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21. 发明申请

US20150118037A1 CENTRIFUGAL FAN 审中-公开
标题翻译：离心风扇
公开(公告)号：US20150118037A1
公开(公告)日：2015-04-30
申请号：US14472438
申请日：2014-08-29
申请人： MINEBEA CO., LTD.
发明人： Takako OTSUKA , Hitoshi IKUTA , Seiya FUJIMOTO , Takayuki YAMASAKI
IPC分类号： F04D17/08 , F04D29/28 , F04D29/42 , F04D25/06
CPC分类号： F04D25/0613 , F04D17/16 , F04D29/281 , F04D29/30 , F05D2240/305
摘要： There is provided a centrifugal fan including a casing having an upper casing with an opening and a lower casing with a recess, a motor disposed in the recess, and an impeller housed in the casing. The impeller includes an annular shroud formed with an inlet, plural blades which are arranged between the annular shroud and the lower casing, and a hub which is connected to respective inner sides of the blades. Each of the blades includes, at a pressure surface side, a first inclined surface which is inclined toward a negative pressure surface of the blade as approaching the lower casing from the annular shroud; and a second inclined surface which is provided closer to the lower casing than the first inclined surface, and is inclined toward the negative pressure surface at an angle steeper than that of the first inclined surface.
摘要翻译：提供了一种离心式风扇，其具有壳体，该壳体具有开口的上壳体和具有凹部的下壳体，设置在凹部中的电动机和容纳在壳体中的叶轮。叶轮包括形成有入口的环形护罩，布置在环形护罩和下壳体之间的多个叶片，以及连接到叶片的相应内侧的毂。每个叶片在压力表面侧包括朝向叶片的负压表面倾斜的第一倾斜表面，从而从环形护罩接近下壳体; 以及比第一倾斜面更靠近下壳体设置的第二倾斜面，并且以比第一倾斜面更陡的角度向负压面倾斜。

22. 发明申请

US20140248157A1 BLADE OR VANE OF DIFFERING ROUGHNESS AND PRODUCTION PROCESS 审中-公开
标题翻译：不同粗糙度和生产过程的叶片或叶片
公开(公告)号：US20140248157A1
公开(公告)日：2014-09-04
申请号：US14061870
申请日：2013-10-24
申请人： Fathi Ahmad
发明人： Fathi Ahmad
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F04D29/023 , F04D29/284 , F04D29/30 , F04D29/324 , F04D29/681 , F05B2250/60 , F05B2250/61 , F05B2250/611 , F05B2250/62 , F05B2250/621 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2240/31 , F05D2250/60 , F05D2250/61 , F05D2250/611 , F05D2250/62 , F05D2250/621 , F05D2300/516 , F05D2300/611 , Y02T50/673 , Y10T29/49336
摘要： A blade or vane of different roughness and a process for producing such a blade or vane are presented. The performance of the blade or vane of a compressor or of a turbine can be improved because of the different configuration of the roughness of the surfaces on the suction side and the pressure side of the blade or vane.
摘要翻译：提供了不同粗糙度的叶片或叶片以及用于生产这种叶片或叶片的方法。压缩机或涡轮机的叶片或叶片的性能可以被改善，因为在叶片或叶片的吸入侧和压力侧上的表面的粗糙度的不同构造。

23. 发明申请

US20140090401A1 Endwall Controuring 有权
标题翻译：端壁控制
公开(公告)号：US20140090401A1
公开(公告)日：2014-04-03
申请号：US13663977
申请日：2012-10-30
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Thomas J. Praisner , Andrew S. Aggarwala , Eric A. Grover , Renee J. Jurek
IPC分类号： F01D9/00 , F02C3/04
CPC分类号： F01D5/145 , F01D5/143 , F04D29/324 , F04D29/329 , F04D29/547 , F04D29/681 , F05D2240/123 , F05D2240/305 , F05D2250/712 , Y02T50/673
摘要： An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoil array may further include a convex profiled region extending from the endwall adjacent the first side of at least one of said plurality of airfoils and near the leading edge of the at least one of said plurality of airfoils. The airfoil array may further include a concave profiled region in the endwall adjacent the first side of said at least one of said plurality of airfoils and aft of the convex profiled region.
摘要翻译：公开了一种翼型阵列。翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。每个翼型件可以具有在前缘和后缘之间以弦状轴向延伸的第一侧和相对的第二侧。翼型阵列还可以包括从邻近所述多个翼型中的至少一个翼型件的第一侧的端壁延伸并且在所述多个翼型中的至少一个翼型件的前缘附近的凸形轮廓区域。所述翼型阵列还可包括邻近所述多个翼型件中的所述至少一个翼型件的第一侧和所述凸形轮廓区域的后部的所述端壁中的凹形轮廓区域。

