专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US07478994B2 Airfoil with supplemental cooling channel adjacent leading edge 有权
标题翻译：机翼与辅助冷却通道相邻的前缘
公开(公告)号：US07478994B2
公开(公告)日：2009-01-20
申请号：US10996539
申请日：2004-11-23
申请人： Frank J. Cunha , Edward F. Pietraszkiewicz , David M. Kontrovitz , Jeffrey R. Levine , Young Chon , Dominic Mongillo , Bret Teller
发明人： Frank J. Cunha , Edward F. Pietraszkiewicz , David M. Kontrovitz , Jeffrey R. Levine , Young Chon , Dominic Mongillo , Bret Teller
IPC分类号： F01D5/20
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.
摘要翻译：在一个公开的实施例中，翼型件具有形成在前缘的薄膜冷却孔。补充膜冷却通道位于前缘附近，但是从前缘向后缘隔开。补充膜冷却通道将膜冷却空气引导到吸力壁上。补充膜冷却通道空气通常指向吸入壁上的位置，这在过去引起了一些挑战。在公开的实施例中，翼型件设置有热障涂层，并且辅助膜冷却空气保护该热障涂层。

2. 发明授权

US07131818B2 Airfoil with three-pass serpentine cooling channel and microcircuit 有权
公开(公告)号：US07131818B2
公开(公告)日：2006-11-07
申请号：US10979597
申请日：2004-11-02
申请人： Frank J. Cunha , Bret Teller , Young Chon , Dominic Mongillo , Edward F. Pietraszkiewicz
发明人： Frank J. Cunha , Bret Teller , Young Chon , Dominic Mongillo , Edward F. Pietraszkiewicz
IPC分类号： F01D5/16
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.

3. 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。

4. 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.

5. 发明申请

US20070224033A1 Fanned trailing edge teardrop array 有权
标题翻译：扇形后缘泪珠阵列
公开(公告)号：US20070224033A1
公开(公告)日：2007-09-27
申请号：US11232701
申请日：2005-09-22
申请人： Dominic Mongillo , Young Chon , Raymond Kulak
发明人： Dominic Mongillo , Young Chon , Raymond Kulak
IPC分类号： F03B11/00
CPC分类号： F01D5/187 , B22C9/10 , F05D2240/122 , F05D2240/304 , F05D2250/18 , F05D2250/311 , F05D2250/71 , F05D2260/202 , F05D2260/22141
摘要： A component for use in a gas turbine engine is provided. The component has an airfoil portion with a plurality of internal cooling passages and a non-linear trailing edge. The component further has a non-linear array of teardrop shaped assemblies which form a plurality of injection slots for injecting a coolant fluid into a fluid passing over the airfoil portion. The teardrop shaped assemblies are designed to maximize thermal performance of the component by reducing a relative diffusion angle between the injected coolant flow and the streamline direction of the fluid passing over the airfoil portion.
摘要翻译：提供了一种用于燃气涡轮发动机的部件。该部件具有具有多个内部冷却通道和非线性后缘的翼型部分。该组件还具有非线性阵列的泪珠形组件，其形成多个注射槽，用于将冷却剂流体喷射到通过翼型部分的流体中。泪滴形组件被设计成通过减少喷射的冷却剂流与通过翼型部分的流体的流线方向之间的相对扩散角来最大化部件的热性能。

6. 发明申请

US20050191167A1 Fanned trailing edge teardrop array 有权
标题翻译：扇形后缘泪珠阵列
公开(公告)号：US20050191167A1
公开(公告)日：2005-09-01
申请号：US10754265
申请日：2004-01-09
申请人： Dominic Mongillo , Young Chon , Raymond Kulak , Eugene Kulak
发明人： Dominic Mongillo , Young Chon , Raymond Kulak , Eugene Kulak
IPC分类号： F01D9/02 , F01D5/08 , F01D5/14 , F01D5/18 , F02C7/18 , F04D29/38
CPC分类号： F01D5/187 , B22C9/10 , F05D2240/122 , F05D2240/304 , F05D2250/18 , F05D2250/311 , F05D2250/71 , F05D2260/202 , F05D2260/22141
摘要： A component for use in a gas turbine engine is provided. The component has an airfoil portion with a plurality of internal cooling passages and a non-linear trailing edge. The component further has a non-linear array of teardrop shaped assemblies which form a plurality of injection slots for injecting a coolant fluid into a fluid passing over the airfoil portion. The teardrop shaped assemblies are designed to maximize thermal performance of the component by reducing a relative diffusion angle between the injected coolant flow and the streamline direction of the fluid passing over the airfoil portion.
摘要翻译：提供了一种用于燃气涡轮发动机的部件。该部件具有具有多个内部冷却通道和非线性后缘的翼型部分。该组件还具有非线性阵列的泪珠形组件，其形成多个注射槽，用于将冷却剂流体注入通过翼型部分的流体中。泪滴形组件被设计成通过减少喷射的冷却剂流与通过翼型部分的流体的流线方向之间的相对扩散角来最大化部件的热性能。

