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1. 发明授权

US07467924B2 Turbine blade including revised platform 有权
标题翻译：涡轮叶片包括修订平台
公开(公告)号：US07467924B2
公开(公告)日：2008-12-23
申请号：US11205274
申请日：2005-08-16
申请人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
发明人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
IPC分类号： F01D5/10
CPC分类号： F01D5/3007 , F01D5/22 , F05D2230/31 , F05D2300/132
摘要： The present invention provides a turbine blade having a revised under-platform structure including a unique coating combination that reduces mechanical stress factors within the turbine blade. The turbine blade includes a platform with an airfoil extending upwardly from the airfoil and a root portion extending downwardly from the platform. Two suction side tabs extend a first distance outward from a suction side of the root potion. Two pressure side tabs extend outward from a pressure side of the root portion. One of the two pressure side tabs extends outward a distance similar to the first distance, however, the other of the two pressure side tabs extends outward a distance much smaller than the first distance, which reduces stresses acting on the turbine blade. In addition, a plurality of coatings are systematically applied to the turbine blade to further reduce mechanical stress factors and improve cooling.
摘要翻译：本发明提供一种涡轮叶片，其具有经修改的平台外结构，其包括独特的涂层组合，其减小涡轮叶片内的机械应力因素。涡轮叶片包括具有从翼型件向上延伸的翼型件和从该平台向下延伸的根部的平台。两个吸力侧翼片从根部的吸力侧向外延伸第一距离。两个压力侧翼片从根部的压力侧向外延伸。两个压力侧翼片之一向外延伸一段类似于第一距离的距离，然而，两个压力侧翼片中的另一个突出部向外延伸远远小于第一距离，这减小了作用在涡轮叶片上的应力。另外，将多个涂层系统地施加到涡轮叶片上，以进一步减少机械应力因素并改善冷却。

2. 发明授权

US07452186B2 Turbine blade including revised trailing edge cooling 有权
标题翻译：涡轮叶片包括修正后缘冷却
公开(公告)号：US07452186B2
公开(公告)日：2008-11-18
申请号：US11205299
申请日：2005-08-16
申请人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
发明人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： The present invention provides an improved cooling circuit for a trailing edge of a turbine blade. The cooling circuit includes an inlet passage that receives a airflow and distributes the airflow through a feed passage. The feed passage primarily includes trip strips, at least one barrier including cross-over holes, teardrop shaped protrusions, and pockets disposed along a trailing edge. The geometry and positioning of both the cross-over holes and teardrop shaped protrusions downstream of the cross-over holes have been optimized to maximize cooling efficiency and reduce airflow. An improved transition between the inlet passage and the feed passage is also provided, which is arcuate and allows the airflow to maintain attachment and flow unimpeded from the inlet passage to the feed passage. The geometry of the pockets disposed along the trailing edge is optimized to improve cooling.
摘要翻译：本发明提供了一种用于涡轮叶片的后缘的改进的冷却回路。冷却回路包括入口通道，其接收气流并将气流分配通过进料通道。进料通道主要包括跳闸带，至少一个屏障，包括交叉孔，泪珠形突起和沿后缘设置的凹穴。交叉孔下游的交叉孔和泪滴形突起的几何形状和定位已被优化，以最大化冷却效率并减少气流。还提供了入口通道和进料通道之间的改进的过渡，其是弧形的并且允许气流保持附件和流动从入口通道畅通到进给通道。沿着后缘设置的凹穴的几何形状被优化以改善冷却。

