公开(公告)号：US08840363B2

公开(公告)日：2014-09-23

申请号：US13228567

申请日：2011-09-09

申请人： Ching-Pang Lee

发明人： Ching-Pang Lee

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/183 ,  F05D2260/202

摘要： An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a plurality of cooling fluid passages. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling fluid passages are in fluid communication with the cooling fluid cavity and include zigzagged passages that include alternating angled sections, each section having both a radial component and a chordal component. The cooling fluid passages extend from the cooling fluid cavity toward the trailing edge of the outer wall and receive cooling fluid from the cooling fluid cavity for cooling the outer wall near the trailing edge.

摘要翻译： 燃气涡轮发动机中的翼型件包括外壁，冷却流体腔和多个冷却流体通道。 外壁具有前缘，后缘，压力侧，吸力侧以及径向内外端。 冷却流体腔被限定在外壁中，大致径向延伸在外壁的内端和外端之间，并接收用于冷却外壁的冷却流体。 冷却流体通道与冷却流体腔流体连通，并且包括包括交替成角度部分的锯齿形通道，每个部分都具有径向部件和弦部件。 冷却流体通道从冷却流体腔朝向外壁的后缘延伸，并接收来自冷却流体腔的冷却流体，用于冷却靠近后缘的外壁。

公开(公告)号：US20140169962A1

公开(公告)日：2014-06-19

申请号：US13714518

申请日：2012-12-14

申请人： Ching-Pang Lee

发明人： Ching-Pang Lee

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F01D5/186 ,  F01D5/20 ,  F05D2240/307 ,  F05D2250/185 ,  F05D2250/75 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/2214

摘要： An air cooled turbine blade including leading and trailing edges, and pressure and suction side walls extending between the leading and trailing edges. Leading and trailing edge cooling circuits extend spanwise adjacent to the leading and trailing edges, respectively. A forward flow mid-section serpentine cooling circuit extends spanwise and is located between the leading and trailing edge cooling circuits. An axial tip cooling circuit extends in the chordal direction and is located between a tip cap of the blade and the serpentine cooling circuit at an outer end of the serpentine cooling circuit. The axial tip cooling circuit has a forward end receiving cooling air from a final channel of the serpentine cooling circuit and discharges the cooling air adjacent to the trailing edge.

摘要翻译： 包括前缘和后缘的空气冷却涡轮叶片，以及在前缘和后缘之间延伸的压力和吸力侧壁。 前缘和后缘冷却回路分别沿着前缘和后缘分别延伸。 向前流动的中段蛇形冷却回路沿横向延伸并且位于前缘和后缘冷却回路之间。 轴向尖端冷却回路在弦向延伸，位于蛇形冷却回路的外端处，位于叶片的顶盖和蛇形冷却回路之间。 轴向尖端冷却回路具有从蛇形冷却回路的最终通道接收冷却空气的前端，并排出与后缘相邻的冷却空气。

公开(公告)号：US08727704B2

公开(公告)日：2014-05-20

申请号：US13213417

申请日：2011-08-19

申请人： Ching-Pang Lee ,  Eric C. Berrong

发明人： Ching-Pang Lee ,  Eric C. Berrong

IPC分类号： F01D11/08

CPC分类号： F01D11/08 ,  F05D2250/70 ,  F05D2260/20

摘要： A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system receives cooling fluid from an outer side of the panel for cooling the panel and includes at least one cooling fluid supply passage, at least one serpentine cooling passage, and at least one cooling fluid discharge passage. The cooling fluid supply passage(s) receive the cooling fluid from the outer side of the panel and deliver the cooling fluid to a first cooling fluid chamber within the panel. The serpentine cooling passage(s) receive the cooling fluid from the first cooling fluid chamber, wherein the cooling fluid provides convective cooling to the panel as it passes through the serpentine cooling passage(s). The cooling fluid discharge passage(s) discharge the cooling fluid from the cooling system.

摘要翻译： 用于燃气涡轮发动机的环段包括面板和冷却系统。 冷却系统从面板的外侧接收冷却流体，用于冷却面板，并且包括至少一个冷却流体供应通道，至少一个蛇形冷却通道和至少一个冷却流体排出通道。 冷却流体供应通道从面板的外侧接收冷却流体，并将冷却流体输送到面板内的第一冷却流体室。 蛇形冷却通道从第一冷却流体室接收冷却流体，其中冷却流体在通过蛇形冷却通道时向面板提供对流冷却。 冷却流体排出通道从冷却系统排出冷却流体。