24. 发明申请

US20130323080A1 VORTEX GENERATORS FOR IMPROVED FILM EFFECTIVENESS 有权
标题翻译： VORTEX发生器，用于改善膜片的有效性
公开(公告)号：US20130323080A1
公开(公告)日：2013-12-05
申请号：US13488858
申请日：2012-06-05
申请人： Thomas J. Martin , Alexander Staroselsky , Thomas N. Slavens , Mark F. Zelesky , Joel H. Wagner
发明人： Thomas J. Martin , Alexander Staroselsky , Thomas N. Slavens , Mark F. Zelesky , Joel H. Wagner
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/145 , F05D2240/121 , F05D2240/123 , F05D2240/303 , F05D2240/305 , F05D2250/181 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/294 , F05D2260/202 , F05D2260/212 , Y02T50/673 , Y02T50/676
摘要： An airfoil includes a suction surface, a pressure surface, a first showerhead cooling hole and a second showerhead cooling hole. The suction surface and the pressure surface both extend axially between a leading edge and a trailing edge, as well as radially from a root section to a tip section. The first showerhead cooling hole and the second showerhead cooling hole both extend into pressure surface near the leading edge. The first showerhead cooling hole and the second showerhead cooling hole are angled in opposing directions.
摘要翻译：翼型件包括抽吸表面，压力表面，第一喷头冷却孔和第二喷头冷却孔。抽吸表面和压力表面两者在前缘和后缘之间轴向延伸，以及从根部到末端部的径向延伸。第一淋浴头冷却孔和第二淋浴头冷却孔都延伸到靠近前缘的压力表面。第一淋浴头冷却孔和第二淋浴头冷却孔在相反的方向上成角度。

25. 发明授权

US08317474B1 Turbine blade with near wall cooling 有权
标题翻译：涡轮叶片近壁冷却
公开(公告)号：US08317474B1
公开(公告)日：2012-11-27
申请号：US12689285
申请日：2010-01-19
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18 , F01D5/08
CPC分类号： F01D5/188 , F01D5/186 , F05D2240/305 , F05D2240/306
摘要： An air cooled turbine blade with an array of sinusoidal shaped chordwise extending cooling air passages that start from a leading edge of the airfoil and extend to the trailing edge on both the pressure side and suction side walls. The sinusoidal shaped cooling channels on the pressure side merge with the sinusoidal shaped cooling channels on the suction side in a trailing edge region cooling channel and exit the blade through a row of trailing edge exit holes. Cooling air from a forward cooling supply cavity provides impingement cooling air for the leading edge that then flows into the sinusoidal shaped cooling channels.
摘要翻译：一种空气冷却的涡轮机叶片，其具有从翼型的前缘开始并延伸到压力侧和吸入侧壁上的后缘的正弦形弦向延伸的冷却空气通道阵列。压力侧的正弦形冷却通道与后缘区域冷却通道中的吸入侧的正弦形冷却通道合并，并通过一排后缘出口孔离开叶片。来自前向冷却供应腔的冷却空气为前缘提供冲击冷却空气，然后流入正弦形冷却通道。

26. 发明授权

US08231330B1 Turbine blade with film cooling slots 有权
标题翻译：涡轮叶片带薄膜冷却槽
公开(公告)号：US08231330B1
公开(公告)日：2012-07-31
申请号：US12466566
申请日：2009-05-15
申请人： George Liang
发明人： George Liang
IPC分类号： B63H1/14
CPC分类号： F01D5/186 , F05D2240/304 , F05D2240/305
摘要： A turbine rotor blade with a row of exit slots adjacent to a trailing edge region of the airfoil that extends from the platform to the blade tip, where the row of exit slots is formed into three groups that include an upper span group, a mid-span group and a lower span group. The upper span group discharges film cooling air upward with respect to the airfoil chordwise direction, the mid-span group discharges along the chordwise direction, and the lower span group discharges in a direction downward with respect to the chordwise direction. Each exit slot is formed with a plurality of metering inlet holes that discharge into a first diffusion section and then a second diffusion section.
摘要翻译：一种涡轮转子叶片，具有一排出口狭槽，该出口狭槽与翼型件的后边缘区域相邻，该翼缘从该平台延伸到叶片尖端，其中一排出口槽形成三组，其包括上跨距组，跨度组和下跨度组。上跨组相对于翼型方向向上排放薄膜冷却空气，中跨组沿着弦方向排出，下跨距组相对于弦方向向下排放。每个出口槽形成有多个计量入口孔，其排放到第一扩散部分中，然后排放到第二扩散部分。

