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1. 发明申请

US20150247411A1 BLADE TIP 有权
标题翻译：刀尖
公开(公告)号：US20150247411A1
公开(公告)日：2015-09-03
申请号：US14613744
申请日：2015-02-04
申请人： ROLLS-ROYCE PLC
发明人： Ian Colin Deuchar CARE , Stephane BARALON
IPC分类号： F01D5/20 , B23P15/04
CPC分类号： F01D5/20 , B23P15/04 , F01D5/147 , F01D5/282 , F04D29/023 , F04D29/324 , F05D2210/33 , F05D2220/36 , F05D2240/307 , F05D2300/603 , F05D2300/6032 , F05D2300/612 , F05D2300/614 , Y10T29/49337 , Y10T29/49339
摘要： There is provided a blade tip for a rotary blade. The blade tip is formed of a metal foam and comprises at least one vortex generator. The vortex generator may comprise at least one passageway and/or cavity in the blade tip. In use, a vortex is created between the blade tip and a fan casing adjacent the blade tip.
摘要翻译：提供了用于旋转叶片的叶片尖端。叶片尖端由金属泡沫形成并且包括至少一个涡流发生器。涡流发生器可以包括叶片尖端中的至少一个通道和/或空腔。在使用中，在叶片尖端和与叶片尖端相邻的风扇壳体之间产生涡流。

2. 发明授权

US08690536B2 Turbine blade tip with vortex generators 失效
标题翻译：涡轮叶片尖端与涡流发生器
公开(公告)号：US08690536B2
公开(公告)日：2014-04-08
申请号：US12892515
申请日：2010-09-28
申请人： Alexander R. Beeck , Glenn E. Brown
发明人： Alexander R. Beeck , Glenn E. Brown
IPC分类号： F01D5/20 , F01D5/08
CPC分类号： F01D5/20 , F01D5/187 , F05D2210/33 , F05D2240/127 , F05D2250/21 , F05D2260/2212
摘要： A turbine blade for a turbine engine having a tip with one or more vortex generators for reducing tip leakage during operation of the turbine engine. The vortex generators may extend radially outward from the radially outer surface of the tip wall. The vortex generator may be positioned between a rib extending radially outward from the radially outer surface of the tip wall and an intersection between the outer surface of the tip wall and an outer surface on the pressure side. The vortex generators may include a base and three sides forming a triangular point with a first side having a larger surface are than second and third sides. One or more film cooling holes may be formed in the tip wall to provide cooling air to the tip. In one embodiment, film cooling holes may be positioned in one or more vortex generators.
摘要翻译：一种用于涡轮发动机的涡轮叶片，其具有具有一个或多个涡流发生器的尖端，用于在涡轮发动机的运行期间减少尖端泄漏。涡流发生器可以从尖端壁的径向外表面径向向外延伸。涡流发生器可以位于从尖端壁的径向外表面径向向外延伸的肋与尖端壁的外表面与压力侧的外表面之间的交叉点之间。涡流发生器可以包括基部，并且形成具有比第二和第三侧更大表面的第一侧的三角形点的三个边。可以在尖端壁中形成一个或多个薄膜冷却孔，以向尖端提供冷却空气。在一个实施例中，膜冷却孔可以定位在一个或多个涡流发生器中。

3. 发明申请

US20120269648A1 SERPENTINE COOLING CIRCUIT WITH T-SHAPED PARTITIONS IN A TURBINE AIRFOIL 有权
标题翻译：在涡轮机空气中的T形成型的SERPENTINE冷却回路
公开(公告)号：US20120269648A1
公开(公告)日：2012-10-25
申请号：US13092303
申请日：2011-04-22
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2210/33 , F05D2250/185 , F05D2260/2212
摘要： A serpentine cooling circuit (AFT) in a turbine airfoil (34A) starting from a radial feed channel (C1), and progressing axially (65) in alternating tangential directions through interconnected channels (C1, C2, C3) formed between partitions (T1, T2, J1). At least one of the partitions (T1, T2) has a T-shaped transverse section, with a base portion (67) extending from a suction or pressure side wall (64, 62) of the airfoil, and a crossing portion (68, 69) parallel to, and not directly attached to, the opposite pressure or suction side wall (62, 64). Each crossing portion bounds a near-wall passage (N1, N2) adjacent to the opposite pressure or suction side wall (62, 64). Each near-wall passage may have a smaller flow aperture area than one, or each, of two adjacent connected channels (C1, C2, C3). The serpentine circuit (AFT) may follow a forward cooling circuit (FWD) in the airfoil (34A).
摘要翻译：涡轮机翼型（34A）中的蛇形冷却回路（AFT），其从径向进料通道（C1）开始，并且沿交替的切线方向通过形成在分隔件（T1，C2）之间的互连通道（C1，C2，C3） T2，J1）。至少一个隔板（T1，T2）具有T形横截面，其中从翼型件的吸力或压力侧壁（64,62）延伸的基部（67）和交叉部分 69）平行于并且不直接附接到相对的压力或吸力侧壁（62,64）。每个交叉部分限定与相对的压力或吸力侧壁（62,64）相邻的近壁通道（N1，N2）。每个近壁通道可以具有比两个相邻连接的通道（C1，C2，C3）中的一个或每个通道更小的流通孔面积。蛇形回路（AFT）可以跟随机翼（34A）中的向前冷却回路（FWD）。