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。

公开(公告)号：US20130156579A1

公开(公告)日：2013-06-20

申请号：US13766909

申请日：2013-02-14

申请人： Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, JR. ,  John J. Marra

发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, JR. ,  John J. Marra

IPC分类号： F01D5/18 ,  F01D25/12

CPC分类号： F01D5/187 ,  F01D5/082 ,  F01D5/143 ,  F01D9/065 ,  F01D11/001 ,  F01D25/12 ,  F02C7/12 ,  F05D2240/127

摘要： A gas turbine engine including: an ambient-air cooling circuit (10) having a cooling channel (26) disposed in a turbine blade (22) and in fluid communication with a source (12) of ambient air: and an pre-swirler (18), the pre-swirler having: an inner shroud (38); an outer shroud (56); and a plurality of guide vanes (42), each spanning from the inner shroud to the outer shroud. Circumferentially adjacent guide vanes (46, 48) define respective nozzles (44) there between. Forces created by a rotation of the turbine blade motivate ambient air through the cooling circuit. The pre-swirler is configured to impart swirl to ambient air drawn through the nozzles and to direct the swirled ambient air toward a base of the turbine blade. The end walls (50, 54) of the pre-swirler may be contoured.

摘要翻译： 一种燃气涡轮发动机，包括：环境空气冷却回路（10），其具有设置在涡轮机叶片（22）中并与环境空气源（12）流体连通的冷却通道（26）;以及预旋流器 18），所述预旋转器具有：内罩（38）; 外护罩（56）; 以及多个导向叶片（42），每个导向叶片从内护罩跨越到外护罩。 周向相邻的导向叶片（46,48）在其间限定相应的喷嘴（44）。 通过涡轮叶片的旋转产生的力通过冷却回路激励环境空气。 预旋流器被配置为对通过喷嘴抽吸的环境空气赋予涡流，并且将旋转的环境空气引导到涡轮叶片的基部。 预旋转器的端壁（50,54）可以是轮廓。

公开(公告)号：US08317457B2

公开(公告)日：2012-11-27

申请号：US11966348

申请日：2007-12-28

申请人： Aspi Rustom Wadia ,  David Scott Clark ,  Ching-Pang Lee ,  Andrew Breeze-Stringfellow ,  Gregory Scott McNulty

发明人： Aspi Rustom Wadia ,  David Scott Clark ,  Ching-Pang Lee ,  Andrew Breeze-Stringfellow ,  Gregory Scott McNulty

IPC分类号： F01D11/20

CPC分类号： F04D27/02 ,  F04D27/001 ,  F04D29/526 ,  F04D29/687 ,  F05D2270/101 ,  F05D2270/172

摘要： A method of operating a compressor having a row of blades for preventing a compressor stall is disclosed, the method comprising the steps of mounting a plasma generator in a casing or a shroud radially outwardly and apart from the blade tips wherein the plasma generator comprises a radially inner electrode and a radially outer electrode separated by a dielectric material; and supplying an AC potential to the radially inner electrode and the radially outer electrode.

摘要翻译： 公开了一种操作具有用于防止压缩机失速的一排叶片的压缩机的方法，所述方法包括以下步骤：将等离子体发生器沿径向向外并且与叶片尖端分开地安装在壳体或护罩中，其中等离子体发生器包括径向 内部电极和由电介质材料隔开的径向外部电极; 并向所述径向内部电极和所述径向外部电极提供AC电位。

公开(公告)号：US20120269647A1

公开(公告)日：2012-10-25

申请号：US13090294

申请日：2011-04-20

申请人： Paul H. Vitt ,  David A. Kemp ,  Ching-Pang Lee ,  John J. Marra

发明人： Paul H. Vitt ,  David A. Kemp ,  Ching-Pang Lee ,  John J. Marra

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F01D5/188 ,  F05D2250/30 ,  F05D2260/221 ,  F05D2260/941

摘要： An airfoil in a gas turbine engine includes an outer wall and an inner wall. The outer wall includes a leading edge, a trailing edge opposed from the leading edge in a chordal direction, a pressure side, and a suction side. The inner wall is coupled to the outer wall at a single chordal location and includes portions spaced from the pressure and suction sides of the outer wall so as to form first and second gaps between the inner wall and the respective pressure and suction sides. The inner wall defines a chamber therein and includes openings that provide fluid communication between the respective gaps and the chamber. The gaps receive cooling fluid that provides cooling to the outer wall as it flows through the gaps. The cooling fluid, after traversing at least substantial portions of the gaps, passes into the chamber through the openings in the inner wall.

