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21. 发明申请

US20140348665A1 PIN-FIN ARRAY 有权
标题翻译： PIN-FIN阵列
公开(公告)号：US20140348665A1
公开(公告)日：2014-11-27
申请号：US14453366
申请日：2014-08-06
申请人： General Electric Company
发明人： Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2240/304 , F05D2260/2212 , F05D2260/2214
摘要： The present application provides an airfoil with a cooling flow therein. The airfoil may include an internal cooling passage, a number of cooling holes in communication with the internal cooling passage, and a number of pin-fins positioned within the internal cooling passage. The pin-fins are arranged with one or more turning openings and one or more guiding openings so as to direct the cooling flow towards the cooling holes.
摘要翻译：本申请提供其中具有冷却流的翼型件。翼型件可以包括内部冷却通道，与内部冷却通道连通的多个冷却孔以及位于内部冷却通道内的多个销翅片。销翅片布置有一个或多个转动开口和一个或多个引导开口，以便将冷却流引向冷却孔。

22. 发明申请

US20140212269A1 COOLING FOR A FLUID FLOW MACHINE 审中-公开
标题翻译：冷却液流动机
公开(公告)号：US20140212269A1
公开(公告)日：2014-07-31
申请号：US14239139
申请日：2012-08-02
申请人： Christoph Kastner , Rudolf Potter
发明人： Christoph Kastner , Rudolf Potter
IPC分类号： F01D3/04
CPC分类号： F01D3/04 , F01D3/02 , F01D25/26 , F02C7/141 , F05D2220/31 , F05D2260/213 , F05D2260/2214 , F05D2260/22141 , F05D2260/2322
摘要： A fluid flow machine, in particular a steam turbine, is provided having a piston-equalizing line which conducts a vapour from a fresh vapour region of a second flow duct to a thrust-equalizing piston, wherein the surface of the piston-equalizing line is enlarged, and wherein the inner surface of the piston-equalizing line is enlarged.
摘要翻译：提供了一种流体流动机，特别是蒸汽涡轮机，其具有将来自第二流动管道的新鲜蒸汽区域的蒸汽传导到推力均衡活塞的活塞均衡管线，其中活塞均衡管线的表面是并且其中活塞均衡线的内表面被扩大。

23. 发明授权

US08764394B2 Component cooling channel 有权
标题翻译：组件冷却通道
公开(公告)号：US08764394B2
公开(公告)日：2014-07-01
申请号：US12985553
申请日：2011-01-06
申请人： Ching-Pang Lee , John J. Marra , Gary B. Merrill , Benjamin E. Heneveld , Jill Klinger
发明人： Ching-Pang Lee , John J. Marra , Gary B. Merrill , Benjamin E. Heneveld , Jill Klinger
IPC分类号： F01D5/18 , F28F3/04 , F28F7/02
CPC分类号： F01D5/18 , F01D5/187 , F05D2240/304 , F05D2250/13 , F05D2260/2214 , F28F3/048 , F28F7/02
摘要： A cooling channel (36, 36B) cools an exterior surface (40 or 42) or two opposed exterior surfaces (40 and 42). The channel has a near-wall inner surface (48, 50) with a width (W1). Interior side surfaces (52, 54) may converge to a reduced channel width (W2). The near-wall inner surface (48, 50) may have fins (44) aligned with a coolant flow (22). The fins may highest at mid-width of the near-wall inner surface. A two-sided cooling channel (36) may have two near-wall inner surfaces (48, 50) parallel to two respective exterior surfaces (40, 42), and may have an hourglass shaped transverse sectional profile. The tapered channel width (W1, W2) and the fin height profile (56A, 56B) increases cooling flow (22) into the corners (C) of the channel for more uniform and efficient cooling.
摘要翻译：冷却通道（36,36B）冷却外表面（40或42）或两个相对的外表面（40和42）。通道具有宽度（W1）的近壁内表面（48,50）。内侧表面（52,54）可以会聚到减小的通道宽度（W2）。近壁内表面（48,50）可以具有与冷却剂流（22）对准的翅片（44）。翅片在近壁内表面的中间宽度处可能最高。双面冷却通道（36）可以具有两个平行于两个相应的外表面（40,42）的近壁内表面（48,50），并且可以具有沙漏形横截面轮廓。锥形通道宽度（W1，W2）和翅片高度轮廓（56A，56B）将冷却流（22）增加到通道的拐角（C），以实现更均匀和有效的冷却。

