16 , F02K7/10 , F02C7/045 , F02K7/00 , F02K7/20 , B64D33/02 , F02K3/02 , F02K1/34 , F02C7/04
摘要： An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.

6. 发明申请

US20160265433A1 ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT 审中-公开
公开(公告)号：US20160265433A1
公开(公告)日：2016-09-15
申请号：US15164557
申请日：2016-05-25
申请人： Gulfstream Aerospace Corporation
发明人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
IPC分类号： F02C7/042 , B64D33/02 , B64C30/00 , B64D27/16 , B64D29/00
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.

7. 发明申请

US20140306058A1 Supersonic Aircraft with Spike for Controlling and Reducing Sonic Boom 有权
标题翻译：超音速飞机与尖峰控制和减少声波
公开(公告)号：US20140306058A1
公开(公告)日：2014-10-16
申请号：US14074913
申请日：2013-11-08
申请人： Gulfstream Aerospace Corporation
发明人： Preston A. Henne , Donald C. Howe
IPC分类号： B64C1/40 , B64C30/00
CPC分类号： B64C23/04 , B64C30/00
摘要： Method and arrangement for reducing the effects of a some boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region there between and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.
摘要翻译：当所述车辆以超音速飞行时，用于减少由航空航天车辆产生的一些起重机的影响的方法和装置。该方法包括向航空航天车辆提供从其鼻部基本上沿着航空航天飞行器的正常飞行方向延伸的第一尖峰，第一尖钉具有位于前端部的后部的第一部分的第二部分，第一和第二部分在其间具有第二过渡区域，每个部分具有不同的横截面积，第一尖端的前端部朝向预定的横截面逐渐变细，第一过渡区域在预定的横截面和第一部分。第一过渡区被配置为在航空航天器的正常超音速飞行期间减少第一尖峰产生的冲击波的聚结。还可以包括从航空航天车辆的尾部延伸的尖峰，以减少在航空航天器的正常超音速飞行期间由尖峰产生的冲击波的聚结。

8. 再颁专利

USRE47304E1 Nozzle arrangement and method of making the same 有权
公开(公告)号：USRE47304E1
公开(公告)日：2019-03-19
申请号：US15693226
申请日：2017-08-31
申请人： Gulfstream Aerospace Corporation
发明人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
IPC分类号： F02K1/46 , F02K1/04 , B64D33/02 , F02K3/02 , F02C7/04
摘要： A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a nozzle having a trailing edge and a plug body partially positioned within the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface. A protruding portion of the plug body extends downstream of the trailing edge for a length greater than a conventional plug body length. The plug body is configured to shape the exhaust gases to flow substantially parallel to a free stream of air flowing off of the trailing edge of the nozzle and to cause the plume of exhaust gases to isentropically turn the free stream of air to move in a direction parallel to a longitudinal axis of the plug body.

9. 发明申请

US20130098454A1 ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT 有权
标题翻译：超音速航空器的ISENTROPIC压缩入口
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。

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