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1. 发明申请

US20060107668A1 Airfoil with supplemental cooling channel adjacent leading edge 有权
公开(公告)号：US20060107668A1
公开(公告)日：2006-05-25
申请号：US10996539
申请日：2004-11-23
申请人： Frank Cunha , Edward Pietraszkiewicz , David Kontrovitz , Jeffrey Levine , Young Chon , Dominic Mongillo , Bret Teller
发明人： Frank Cunha , Edward Pietraszkiewicz , David Kontrovitz , Jeffrey Levine , Young Chon , Dominic Mongillo , Bret Teller
IPC分类号： F02C7/12
CPC分类号： F01D5/28 , F01D5/18 , F01D5/186 , F01D5/188 , F02C7/12 , F05D2260/202 , Y02T50/67 , Y02T50/673 , Y02T50/676
摘要： An airfoil, and in a disclosed embodiment a rotor blade, has film cooling holes formed at a leading edge. A supplemental film cooling channel is positioned near the leading edge, but spaced toward the trailing edge from the leading edge. The supplemental film cooling channel directs film cooling air onto a suction wall. The supplemental film cooling channel air is generally directed to a location on the suction wall that has raised some challenges in the past. In a disclosed embodiment, the airfoil is provided with a thermal barrier coating, and the supplemental film cooling air protects this thermal barrier coating.

2. 发明申请

US20060093480A1 Airfoil with three-pass serpentine cooling channel and microcircuit 有权
标题翻译：翼型具有三通蛇形冷却通道和微电路
公开(公告)号：US20060093480A1
公开(公告)日：2006-05-04
申请号：US10979597
申请日：2004-11-02
申请人： Frank Cunha , Bret Teller , Young Chon , Dominic Mongillo , Edward Pietraszkiewicz
发明人： Frank Cunha , Bret Teller , Young Chon , Dominic Mongillo , Edward Pietraszkiewicz
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F01D5/187 , F05D2250/13 , F05D2250/185 , F05D2250/23 , F05D2260/202 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： An airfoil, and in a disclosed embodiment a rotor blade, has a serpentine cooling path. To best account for the Coriolis effect, the paths of the serpentine cooling channel have trapezoidal cross-sections. An area of the rotor blade between a smaller side of the trapezoidal-shaped paths, and a facing wall of the rotor blade has high thermal and mechanical stresses, and is a challenge to adequately cool. A microcircuit, which is a very thin cooling circuit having crossing pedestals, is embedded into the blade in this area. The microcircuit provides additional cooling, and addresses the challenges with regard to cooling these areas.
摘要翻译：翼型件，并且在所公开的实施例中，转子叶片具有蛇形冷却路径。为了最好地解释科里奥利效应，蛇形冷却通道的路径具有梯形横截面。在梯形路径的较小侧和转子叶片的相对壁之间的转子叶片的区域具有高的热和机械应力，并且是充分冷却的挑战。微型电路是具有交叉基座的非常薄的冷却回路，嵌入到该区域的叶片中。该微型电路提供额外的冷却，并解决了冷却这些领域的挑战。

3. 发明申请

US20070041838A1 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：US20070041838A1
公开(公告)日：2007-02-22
申请号：US11205274
申请日：2005-08-16
申请人： Robert Charbonneau , Kenneth Botticello , Shawn Gregg , Kirk Hlavaty , Jeffrey Levine , Kenneth Lonczak , Craig McGarrah , Dominic Mongillo , Lisa O'Neill , Edward Pietraszkiewicz , Richard Salzillo , Heather Terry
发明人： Robert Charbonneau , Kenneth Botticello , Shawn Gregg , Kirk Hlavaty , Jeffrey Levine , Kenneth Lonczak , Craig McGarrah , Dominic Mongillo , Lisa O'Neill , Edward Pietraszkiewicz , Richard Salzillo , Heather Terry
IPC分类号： F01D11/00
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离第一距离的距离，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。

4. 发明申请

US20070041835A1 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：US20070041835A1
公开(公告)日：2007-02-22
申请号：US11205299
申请日：2005-08-16
申请人： Robert Charbonneau , Kenneth Botticello , Shawn Gregg , Kirk Hlavaty , Jeffrey Levine , Kenneth Lonczak , Craig McGarrah , Dominic Mongillo , Lisa O'Neill , Edward Pietraszkiewicz , Richard Salzillo , Heather Terry
发明人： Robert Charbonneau , Kenneth Botticello , Shawn Gregg , Kirk Hlavaty , Jeffrey Levine , Kenneth Lonczak , Craig McGarrah , Dominic Mongillo , Lisa O'Neill , Edward Pietraszkiewicz , Richard Salzillo , Heather 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。

5. 发明申请

US20050265844A1 Cooled rotor blade 有权
标题翻译：冷却转子叶片
公开(公告)号：US20050265844A1
公开(公告)日：2005-12-01
申请号：US10855188
申请日：2004-05-27
申请人： Jeffrey Levine , Edward Pietraszkiewicz , John Calderbank , Dominic Mongillo
发明人： Jeffrey Levine , Edward Pietraszkiewicz , John Calderbank , Dominic Mongillo
IPC分类号： B63H1/14 , F01D5/14 , F01D5/18 , F02C7/18
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。

6. 发明申请

US20050265842A1 Cooled rotor blade 有权
标题翻译：冷却转子叶片
公开(公告)号：US20050265842A1
公开(公告)日：2005-12-01
申请号：US10855183
申请日：2004-05-27
申请人： Dominic Mongillo , Shawn Gregg , Jeffrey Levine , Edward Pietraszkiewicz
发明人： Dominic Mongillo , Shawn Gregg , Jeffrey Levine , Edward Pietraszkiewicz
IPC分类号： F01D5/18 , F02C7/18 , B63H1/14
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。