24. 发明授权

US08585351B2 Gas turbine blade 有权
标题翻译：燃气轮机叶片
公开(公告)号：US08585351B2
公开(公告)日：2013-11-19
申请号：US13806196
申请日：2011-06-01
申请人： Vitaly Bregman , Mikhail Petukhovskiy
发明人： Vitaly Bregman , Mikhail Petukhovskiy
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/20 , F05D2240/307 , F05D2260/20 , F05D2260/2214
摘要： A gas turbine blade including a root, an airfoil with a leading edge and a trailing edge, a radial outer tip, and a pressure side and a suction side between the leading edge and the trailing edge, and a cooling air channel system extending from an air inlet opening in the root throughout the airfoil to a plurality of air outlets at the pressure side and the leading edge of the top of the tip of the airfoil.
摘要翻译：一种包括根部的燃气轮机叶片，具有前缘和后缘的翼型件，径向外端头，以及前缘和后缘之间的压力侧和吸力侧;以及冷却空气通道系统，其从在整个翼型件的根部中的空气入口开口到在压力侧的多个空气出口和翼型的顶端的顶部的前缘。

25. 发明申请

US20130232991A1 AIRFOIL WITH IMPROVED INTERNAL COOLING CHANNEL PEDESTALS 有权
标题翻译：具有改进的内部冷却通道的AIRFOIL
公开(公告)号：US20130232991A1
公开(公告)日：2013-09-12
申请号：US13413969
申请日：2012-03-07
申请人： Edwin Otero
发明人： Edwin Otero
IPC分类号： F02C7/18 , F01D5/18
CPC分类号： F01D5/187 , F01D5/188 , F05D2240/304 , F05D2250/14 , F05D2250/231 , F05D2260/202 , F05D2260/2214
摘要： An airfoil for a turbine engine, the airfoil including a first side wall, a second side wall spaced apart from the first side wall, and an internal cooling channel formed between the first side wall and the second side wall. The internal cooling channel includes at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall. The internal cooling channel also includes a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end. At least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end.
摘要翻译：一种用于涡轮发动机的翼型件，所述翼型件包括第一侧壁，与第一侧壁间隔开的第二侧壁以及形成在第一侧壁和第二侧壁之间的内部冷却通道。内部冷却通道包括具有连接到第一侧壁的第一基座端和连接到第二侧壁的第二基座端的至少一个基座。内部冷却通道还包括在第一侧壁和第一基座端之间围绕第一基座端部的周边设置的第一圆角; 以及在所述第二侧壁和所述第二基座端之间围绕所述第二基座端部的周边设置的第二圆角。第一圆角和第二圆角中的至少一个包括在相应基座端的周边周围不均匀的轮廓。

26. 发明申请

US20130142649A1 COOLED TURBINE BLADE AND METHOD FOR COOLING A TURBINE BLADE 有权
标题翻译：冷却涡轮叶片和用于冷却涡轮叶片的方法
公开(公告)号：US20130142649A1
公开(公告)日：2013-06-06
申请号：US13308927
申请日：2011-12-01
申请人： Matthew Durham Collier , Anthony Louis Giglio , Gayathri Puram
发明人： Matthew Durham Collier , Anthony Louis Giglio , Gayathri Puram
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/225 , F05D2260/201 , F05D2260/204 , F05D2260/205 , F05D2260/2214 , Y02T50/673 , Y02T50/676
摘要： A cooled turbine blade comprises a root for fixing the blade to rotor, an airfoil extending along a radial axis from the root, and a tip shroud disposed at a radially outward end of the airfoil. The tip shroud extends in a circumferential direction from the airfoil and defines, within itself, a core plenum and a peripheral plenum. The airfoil defines an aft airfoil cooling passage that extends radially through the airfoil proximate a trailing edge portion of the airfoil. The airfoil also defines an aft cooling inlet for providing an aft stream of cooling fluid to the aft airfoil cooling passage. The airfoil also defines at least one aft cooling exit for discharging the aft stream of cooling fluid from the aft airflow cooling passage to the peripheral plenum. The tip shroud defines at least one peripheral plenum vent for discharging the aft stream of cooling fluid.
摘要翻译：冷却的涡轮叶片包括用于将叶片固定到转子的根部，沿着径向轴线从根部延伸的翼型件，以及设置在翼型件的径向向外端部处的尖端护罩。尖端护罩从翼型件在圆周方向上延伸，并且在其本身内限定出一个内部集气室和一个周边通风室。翼型件限定了靠近翼型件的后缘部分的径向延伸穿过翼型件的后翼型件冷却通道。翼型件还限定了一个后部冷却入口，用于向后翼型冷却通道提供冷却流体的后部流。翼型件还限定至少一个后冷却出口，用于将后流冷却流体从尾气流冷却通道排出到周边通风室。尖端罩限定了至少一个周边通风口，用于排出冷却流体的后部流。

