专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

11. 发明授权

US08844553B2 Passive boundary layer bleed system for nacelle inlet airflow control 有权
标题翻译：被动边界层排气系统，用于机舱入口气流控制
公开(公告)号：US08844553B2
公开(公告)日：2014-09-30
申请号：US12446786
申请日：2006-10-12
申请人： Steven H. Zysman , Wesley K. Lord , Robert M. Miller , Oliver V. Atassi
发明人： Steven H. Zysman , Wesley K. Lord , Robert M. Miller , Oliver V. Atassi
IPC分类号： F02C7/04 , F02C7/045 , F02K3/06 , B64D33/02
CPC分类号： F02C7/04 , B64D33/02 , B64D2033/0226 , F02C7/045 , F05D2250/324 , F05D2250/71 , F05D2270/17 , Y10T137/0536
摘要： A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle.
摘要翻译：燃气涡轮发动机系统包括具有压力侧和吸力侧的机舱。通道在压力侧和吸力侧之间延伸，允许从压力侧到吸力侧的气流。通道在机舱上接收湍流气流，以在通道后面的机舱上方产生层流气流，从而减少机舱上的阻力。

12. 发明授权

US08708274B2 Transverse mounted gas turbine engine 有权
标题翻译：横向安装的燃气轮机
公开(公告)号：US08708274B2
公开(公告)日：2014-04-29
申请号：US13228942
申请日：2011-09-09
申请人： Wesley K. Lord
发明人： Wesley K. Lord
IPC分类号： B64D27/00
CPC分类号： F02C6/206 , B64D27/14 , B64D35/06 , B64D2027/005 , F05D2220/324 , F05D2220/325 , Y02T50/44 , Y02T50/66 , Y02T50/671
摘要： A propulsion engine comprises a compressor, a combustor and a turbine arranged in flow series about a turbine axis. A shaft is coupled to the turbine along the turbine axis, and first and second propulsions fans are rotationally coupled to the turbine at opposite ends of the shaft. The first and second propulsion fans rotate substantially parallel to one another, and transversely with respect to the turbine axis.
摘要翻译：推进发动机包括压缩机，燃烧器和涡轮机，其围绕涡轮机轴线流动。轴沿着涡轮机轴线联接到涡轮机，并且第一和第二推进风扇在轴的相对端旋转地联接到涡轮机。第一和第二推进风扇基本上彼此平行地旋转，并且相对于涡轮轴线横向旋转。

13. 发明授权

US06379110B1 Passively driven acoustic jet controlling boundary layers 有权
标题翻译：被动驱动的声喷射控制边界层
公开(公告)号：US06379110B1
公开(公告)日：2002-04-30
申请号：US09257563
申请日：1999-02-25
申请人： Duane C. McCormick , Wesley K. Lord
发明人： Duane C. McCormick , Wesley K. Lord
IPC分类号： F01D2504
CPC分类号： F01D11/08 , B64C23/00 , B64C2230/02 , B64C2230/08 , B64C2230/24 , B64C2230/28 , F01D11/10 , F05D2260/96 , Y02T50/166 , Y10S415/914
摘要： Existing pressure oscillations created by axial or centrifugal fans in a diverging shroud are utilized to power a passive, acoustic jet, the nozzle of which directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, or a duct, the fluid particles in the resonant chamber of the passive acoustic jet being replenished with low momentum flux particles drawn from the fluid flow in a direction normal to the surface, thereby to provide a net time averaged flow of increased momentum flux particles to defer, even eliminate, the onset of boundary layer separation in the diffuser or duct. The passive acoustic jet is used in the vicinity of fan blade tips to alleviate undesirable flow effects in the tip region, such as leakage.
摘要翻译：在发散的护罩中由轴向或离心风扇产生的现有压力振荡用于为被动的声射流提供动力，其中喷嘴将高动量通量气体颗粒基本切向地引入扩散器或管道中的流动的边界层，被动声射流的谐振腔中的流体颗粒被补充有从垂直于表面的方向从流体流中抽出的低动量通量粒子，从而提供增加的动量通量粒子的净时间平均流量推迟甚至消除，扩散器或管道中边界层分离的开始。在风扇叶片尖端附近使用无源的声学射流以减轻尖端区域中的不期望的流动效应，例如泄漏。