4. 发明申请

US20120251323A1 IMPELLER 有权
标题翻译：叶轮
公开(公告)号：US20120251323A1
公开(公告)日：2012-10-04
申请号：US13435911
申请日：2012-03-30
申请人： CHUN-LUNG CHIU , HSIANG-JUNG HUANG , HSIN-CHEN LIN , CHIH-HUI WU , BAO-HONG TONG
发明人： CHUN-LUNG CHIU , HSIANG-JUNG HUANG , HSIN-CHEN LIN , CHIH-HUI WU , BAO-HONG TONG
IPC分类号： F01D5/14 , F01D5/02
CPC分类号： F01D5/02 , F01D5/14 , F04D29/188 , F05D2210/33 , F05D2260/96
摘要： An impeller is provided. The impeller includes a hub, a plurality of upper blades, and a plurality of lower blades. The hub has an upper surface and a lower surface. The upper blades are disposed around the hub and connect to the upper surface. The lower blades are disposed around the hub and connect to the lower surface. The upper and lower blades are alternately disposed and outwardly extend from the hub.
摘要翻译：提供叶轮。叶轮包括轮毂，多个上叶片和多个下叶片。轮毂具有上表面和下表面。上叶片围绕轮毂设置并连接到上表面。下刀片设置在轮毂周围并连接到下表面。上下叶片交替地设置并从轮毂向外延伸。

5. 发明申请

US20120199212A1 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：US20120199212A1
公开(公告)日：2012-08-09
申请号：US13338005
申请日：2011-12-27
申请人： Preston A. Henne , Timothy R. Conners , Donald C. Howe
发明人： Preston A. Henne , Timothy R. Conners , Donald C. Howe
IPC分类号： B64D33/02
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 employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, 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 performance.
摘要翻译：超音速入口采用轻松的等熵压缩，以通过使入口的压缩表面成形来改善净推进力。入口压缩表面的轻松等熵压缩成形功能可减少罩面表面的角度，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表现出在保持性能的同时降低峰值声波悬臂超压。

6. 发明授权

US09347324B2 Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles 有权
标题翻译：具有冲击插入件的涡轮机翼型叶片具有多个冲击喷嘴
公开(公告)号：US09347324B2
公开(公告)日：2016-05-24
申请号：US14133773
申请日：2013-12-19
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D5/188 , F01D9/04 , F05D2210/33 , F05D2240/12 , F05D2240/127 , F05D2260/2212
摘要： A turbine vane includes a generally elongated hollow airfoil and a cooling system. The cooling system is positioned within the airfoil and includes a cooling chamber and an impingement insert positioned in the cooling chamber. The impingement insert and an inner surface of an outer wall of the airfoil define a cooling channel therebetween. The impingement insert includes a plurality of impingement nozzles extending toward the inner surface of the outer wall and a plurality of impingement orifices. At least one of the impingement orifices is arranged in a non-aligned pattern with respect to at least one adjacent impingement orifice such that cooling fluid passing out of the at least one impingement orifice does not directly flow into a centerline of a cooling fluid flowpath of cooling fluid passing out of the at least one adjacent impingement orifice.
摘要翻译：涡轮叶片包括大致细长的中空翼型件和冷却系统。冷却系统定位在翼型内，并且包括冷却室和位于冷却室中的冲击插入件。冲击插入件和翼型件的外壁的内表面在它们之间限定冷却通道。冲击插入件包括朝向外壁的内表面延伸的多个冲击喷嘴和多个冲击孔。冲击孔中的至少一个相对于至少一个相邻的冲击孔布置成非对准图案，使得流出至少一个冲击孔的冷却流体不直接流入冷却流体流动路径的中心线从至少一个相邻的冲击孔流出的冷却流体。

7. 发明授权

US09334801B2 Supersonic aircraft jet engine installation 有权
标题翻译：超音速喷气发动机安装
公开(公告)号：US09334801B2
公开(公告)日：2016-05-10
申请号：US13565350
申请日：2012-08-02
申请人： Preston A. Henne , Timothy R. Conners , Donald C. Howe
发明人： Preston A. Henne , Timothy R. Conners , Donald C. Howe
IPC分类号： F02C7/04 , B21D53/92 , F02C7/042 , B64D33/02
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。