3. 发明授权

US07665968B2 Cooled rotor blade 有权
标题翻译：冷却转子叶片
公开(公告)号：US07665968B2
公开(公告)日：2010-02-23
申请号：US10855183
申请日：2004-05-27
申请人： Dominic J. Mongillo, Jr. , Shawn J. Gregg , Jeffrey R. Levine , Edward Pietraszkiewicz
发明人： Dominic J. Mongillo, Jr. , Shawn J. Gregg , Jeffrey R. Levine , Edward Pietraszkiewicz
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2212 , F05D2260/22141
摘要： A rotor blade is provided that includes a root and a hollow airfoil. The hollow airfoil has a cavity defined by a suction side wall, a pressure side wall, a leading edge, a trailing edge, a base, and a tip. An internal passage configuration is disposed within the cavity. The configuration includes a passage disposed adjacent the leading edge, and an axially extending passage disposed adjacent the tip. The first passage is connected to the second passage. The second passage includes an opening disposed at the trailing edge of the airfoil. A conduit is disposed within the root that is operable to permit airflow through the root and into the leading edge passage, wherein the conduit provides the primary path into the leading edge passage.
摘要翻译：提供了包括根部和中空翼型件的转子叶片。中空翼片具有由吸力侧壁，压力侧壁，前缘，后缘，底座和尖端限定的空腔。内部通道构造设置在空腔内。该构造包括邻近前缘设置的通道和邻近尖端设置的轴向延伸通道。第一个通道连接到第二个通道。第二通道包括设置在翼型的后缘处的开口。管道设置在根部内，其可操作以允许气流通过根部并进入前缘通道，其中导管将主路径提供到前缘通道中。

4. 发明授权

US07195448B2 Cooled rotor blade 有权
标题翻译：冷却转子叶片
公开(公告)号：US07195448B2
公开(公告)日：2007-03-27
申请号：US10855188
申请日：2004-05-27
申请人： Jeffrey R. Levine , Edward Pietraszkiewicz , John Calderbank , Dominic J. Mongillo, Jr.
发明人： Jeffrey R. Levine , Edward Pietraszkiewicz , John Calderbank , Dominic J. Mongillo, Jr.
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/30 , F05D2250/314 , F05D2260/22141
摘要： A rotor blade is provided that includes a root, a hollow airfoil, and a conduit disposed within the root. The hollow airfoil has a cavity defined by a suction side wall, a pressure side wall, a leading edge, a trailing edge, a base, and a tip. An internal passage configuration is disposed within the cavity. The configuration includes a first radial passage, a second radial passage, a rib disposed between and separating the first radial passage and second radial passage, a plurality of crossover apertures disposed within the rib, and a plurality of trip strips disposed within the second radial passage. The trip strips are attached to an interior surface of one or both of the pressure side wall and the suction side wall. The trip strips are disposed within the first radial passage at an angle α that is skewed relative to a cooling airflow direction within the first radial passage, and positioned such that each of the plurality of trip strips converges toward the rib. The rib end of at least a portion of the plurality of trip strips is located between a pair of adjacent crossover apertures. The conduit is operable to permit airflow through the root and into the first passage.
摘要翻译：提供了一种转子叶片，其包括根部，中空翼片和设置在根部内的导管。中空翼片具有由吸力侧壁，压力侧壁，前缘，后缘，底座和尖端限定的空腔。内部通道构造设置在空腔内。该构造包括第一径向通道，第二径向通道，设置在第一径向通道和第二径向通道之间并分离第一径向通道和第二径向通道的肋，布置在肋内的多个交叉孔，以及设置在第二径向通道内的多个跳闸带。脱扣带附接到压力侧壁和吸力侧壁中的一个或两个的内表面。跳闸条以第一径向通道内的相对于冷却风向倾斜的角度α设置在第一径向通道内，并且定位成使得多个跳闸带中的每一个朝向肋收敛。多个跳闸带的至少一部分的肋端部位于一对相邻的交叉孔之间。管道可操作以允许气流通过根部并进入第一通道。