14. 发明授权

US5775095A Method of noise suppression for a turbine engine 失效
标题翻译：涡轮发动机噪声抑制方法
公开(公告)号：US5775095A
公开(公告)日：1998-07-07
申请号：US771294
申请日：1996-12-20
申请人： Steven H. Zysman , Wesley K. Lord , Thomas J. Barber
发明人： Steven H. Zysman , Wesley K. Lord , Thomas J. Barber
IPC分类号： F02K1/40 , F02K1/38 , F02K1/46 , F02K1/48 , F02K3/06
CPC分类号： F02K1/386 , F02K1/48 , F05D2200/261
摘要： A method for suppressing noise in a turbofan engine includes segmenting coaxial inner and outer flow streams into circumferentially interleaved inner and outer segments beginning at a common location along the engine axis, diverting additional portions of the outer stream radially inwardly from an axial location downstream of the common location and combining the inner segments, the outer segments and the additional portions into a common stream so that the additional portions are introduced into discrete radial locations in the common stream. The diverted additional portions of the outer stream eliminate localized regions of hot, high velocity gases in the combined stream to achieve improved noise suppression.
摘要翻译：一种用于抑制涡扇发动机发动机噪声的方法包括将同轴的内部和外部流动流分为沿着沿着发动机轴线的公共位置开始的周向交错的内部和外部段，将外部流的附加部分从下游的轴向位置公共位置并且将内部段，外部段和附加部分组合成公共流，使得附加部分被引入公共流中的离散径向位置。外流的转向附加部分消除组合流中热，高速气体的局部区域，以实现改进的噪声抑制。

15. 发明授权

US5638675A Double lobed mixer with major and minor lobes 失效
标题翻译：双叶混合器主要和次生叶
公开(公告)号：US5638675A
公开(公告)日：1997-06-17
申请号：US525113
申请日：1995-09-08
申请人： Steven H. Zysman , Wesley K. Lord , Thomas J. Barber
发明人： Steven H. Zysman , Wesley K. Lord , Thomas J. Barber
IPC分类号： F02K1/40 , F02K1/38 , F02K1/46 , F02K1/48 , F02K3/06
CPC分类号： F02K1/386 , F02K1/48 , F05D2200/261
摘要： A lobed mixer has major and minor lobes. The major lobes increase in both height and width in the downstream axial direction. Each major lobe has two minor lobes positioned on its radially outer surface located downstream of the beginning of the major lobe. The radial depth of the minor lobes increases with downstream axial distance but is never greater than the depth of the major lobes. Each of the chutes formed between the minor lobes introduces an additional stream of cold, low velocity fan flow into the hot, high velocity core flow to improve the uniformity of mixing. The double lobed mixer decreases acoustic intensity while having little or no effect on engine performance.
摘要翻译：破碎的搅拌机有主瓣和小叶。主轴在下游轴向高度和宽度上均有增加。每个主瓣具有位于主瓣开始下游的径向外表面上的两个小叶。次叶的径向深度随着下游轴向距离而增加，但不会大于主瓣的深度。形成在小裂片之间的每个斜槽引入另外的冷的低速风扇流进入热的高速芯流，以提高混合的均匀性。双叶混合器降低声强，同时对发动机性能影响很小或没有影响。

16. 发明申请

US20080190096A1 FLUID MIXER WITH AN INTEGRAL FLUID CAPTURE DUCTS FORMING AUXILIARY SECONDARY CHUTES AT THE DISCHARGE END OF SAID DUCTS 有权
标题翻译：具有集成流体捕集管道的流体混合器在排放终止时形成辅助二次循环
公开(公告)号：US20080190096A1
公开(公告)日：2008-08-14
申请号：US10973103
申请日：2004-10-25
申请人： Wesley K. Lord , Steven H. Zysman , Matthew J. Howlett
发明人： Wesley K. Lord , Steven H. Zysman , Matthew J. Howlett
IPC分类号： F02K1/38
CPC分类号： F02K1/386 , B64D33/06
摘要： A fluid mixer for mixing two fluid streams 40, 42 includes a set of main lobes 26 defining alternating primary and secondary main chutes 30, 32, one or more auxiliary lobes 28 intermediate two of the main lobes, and an auxiliary fluid capture duct 62. The auxiliary lobes are defined, at least in part, by the discharge end of the duct. In operation, the duct conveys secondary fluid to secondary chutes 36 defined by the lobes thereby improving the performance of the mixer despite the presence of an obstruction 18 that would otherwise impede thorough mixing of two fluid streams.
摘要翻译：用于混合两个流体流40,42的流体混合器包括一组主瓣26，其限定了交替的主要主槽30和次主主槽30,32，一个或多个辅助凸角28中间的两个主叶片，以及辅助流体捕获导管62。辅助叶片至少部分地由管道的排放端限定。在操作中，管道将次级流体输送到由叶片限定的次级槽36，由此改善了混合器的性能，尽管存在阻碍物18，否则阻碍了两种流体流的充分混合。

17. 发明授权

US07018172B2 Airfoil surface impedance modification for noise reduction in turbofan engines 有权
标题翻译：涡轮风扇发动机噪声降低的翼型表面阻抗修正
公开(公告)号：US07018172B2
公开(公告)日：2006-03-28
申请号：US10744983
申请日：2003-12-22
申请人： Dilip Prasad , Bruce L. Morin , Wesley K. Lord , Douglas C. Mathews
发明人： Dilip Prasad , Bruce L. Morin , Wesley K. Lord , Douglas C. Mathews
IPC分类号： F04D29/66
CPC分类号： F04D29/667 , F01D5/16 , F01D5/18 , F04D29/324 , F05D2260/96 , F05D2270/17 , Y02T50/671 , Y02T50/673 , Y02T50/676 , Y10S416/50
摘要： In accordance with the present invention, an aircraft engine is provided with a component which helps reduce the noise generated by the engine. The component has a first aerodynamic surface, a second aerodynamic surface, and a system for reducing noise without altering a pressure differential between the first aerodynamic surface and the second aerodynamic surface.
摘要翻译：根据本发明，飞机发动机设置有有助于降低发动机产生的噪音的部件。该部件具有第一空气动力学表面，第二空气动力学表面和用于在不改变第一空气动力学表面和第二空气动力学表面之间的压力差的情况下降低噪音的系统。