27. 发明授权

US5498133A Pressure regulated film cooling 失效
标题翻译：压力调节膜冷却
公开(公告)号：US5498133A
公开(公告)日：1996-03-12
申请号：US471291
申请日：1995-06-06
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2240/305 , F05D2240/306 , F05D2250/52 , F05D2260/202
摘要： A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges and spaced apart from each other to define at least one internal flow channel for channeling cooling air therein. A plenum is defined by an inner surface of the first sidewall and by an internal wall adjoining the flow channel. A pair of injection holes extend through the internal wall to feed the cooling air into the plenum. A plurality of film cooling holes extend through the first sidewall in flow communication with the plenum for channeling the cooling air in a film along an outer surface of the first sidewall to effect film cooling. The injection holes are aligned to converge toward each other so that cooling air jets discharged therefrom collide with each other inside the plenum to reduce pressure thereof. This regulates the pressure across the film cooling holes to improve film cooling.
摘要翻译：燃气涡轮发动机翼型件包括在相对的前缘和后缘处连接在一起并且彼此间隔开的第一和第二侧壁，以限定至少一个用于在其中引导冷却空气的内部流动通道。气室由第一侧壁的内表面和毗邻流动通道的内壁限定。一对注射孔延伸穿过内壁，以将冷却空气送入气室。多个膜冷却孔延伸穿过第一侧壁，与气室成流动连通，用于沿着第一侧壁的外表面引导薄膜中的冷却空气，以实现薄膜冷却。喷射孔对准，朝向彼此会聚，使得排出的冷却空气射流彼此在气室内相互碰撞以减小压力。这调节膜冷却孔的压力以改善膜冷却。

28. 发明公开

US20240376824A1 GAS TURBINE AIRFOIL NOISE REDUCTION 审中-公开
公开(公告)号：US20240376824A1
公开(公告)日：2024-11-14
申请号：US18314244
申请日：2023-05-09
申请人： General Electric Company
发明人： Balaraju Suresh , Guru Venkata Dattu Jonnalagadda , Trevor Howard Wood , Nicholas Joseph Kray , Vishnu Vardhan Venkata Tatiparthi , Nitesh Jain
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2220/323 , F05D2220/36 , F05D2240/305 , F05D2240/306 , F05D2260/961
摘要： An airfoil for a turbofan engine includes a first contoured sidewall, a second contoured sidewall, a leading edge, and a trailing edge with each extending in a spanwise direction defined between a root and a tip portion of the airfoil. The first contoured sidewall and the second contoured sidewall define an outer surface of the airfoil. The airfoil further includes a plurality of protrusions where each protrusion of the plurality of protrusions has a curvilinear shape and extends outwardly from the outer surface along at least one of the first contoured sidewall or the second contoured sidewall. The plurality of protrusions is defined downstream from a mid-point of a chord length of the airfoil and terminates upstream of the trailing edge.

29. 发明公开

US20240151146A1 COOLING SCHEMES FOR AIRFOILS FOR GAS TURBINE ENGINES 审中-公开
公开(公告)号：US20240151146A1
公开(公告)日：2024-05-09
申请号：US18404278
申请日：2024-01-04
申请人： RTX Corporation
发明人： Brandon W. Spangler , David R. Pack
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/187 , F01D5/147 , F05D2240/303 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2250/11 , F05D2260/201 , F05D2260/22141
摘要： Airfoils and core assemblies for such airfoils are described. The airfoils include a leading edge cavity defined, in part, by a leading edge interior rib and a trailing edge cavity defined, in part, by a trailing edge interior rib. A plurality of pressure side cavities are defined by pressure side skin cavity walls with at least one pressure side skin cavity wall not extending to the suction side wall. A plurality of suction side cavities are defined by suction side skin cavity walls with at least one suction side skin cavity wall not extending to the pressure side wall. A main body cavity extends between the leading edge interior rib and the trailing edge interior rib and the plurality of side cavities are arranged in a staggered pattern to define the bounds of the main body cavity.

30. 发明公开

US20240018871A1 AIRFOIL ASSEMBLY WITH FIBER-REINFORCED COMPOSITE RINGS AND TOOTHED EXIT SLOT 审中-公开
公开(公告)号：US20240018871A1
公开(公告)日：2024-01-18
申请号：US18183079
申请日：2023-03-13
申请人： RAYTHEON TECHNOLOGIES CORPORATION
发明人： Jon E. Sobanski
IPC分类号： F01D5/18 , F01D5/08 , F01D5/14 , F01D5/28 , F01D9/04
CPC分类号： F01D5/187 , F01D5/081 , F01D5/14 , F01D5/147 , F01D5/18 , F01D5/282 , F01D9/041 , F05D2220/323 , F05D2240/305 , F05D2240/306 , F05D2260/2214 , F05D2300/601 , F05D2300/603
摘要： A method of fabricating a fiber-reinforced airfoil ring includes providing a mandrel that has a mandrel suction side and mandrel pressure side, and forming an endless braid around the mandrel. The endless braid conforms to the mandrel suction side and the mandrel pressure side. The endless braid is then consolidated with a matrix material. The mandrel is then removed, leaving the consolidated endless braid as a fiber-reinforced airfoil ring that has a suction side wall that extends between inner and outer platforms, a pressure side wall that extends between the inner and outer platforms, and suction and pressure side mate faces along, respectively, edges of the suction side wall and the pressure side wall, and at least one of the suction or pressure side mate faces includes protrusions along a trailing edge.

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