27. 发明申请

US20130091824A1 GAS TURBINE AND GAS-TURBINE PLANT HAVING THE SAME 有权
标题翻译：气体涡轮机及其涡轮机厂
公开(公告)号：US20130091824A1
公开(公告)日：2013-04-18
申请号：US13806961
申请日：2011-10-27
申请人： Masayuki Murakami , Kazuya Higashi , Yukimasa Nakamoto , Satoko Fujii , Takeyuki Shimizu , Keigo Matsumoto
发明人： Masayuki Murakami , Kazuya Higashi , Yukimasa Nakamoto , Satoko Fujii , Takeyuki Shimizu , Keigo Matsumoto
IPC分类号： F02C7/232 , F23R3/34 , F23R3/36 , F02C9/40
CPC分类号： F02C7/232 , F01D25/12 , F02C3/30 , F02C7/14 , F02C7/222 , F02C7/228 , F02C9/40 , F05D2260/213 , F05D2260/2214 , F05D2260/608 , F23D2209/30 , F23K2301/203 , F23R3/283 , F23R3/343 , F23R3/36
摘要： The invention provides a gas-turbine fuel nozzle (1) that includes a plurality of fuel supply channels (3a) to which fuel is supplied, a plurality of fuel/scavenging-fluid supply channels (3b) to which fuel or a scavenging fluid for scavenging the fuel is supplied, and a plurality of injection holes (7a, 7b) that are provided at downstream ends of the fuel supply channels (3a) or the fuel/scavenging-fluid supply channels (3b) and that inject the fuel guided from the fuel supply channels (3a) or the fuel/scavenging-fluid supply channels (3b); a scavenging-fluid supply channel (21) that is connected to the fuel/scavenging-fluid supply channels (3b) to guide the scavenging fluid; and scavenging-fluid cooling means (23) for cooling the scavenging fluid to a temperature lower than a self-ignition temperature of the fuel.
摘要翻译：本发明提供了一种燃气涡轮燃料喷嘴（1），其包括供应燃料的多个燃料供应通道（3a），多个燃料/扫气流体供应通道（3b），燃料或清除流体供提供清除燃料的多个喷射孔（7a，7b），其设置在燃料供给通道（3a）或燃料/扫气流体供应通道（3b）的下游端，并且喷射从燃料供应通道（3a）或燃料/清除液供应通道（3b）; 与所述燃料/清扫液供给通道（3b）连接以引导所述清扫流体的扫气供给通道（21）; 以及用于将清扫流体冷却至低于燃料的自燃温度的温度的扫气流体冷却装置（23）。