18. 发明授权

US06203269B1 Centrifugal air flow control 有权
标题翻译：离心式气流控制
公开(公告)号：US06203269B1
公开(公告)日：2001-03-20
申请号：US09257483
申请日：1999-02-25
申请人： Peter F. Lorber , Wesley K. Lord
发明人： Peter F. Lorber , Wesley K. Lord
IPC分类号： F01D514
CPC分类号： B64C21/025 , B64C11/18 , B64C27/467 , B64C2230/20 , B64C2230/28 , F01D5/145 , F04D29/682 , F04D29/684 , Y02T50/166 , Y02T50/66 , Y02T50/673 , Y10S415/914
摘要： Blades, including helicopter rotor blades, gas turbine engine fan blades, air moving machinery fan blades, and the like, have an air inlet near the hub of the blade, which may be on the pressure side of the blade and/or near the leading edge or trailing edge nearer the tip of the blades, with an air plenum between the air inlet and the slots, whereby air is forced into the inlet, through the plenum and out of the slots into the flow adjacent the blades. The slots may be through the suction surface of the blade, typically near the boundary layer separation point, so that air flowing out of the slots into the boundary layer of the suction surface of the blade, thereby delay or prevent the onset of boundary layer separation, or to reduce supersonic shock. The inlet may be near the trailing edge of the blade, near the root, adjacent to the air inlet of the core of a jet engine, to suction off air and reduce fan wake blockage at the core inlet. The slots may be through the pressure surface adjacent the blade tip edge of fan blades to reduce blade tip leakage effects.
摘要翻译：包括直升机转子叶片，燃气涡轮发动机风扇叶片，气动机械风扇叶片等的叶片在叶片的轮毂附近具有空气入口，其可以在叶片的压力侧和/或靠近叶片的压力侧靠近叶片尖端的边缘或后缘，在空气入口和狭槽之间具有空气增压室，由此空气被迫进入入口，通过气室，并从槽中进入与叶片相邻的流中。槽可以通过叶片的吸附表面，通常在边界层分离点附近，使得空气从槽中流出到叶片的吸力表面的边界层中，从而延迟或防止边界层分离的开始，或减少超音速冲击。入口可以靠近叶片的后缘，靠近根部，与喷气发动机的核心的空气入口相邻，以吸入空气并减少在核心入口处的风扇尾部堵塞。槽可以通过与风扇叶片的叶片尖端边缘相邻的压力表面，以减少叶片尖端泄漏效应。

19. 发明授权

US08839805B2 Passive boundary layer bleed system for nacelle inlet airflow control 有权
公开(公告)号：US08839805B2
公开(公告)日：2014-09-23
申请号：US12428582
申请日：2009-04-23
申请人： Steven H. Zysman , Wesley K. Lord , Robert M. Miller , Oliver V. Atassi
发明人： Steven H. Zysman , Wesley K. Lord , Robert M. Miller , Oliver V. Atassi
IPC分类号： F02K3/06 , F02C7/04 , F02C7/045 , B64D33/02
CPC分类号： F02C7/04 , B64D33/02 , B64D2033/0226 , B64D2033/0286 , F05D2240/14 , F05D2260/60 , F05D2270/17 , Y10T137/0536
摘要： A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle.

20. 发明申请

US20130062463A1 TRANSVERSE MOUNTED GAS TURBINE ENGINE 有权
标题翻译：横向安装气体涡轮发动机
公开(公告)号：US20130062463A1
公开(公告)日：2013-03-14
申请号：US13228942
申请日：2011-09-09
申请人： Wesley K. Lord
发明人： Wesley K. Lord
IPC分类号： B64D27/14 , B64C11/48 , F02C3/10 , B64C5/06
CPC分类号： F02C6/206 , B64D27/14 , B64D35/06 , B64D2027/005 , F05D2220/324 , F05D2220/325 , Y02T50/44 , Y02T50/66 , Y02T50/671
摘要： A propulsion engine comprises a compressor, a combustor and a turbine arranged in flow series about a turbine axis. A shaft is coupled to the turbine along the turbine axis, and first and second propulsions fans are rotationally coupled to the turbine at opposite ends of the shaft. The first and second propulsion fans rotate substantially parallel to one another, and transversely with respect to the turbine axis.
摘要翻译：推进发动机包括压缩机，燃烧器和涡轮机，其围绕涡轮机轴线流动。轴沿着涡轮机轴线联接到涡轮机，并且第一和第二推进风扇在轴的相对端旋转地联接到涡轮机。第一和第二推进风扇基本上彼此平行地旋转，并且相对于涡轮轴线横向旋转。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式