摘要翻译： 燃气涡轮发动机中的翼型件包括外壁和内壁。 外壁包括前缘，从前缘朝向方向相对的后缘，压力侧和吸力侧。 内壁在单个弦位置处联接到外壁，并且包括与外壁的压力和吸力侧隔开的部分，以便在内壁和相应的压力和吸力侧之间形成第一和第二间隙。 内壁在其中限定一个室，并且包括在相应间隙和室之间提供流体连通的开口。 间隙接收冷却流体，当其流过间隙时，向外壁提供冷却。 冷却流体在穿过至少大部分间隙之后通过内壁中的开口进入腔室。

公开(公告)号：US08226360B2

公开(公告)日：2012-07-24

申请号：US12262437

申请日：2008-10-31

申请人： Patrick Jarvis Scoggins ,  James Harvey Laflen ,  Ching-Pang Lee ,  Wilson Frost

发明人： Patrick Jarvis Scoggins ,  James Harvey Laflen ,  Ching-Pang Lee ,  Wilson Frost

IPC分类号： F01D1/02

CPC分类号： F01D9/041 ,  F01D25/246 ,  F05D2220/3212 ,  F05D2240/55 ,  F05D2250/182 ,  Y02T50/671

摘要： A turbine nozzle includes a row of vanes extending radially between annular outer and inner bands. The outer band includes a pair of radial flanges defining an annular seal groove therebetween. One of the flanges is crenelated to improve nozzle life.

摘要翻译： 涡轮喷嘴包括在环形外带和内带之间径向延伸的一排叶片。 外带包括在其间限定环形密封槽的一对径向凸缘。 其中一个法兰被切割以改善喷嘴寿命。

公开(公告)号：US20120057960A1

公开(公告)日：2012-03-08

申请号：US13213459

申请日：2011-08-19

申请人： Eric C. Berrong ,  Ching-Pang Lee ,  Akash Bhatia ,  Ryan S. Yamane ,  Stefan Tschirren ,  Leonard J. Meyer

发明人： Eric C. Berrong ,  Ching-Pang Lee ,  Akash Bhatia ,  Ryan S. Yamane ,  Stefan Tschirren ,  Leonard J. Meyer

IPC分类号： F01D9/02

CPC分类号： F01D11/08 ,  F05D2250/70 ,  F05D2260/20

摘要： A ring segment is provided for a gas turbine engine includes a panel and a cooling system. Cooling fluid is provided to an outer side of the panel and an inner side of the panel defines at least a portion of a hot gas flow path through the engine. The cooling system is located within that panel and receives cooling fluid from the outer side of the panel for cooling the panel. The cooling system includes a plurality of cooling fluid passages that receive cooling fluid from the outer side of the panel. The cooling fluid passages each have a generally axially extending portion that includes at least one fork. The fork(s) divide each cooling fluid passage into at least two downstream portions that each receives cooling fluid from the respective axially extending portion.

摘要翻译： 提供了一种用于燃气涡轮发动机的环段，其包括面板和冷却系统。 冷却流体设置在面板的外侧，并且面板的内侧限定通过发动机的热气体流路的至少一部分。 冷却系统位于该面板内并从面板的外侧接收冷却流体以冷却面板。 冷却系统包括从板的外侧接收冷却流体的多个冷却流体通道。 冷却流体通道各自具有包括至少一个叉的大致轴向延伸的部分。 叉子将每个冷却流体通道分成至少两个下游部分，每个下游部分从相应的轴向延伸部分接收冷却流体。

公开(公告)号：US20120014808A1

公开(公告)日：2012-01-19

申请号：US12836060

申请日：2010-07-14

申请人： Ching-Pang Lee

发明人： Ching-Pang Lee

IPC分类号： F01D5/18

CPC分类号： F01D25/12 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/22141

摘要： A serpentine coolant flow path (54A-54G) formed by inner walls (50, 52) in a cavity (49) between pressure and suction side walls (22, 24) of a turbine airfoil (20A). A coolant flow (58) enters (56) an end of the airfoil, flows into a span-wise channel (54A), then flows forward (54B) over the inner surface of the pressure side wall, then turns behind the leading edge (26), and flows back along a forward part of the suction side wall, then follows a loop (54E) forward and back around an inner wall (52), then flows along an intermediate part of the suction side wall, then flows into an aft channel (54G) between the pressure and suction side walls, then exits the trailing edge (28). This provides cooling matched to the heating topography of the airfoil, minimizes differential thermal expansion, revives the coolant, and minimizes the flow volume needed.

摘要翻译： 由涡轮机翼（20A）的压力侧和吸力侧壁（22,24）之间的空腔（49）中的内壁（50,52）形成的蛇形冷却剂流动路径（54A-54G）。 冷却剂流（58）进入（56）翼型件的端部，流入跨度通道（54A），然后在压力侧壁的内表面上向前（54B）流动，然后在前缘 26），并且沿吸力侧壁的前部流回，然后围绕内壁（52）向前和向后循环（54E），然后沿着吸力侧壁的中间部分流动，然后流入 在压力侧和吸力侧壁之间的后通道（54G），然后离开后缘（28）。 这提供了与翼型件的加热形状相匹配的冷却，最小化差异热膨胀，恢复冷却剂，并最小化所需的流量。