5. 发明授权

US09157329B2 Gas turbine engine airfoil internal cooling features 有权
标题翻译：燃气涡轮发动机翼型内部冷却功能
公开(公告)号：US09157329B2
公开(公告)日：2015-10-13
申请号：US13591773
申请日：2012-08-22
申请人： Daniel C. Nadeau , Jeffrey R. Levine , Dominic J. Mongillo, Jr.
发明人： Daniel C. Nadeau , Jeffrey R. Levine , Dominic J. Mongillo, Jr.
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/127 , F05D2240/305 , F05D2240/306 , F05D2250/185 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes spaced apart pressure and suction walls joined at leading and trailing edges to provide an airfoil. Intermediate walls interconnect the pressure and suction walls to provide cooling passageways. The cooing passageways have interior pressure and suction surfaces that are respectively provided on the pressure and suction walls. Trip strips include a chevron-shaped trip strip that is provided on at least one of the interior pressure and suction surfaces.
摘要翻译：用于燃气涡轮发动机的翼型件包括在前缘和后缘处连接的间隔开的压力和抽吸壁，以提供翼型件。中间壁互连压力和吸力壁，以提供冷却通道。冷却通道具有分别设置在压力和吸力壁上的内部压力和吸力表面。跳闸条包括设置在内部压力和吸力表面中的至少一个上的人字形状的跳闸条。

6. 发明申请

US20140056717A1 GAS TURBINE ENGINE AIRFOIL INTERNAL COOLING FEATURES 有权
标题翻译：气体涡轮发动机气动内燃冷却特点
公开(公告)号：US20140056717A1
公开(公告)日：2014-02-27
申请号：US13591773
申请日：2012-08-22
申请人： Daniel C. Nadeau , Jeffrey R. Levine , Dominic J. Mongillo, JR.
发明人： Daniel C. Nadeau , Jeffrey R. Levine , Dominic J. Mongillo, JR.
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/127 , F05D2240/305 , F05D2240/306 , F05D2250/185 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes spaced apart pressure and suction walls joined at leading and trailing edges to provide an airfoil. Intermediate walls interconnect the pressure and suction walls to provide cooling passageways. The cooing passageways have interior pressure and suction surfaces that are respectively provided on the pressure and suction walls. Trip strips include a chevron-shaped trip strip that is provided on at least one of the interior pressure and suction surfaces.
摘要翻译：用于燃气涡轮发动机的翼型件包括在前缘和后缘处连接的间隔开的压力和抽吸壁，以提供翼型件。中间壁互连压力和吸力壁，以提供冷却通道。冷却通道具有分别设置在压力和吸力壁上的内部压力和吸力表面。跳闸条包括设置在内部压力和吸力表面中的至少一个上的人字形状的跳闸条。

7. 发明申请

US20140219813A1 GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE 审中-公开
标题翻译：燃气涡轮发动机SERPENTINE冷却通风
公开(公告)号：US20140219813A1
公开(公告)日：2014-08-07
申请号：US13618178
申请日：2012-09-14
申请人： Rafael A. Perez , Edward F. Pietraszkiewicz , Jeffrey R. Levine , Dominic J. Mongillo, JR.
发明人： Rafael A. Perez , Edward F. Pietraszkiewicz , Jeffrey R. Levine , Dominic J. Mongillo, JR.
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/187 , F05D2250/183 , F05D2250/185 , F05D2260/2212 , F05D2260/22141 , F05D2270/17 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. The downstream portion includes an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls. A turbulence promoter extends from the outer wall adjacent to the bend in the downstream portion. The turbulence promoter is absent from a stagnation region adjoining the inner wall adjacent to the bend in the downstream portion
摘要翻译：燃气涡轮发动机部件包括具有冷却通道的结构，该冷却通道提供通过内壁彼此分离并通过弯曲部流体连接的上游和下游部分。下游部分包括与内壁相对的外壁，以提供在内壁和外壁之间延伸的下游区域。湍流促进剂从与下游部分中的弯曲部相邻的外壁延伸。在与下游部分中的弯曲部相邻的内壁的停滞区域中不存在湍流促进剂