8. 发明申请

US20140352276A1 Dual-Vortical-Flow Hybrid Rocket Engine 有权
标题翻译：双涡流混合火箭发动机
公开(公告)号：US20140352276A1
公开(公告)日：2014-12-04
申请号：US14070881
申请日：2013-11-04
申请人： National Chiao Tung University , National Applied Research Laboratories
发明人： Yen-Sen Chen , Men-Zen Wu , Jong-Shinn Wu , Alfred Lai , Jhe-Wei Lin , Tzu-Hao Chou
IPC分类号： F02K9/00
CPC分类号： F02K9/72 , F05D2210/33 , F05D2240/35
摘要： The present invention discloses a dual-vortical-flow hybrid rocket engine, including a main body and a nozzle communicating with an end of the main body. The main body includes a plurality of disk-like combustion chambers arranged longitudinally, and a central combustion chamber formed along the axial portion and communicating the disk-like combustion chambers. Each of the disk-like combustion chambers is provided with a plurality of oxidizer injection nozzles at its inner circumference surface. Inside the disk-like combustion chambers, the oxidizer is injected in nearly the tangent directions of the circumference, and the injection directions are opposite for the neighboring disk-like combustion chambers, which creates vortical flows with opposite rotating directions so as to increase the total residence time of the combustion reactions of the oxidizer and the solid-state fuel in the disk-like combustion chambers of the present invention.
摘要翻译：本发明公开了一种双涡旋混合火箭发动机，其包括主体和与主体的端部连通的喷嘴。主体包括纵向布置的多个盘形燃烧室和沿轴向部分形成并连通圆盘状燃烧室的中心燃烧室。每个盘状燃烧室在其内圆周表面上设置有多个氧化剂注入喷嘴。在盘状燃烧室内部，氧化剂沿着圆周的切线方向喷射，并且相邻的盘状燃烧室的喷射方向相反，这形成相反旋转方向的涡旋流，从而增加总量本发明的盘状燃烧室中的氧化剂和固体燃料的燃烧反应的停留时间。

9. 发明申请

US20140105726A1 TURBINE AIRFOIL VANE WITH AN IMPINGEMENT INSERT HAVING A PLURALITY OF IMPINGEMENT NOZZLES 有权
标题翻译：具有多个冲击喷嘴的涡旋空气涡街风扇
公开(公告)号：US20140105726A1
公开(公告)日：2014-04-17
申请号：US14133773
申请日：2013-12-19
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D9/04 , F05D2210/33 , F05D2240/12 , F05D2240/127 , F05D2260/2212
摘要： A turbine vane includes a generally elongated hollow airfoil and a cooling system. The cooling system is positioned within the airfoil and includes a cooling chamber and an impingement insert positioned in the cooling chamber. The impingement insert and an inner surface of an outer wall of the airfoil define a cooling channel therebetween. The impingement insert includes a plurality of impingement nozzles extending toward the inner surface of the outer wall and a plurality of impingement orifices. At least one of the impingement orifices is arranged in a non-aligned pattern with respect to at least one adjacent impingement orifice such that cooling fluid passing out of the at least one impingement orifice does not directly flow into a centerline of a cooling fluid flowpath of cooling fluid passing out of the at least one adjacent impingement orifice.
摘要翻译：涡轮叶片包括大致细长的中空翼型件和冷却系统。冷却系统定位在翼型内，并且包括冷却室和位于冷却室中的冲击插入件。冲击插入件和翼型件的外壁的内表面在它们之间限定冷却通道。冲击插入件包括朝向外壁的内表面延伸的多个冲击喷嘴和多个冲击孔。冲击孔中的至少一个相对于至少一个相邻的冲击孔布置成非对准图案，使得流出至少一个冲击孔的冷却流体不直接流入冷却流体流动路径的中心线从至少一个相邻的冲击孔流出的冷却流体。

10. 发明申请

US20130327052A1 EXHAUST SYSTEM FOR GAS TURBINES 审中-公开
标题翻译：排气系统用于气体涡轮机
公开(公告)号：US20130327052A1
公开(公告)日：2013-12-12
申请号：US13916396
申请日：2013-06-12
申请人： GENALTA POWER INC.
发明人： Chris O'NEILL , Dobromir FILIP , Joseph KISS , Graham ILLINGWORTH
IPC分类号： F02C6/18 , F02C7/141
CPC分类号： F02C6/18 , F01D25/30 , F02C6/00 , F02C7/141 , F05D2210/33
摘要： An exhaust system is provided for mitigating condensate formation in a common exhaust stack and for effecting improved heat transfer. Reduced condensate formation and improved heat transfer is achieved by inducing non-laminar flow through the common exhaust stack and a heat exchanger operatively coupled to the common exhaust stack. Heat transfer is further improved by dew point control. Non-laminar flow is induced by connecting more than one gas turbine to the common exhaust stack through non-laminar flow inducing arrangements. The various coupling arrangements also add structural rigidity to the common exhaust stack for increased stack height and improved plume dispersion.
摘要翻译：提供了一种排气系统，用于减轻公共排气叠层中的冷凝物形成并实现改进的热传递。通过引导非层流流经公共排气叠层和可操作地连接到公共排气叠层的热交换器来实现冷凝物形成减少和热传递的改善。通过露点控制进一步提高了热传递。通过非层流引导装置将多于一个燃气轮机连接到公共排气叠层引起非层流。各种联接布置还增加了公共排气叠层的结构刚度，以增加堆叠高度和改进的羽流分散。

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