7. 发明申请

US20070048134A1 Manufacturable and inspectable microcircuit cooling for blades 有权
标题翻译：用于刀片的可制造和可检查的微电路冷却
公开(公告)号：US20070048134A1
公开(公告)日：2007-03-01
申请号：US11217560
申请日：2005-08-31
申请人： Frank Cunha , Om Sharma , Edward Pietraszkiewicz
发明人： Frank Cunha , Om Sharma , Edward Pietraszkiewicz
IPC分类号： F01D5/18
CPC分类号： B23P15/04 , B22F2998/00 , F01D5/005 , F01D5/187 , F01D5/20 , F01D21/003 , F05D2230/211 , F05D2230/232 , F05D2260/203 , F05D2260/2212 , F05D2260/22141 , Y10T29/49336 , Y10T29/49341 , C22C47/16
摘要： A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a plurality of microcircuits having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, and forming at least one additional cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion. Thereafter, the first half is placed in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected. The first half and the second half are joined together to form the airfoil portion.
摘要翻译：一种用于制造涡轮发动机部件的方法包括以下步骤：形成涡轮发动机部件的翼型部分的第一半部分，并且在翼型部分的前半部分的暴露的内壁上形成多个具有至少一个通道的微电路。该方法还包括形成所述涡轮发动机部件的翼型部分的第二半部分，并且在翼型部分的第二半部的暴露的内壁上形成至少一个附加的冷却微型电路，其具有至少一个通道。此后，在形成冷却微电路并进行检查之后，将第一半与第二半对置。上半部和第二半部接合在一起形成翼型部。

8. 发明申请

US20070237638A1 Manufacturable and inspectable microcircuits 有权
标题翻译：可制造和可检查的微电路
公开(公告)号：US20070237638A1
公开(公告)日：2007-10-11
申请号：US11217703
申请日：2005-08-31
申请人： Om Sharma , Frank Cunha , Edward Pietraszkiewicz
发明人： Om Sharma , Frank Cunha , Edward Pietraszkiewicz
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , B23P15/04 , F01D5/005 , F01D5/187 , F01D21/003 , F05D2230/211 , F05D2230/232 , F05D2260/203 , F05D2260/2212 , F05D2260/22141 , Y10T29/49336 , Y10T29/49341
摘要： A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a first cooling microcircuit having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, forming a second cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion, and placing the first half in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected.
摘要翻译：一种用于制造涡轮发动机部件的方法包括以下步骤：形成涡轮发动机部件的翼型部分的第一半部分，并形成在翼型部分的前半部分的暴露内壁上具有至少一个通道的第一冷却微电路。该方法还包括形成所述涡轮发动机部件的翼型部分的第二半部分，形成第二冷却微电路，该第二冷却微型电路在翼型部分的第二半部的暴露的内壁上具有至少一个通道，在冷却微电路形成和检查后与下半年的关系。

9. 发明申请

US20070048128A1 Manufacturable and inspectable cooling microcircuits for blade-outer-air-seals 有权
标题翻译：用于叶片外部空气密封件的可制造和可检查的冷却微电路
公开(公告)号：US20070048128A1
公开(公告)日：2007-03-01
申请号：US11217702
申请日：2005-08-31
申请人： Frank Cunha , Om Sharma , Edward Pietraszkiewicz
发明人： Frank Cunha , Om Sharma , Edward Pietraszkiewicz
IPC分类号： F04D29/08
CPC分类号： B23P15/00 , F01D11/24 , F05D2230/211 , Y10T29/4932 , Y10T29/49341 , Y10T29/49988
摘要： A method for manufacturing a cooling microcircuit in a blade-outer-air-seal is provided. The method broadly comprises the steps of forming a first section of the blade-outer-air-seal having a first exposed internal wall, forming a second section of the blade-outer-air-seal having a second exposed internal wall, and forming at least one cooling microcircuit on at least one of the first and second exposed internal walls.
摘要翻译：提供了一种用于制造叶片 - 外部空气密封件中的冷却微型电路的方法。该方法广泛地包括以下步骤：形成具有第一暴露内壁的叶片 - 外部空气密封件的第一部分，形成具有第二暴露内壁的叶片 - 外部空气密封件的第二部分，并且形成在在第一和第二暴露的内壁中的至少一个上的至少一个冷却微电路。

10. 发明申请

US20060083613A1 Impingement cooling of large fillet of an airfoil 有权
标题翻译：机翼大圆角的冲击冷却
公开(公告)号：US20060083613A1
公开(公告)日：2006-04-20
申请号：US10967557
申请日：2004-10-18
申请人： Frank Cunha , Jason Albert , Edward Pietraszkiewicz
发明人： Frank Cunha , Jason Albert , Edward Pietraszkiewicz
IPC分类号： F01D5/18
CPC分类号： F01D5/145 , F01D5/081 , F01D5/143 , F01D5/187 , F05D2240/80 , F05D2260/201 , F05D2260/202
摘要： A gas turbine engine blade has a relatively large fillet to improve the characteristics of the air flow thereover. The fillet has a thin wall which, together with an impingement rib, defines a fillet cavity therebetween, and cooling air is provided to flow through impingement holes in the impingement rib and impinge on the rear surface of the fillet. The impingement holes are elongated in cross sectional shape with their elongations being orient in a direction generally transverse to a radial direction.
摘要翻译：燃气涡轮发动机叶片具有较大的圆角以改善其上的空气流的特性。圆角具有薄壁，其与冲击肋一起在其间限定圆角腔，并且提供冷却空气以流过冲击肋中的冲击孔并撞击圆角的后表面。冲击孔的横截面形状是细长的，它们的伸长方向在大致横向于径向的方向上定向。

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