8. 发明授权

US09045987B2 Cooling for a turbine airfoil trailing edge 有权
标题翻译：冷却涡轮机翼缘后缘
公开(公告)号：US09045987B2
公开(公告)日：2015-06-02
申请号：US13524295
申请日：2012-06-15
申请人： Jeffrey R. Levine , Dominic J. Mongillo , Brandon S. Donnell
发明人： Jeffrey R. Levine , Dominic J. Mongillo , Brandon S. Donnell
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D5/187 , F01D5/145 , F01D5/186 , F01D9/041 , F01D9/065 , F05D2240/122 , F05D2240/304 , F05D2250/12 , F05D2260/202
摘要： An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a first center cooling discharge opening. A pressure side wall of the airfoil and the first platform form an acute angle at the trailing edge. The first fillet is formed around a perimeter of the airfoil where the airfoil extends from the first platform. The pressure side biased cooling discharge openings are along the trailing edge outside of the first fillet. Each pressure side biased cooling discharge opening extends from the trailing edge along the pressure side wall. The first center cooling discharge opening extends along the trailing edge into the first fillet and is centrally located between the pressure side wall and the suction side wall.
摘要翻译：用于燃气涡轮发动机的组件包括第一平台和从第一平台延伸的翼型件。翼型件包括第一圆角，压力侧偏压排出口和第一中心冷却排出口。翼型件的压力侧壁和第一平台在后缘处形成锐角。第一圆角围绕机翼的周边形成，其中翼型件从第一平台延伸。压力侧偏压的冷却排出口沿着第一圆角外侧的后缘。每个压力侧偏压的冷却排放口从后缘沿压力侧壁延伸。第一中心冷却排出口沿着后缘延伸到第一圆角中并且位于压力侧壁和吸力侧壁之间的中心。

9. 发明申请

US20130336767A1 COOLING FOR A TURBINE AIRFOIL TRAILING EDGE 有权
标题翻译：冷却涡轮机空运货物边缘
公开(公告)号：US20130336767A1
公开(公告)日：2013-12-19
申请号：US13524295
申请日：2012-06-15
申请人： Jeffrey R. Levine , Dominic J. Mongillo , Brandon S. Donnell
发明人： Jeffrey R. Levine , Dominic J. Mongillo , Brandon S. Donnell
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D5/187 , F01D5/145 , F01D5/186 , F01D9/041 , F01D9/065 , F05D2240/122 , F05D2240/304 , F05D2250/12 , F05D2260/202
摘要： An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a first center cooling discharge opening. A pressure side wall of the airfoil and the first platform form an acute angle at the trailing edge. The first fillet is formed around a perimeter of the airfoil where the airfoil extends from the first platform. The pressure side biased cooling discharge openings are along the trailing edge outside of the first fillet. Each pressure side biased cooling discharge opening extends from the trailing edge along the pressure side wall. The first center cooling discharge opening extends along the trailing edge into the first fillet and is centrally located between the pressure side wall and the suction side wall.
摘要翻译：用于燃气涡轮发动机的组件包括第一平台和从第一平台延伸的翼型件。翼型件包括第一圆角，压力侧偏压排出口和第一中心冷却排出口。翼型件的压力侧壁和第一平台在后缘处形成锐角。第一圆角围绕机翼的周边形成，其中翼型件从第一平台延伸。压力侧偏压的冷却排出口沿着第一圆角外侧的后缘。每个压力侧偏压的冷却排放口从后缘沿压力侧壁延伸。第一中心冷却排出口沿着后缘延伸到第一圆角中并且位于压力侧壁和吸力侧壁之间的中心。

10. 发明申请

US20130230402A1 TAPERED THERMAL COATING FOR AIRFOIL 有权
标题翻译：用于气流的热转印热涂层
公开(公告)号：US20130230402A1
公开(公告)日：2013-09-05
申请号：US13410675
申请日：2012-03-02
申请人： Jeffrey R. Levine , Shawn J. Gregg
发明人： Jeffrey R. Levine , Shawn J. Gregg
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , Y02T50/676
摘要： An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, the root section and the tip section defining a span therebetween. A thermal coating extends from the root section of the airfoil toward the tip section of the airfoil. A relative coating thickness of the thermal coating decreases by at least thirty percent at full span in the tip section, as compared to minimum span in the root section.
摘要翻译：翼型件包括从前缘到后缘轴向延伸的压力和抽吸表面，并且从根部到尖端部分径向地延伸，根部和末端部分限定了它们之间的跨度。热涂层从翼型的根部朝向翼型的末端部分延伸。与根部中的最小跨度相比，热涂层的相对涂层厚度在末端部分的全跨度处降低至少30％。

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