28. 发明授权

US08348613B2 Airflow influencing airfoil feature array 有权
标题翻译：气流影响翼型特征阵列
公开(公告)号：US08348613B2
公开(公告)日：2013-01-08
申请号：US12413649
申请日：2009-03-30
申请人： Shawn J. Gregg , Tracy A. Propheter-Hinckley , Amanda Jean Learned
发明人： Shawn J. Gregg , Tracy A. Propheter-Hinckley , Amanda Jean Learned
IPC分类号： B64C11/00
CPC分类号： F01D5/189 , F05D2240/121 , F05D2240/303 , F05D2260/201 , F05D2260/2214 , F05D2260/22141
摘要： An example gas turbine engine airfoil includes an airfoil wall establishing a cavity that extends axially from an airfoil leading edge portion to an airfoil trailing edge portion and extends radially from an airfoil inner end to an airfoil outer end. The cavity is configured to receive a baffle that is spaced from the airfoil leading edge portion such that an impingement cooling area is established between the airfoil leading edge portion and the baffle when the baffle is received within the cavity. An array of nonuniformly distributed features is disposed on the airfoil wall within the impingement cooling area. The features are configured to influence airflow within the impingement cooling area.
摘要翻译：一个示例性的燃气涡轮发动机翼型件包括一个翼型壁，其形成一个空腔，其从翼型件前缘部分轴向延伸到翼型件后缘部分，并从翼型件内端径向延伸到翼型件外端。空腔构造成接收与翼型件前缘部分间隔开的挡板，使得当挡板接收在空腔内时，在翼型件前缘部分和挡板之间建立冲击冷却区域。不均匀分布的特征阵列设置在冲击冷却区域内的翼型壁上。这些特征被配置成影响冲击冷却区域内的气流。

29. 发明申请

US20120301319A1 Curved Passages for a Turbine Component 审中-公开
标题翻译：涡轮组件弯曲通道
公开(公告)号：US20120301319A1
公开(公告)日：2012-11-29
申请号：US13114702
申请日：2011-05-24
申请人： Benjamin Paul Lacy , Jesse Blair Butler
发明人： Benjamin Paul Lacy , Jesse Blair Butler
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/186 , F01D5/187 , F05D2250/292 , F05D2250/314 , F05D2250/71 , F05D2260/221 , F05D2260/2214 , Y02T50/673 , Y02T50/676 , Y10T29/49341
摘要： A turbine component may generally comprise an airfoil having a base and a tip disposed opposite the base. The airfoil may further include a pressure side surface and a suction side surface extending between a leading edge and a trailing edge. An airfoil circuit may be at least partially disposed within the airfoil and may be configured to supply a medium through the airfoil. The turbine component may also include a curved passage defined in the airfoil so as to be in flow communication with the airfoil circuit. Additionally, an outlet may be defined through the pressure side surface or the suction side surface of the airfoil. The outlet may be in flow communication with the curved passage and may have a cross-sectional area that is greater than a cross-sectional area of the curved passage.
摘要翻译：涡轮机部件通常可以包括具有基部和与基部相对设置的尖端的翼型件。翼型件还可以包括在前缘和后缘之间延伸的压力侧表面和吸力侧表面。翼型电路可以至少部分地设置在翼型内，并且可以被配置成通过翼型件提供介质。涡轮机部件还可以包括限定在翼型件中的弯曲通道，以便与翼型件回路流动连通。此外，可以通过翼型的压力侧表面或吸力侧表面限定出口。出口可以与弯曲通道流动连通，并且可以具有大于弯曲通道的横截面面积的横截面面积。

30. 发明授权

US07866947B2 Turbine blade trip strip orientation 有权
标题翻译：涡轮叶片脱扣条取向
公开(公告)号：US07866947B2
公开(公告)日：2011-01-11
申请号：US11648929
申请日：2007-01-03
申请人： Edward F. Pietraszkiewicz , James P. Downs
发明人： Edward F. Pietraszkiewicz , James P. Downs
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D5/186 , F01D5/188 , F05D2240/126 , F05D2240/127 , F05D2250/183 , F05D2250/314 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , Y02T50/676
摘要： A turbine component includes a coolant passage and a plurality of trip members that extend within the coolant passage. Each of the plurality of trip members includes an orientation relative to an expected flow direction through the coolant passage. At least three of the trip members have orientations that are different from each other. For example, the orientations of the trip members progressively transition along the length of the coolant passage.
摘要翻译：涡轮机部件包括在冷却剂通道内延伸的冷却剂通道和多个跳闸部件。多个跳闸构件中的每一个包括相对于穿过冷却剂通道的预期流动方向的取向。至少三个跳闸构件具有彼此不同的取向。例如，跳闸构件的取向沿着冷却剂通道的长度逐渐过渡。

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