7. 发明申请

US20050106007A1 Spanwisely variable density pedestal array 有权
公开(公告)号：US20050106007A1
公开(公告)日：2005-05-19
申请号：US10717806
申请日：2003-11-19
申请人： Dominic Mongillo , Young Chon
发明人： Dominic Mongillo , Young Chon
IPC分类号： F01D9/02 , F01D5/18 , F02C7/18 , F01D5/14
CPC分类号： F01D5/187 , F05D2260/2212
摘要： A turbine engine component, such as a blade or vane, has a system for cooling a trailing edge portion thereof. The system includes a plurality of rows of pedestals which vary in density along a span of the component. In a preferred embodiment of the present invention, the number of rows of pedestals increases as one moves along the span of the component from an inner diameter region to an outer diameter region.

8. 发明申请

US20050265836A1 Cooled rotor blade and method for cooling a rotor blade 有权
标题翻译：冷却转子叶片和冷却转子叶片的方法
公开(公告)号：US20050265836A1
公开(公告)日：2005-12-01
申请号：US10855010
申请日：2004-05-27
申请人： Dominic Mongillo , Shawn Gregg
发明人： Dominic Mongillo , Shawn Gregg
IPC分类号： F01D5/18 , F02C7/18 , B63H1/00
CPC分类号： F01D5/187 , F05D2260/221 , F05D2260/22141
摘要： According to the present invention, a rotor blade and a method for cooling a rotor blade is provided. The rotor blade includes a root and a hollow airfoil having a cavity defined by 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 serpentine passage having at least three radial segments connected to one another, an axially extending passage disposed between the tip and the serpentine passage, at least one aperture extending between the last radial segment and the axially extending passage, and one or more sink apertures disposed within one of the suction side wall or the pressure side wall of the last radial segment of the serpentine passage. At least one conduit is disposed within the root. The conduit is operable to permit airflow through the root and into the internal passage configuration.
摘要翻译：根据本发明，提供了一种转子叶片和用于冷却转子叶片的方法。转子叶片包括根部和具有由吸力侧壁，压力侧壁，前缘，后缘，基部和尖端限定的空腔的中空翼型件。内部通道构造设置在空腔内。该构造包括具有至少三个彼此连接的径向段的蛇形通道，设置在尖端和蛇形通道之间的轴向延伸的通道，在最后的径向段和轴向延伸通道之间延伸的至少一个孔，以及一个或多个设置在蛇形通道的最后一个径向段的吸入侧壁或压力侧壁之一内的吸入孔。至少一根导管设置在根部内。管道可操作以允许气流通过根部并进入内部通道构造。

9. 发明申请

US20050135933A1 COOLED ROTOR BLADE WITH VIBRATION DAMPING DEVICE 有权
标题翻译：具有振动阻尼装置的冷却转子叶片
公开(公告)号：US20050135933A1
公开(公告)日：2005-06-23
申请号：US10741106
申请日：2003-12-19
申请人： Shawn Gregg , Dominic Mongillo
发明人： Shawn Gregg , Dominic Mongillo
IPC分类号： F01D5/16 , F01D5/18 , F03D1/00
CPC分类号： F01D5/187 , F01D5/16 , F01D5/189 , F01D5/26 , F05D2240/126 , F05D2240/307 , F05D2260/22141 , Y10S416/50
摘要： A rotor blade for a rotor assembly is provided that includes a root, an airfoil, and a damper. The airfoil includes a base, a tip, a pressure side wall, a suction side wall, and a cavity disposed therebetween. The cavity extends substantially between the base and the tip, and includes a first cavity portion, a second cavity portion, and a channel disposed between the first cavity portion and the second cavity portion. A plurality of first pedestals are disposed within the first cavity portion adjacent the channel, and a plurality of second pedestals are disposed within the second cavity portion adjacent the channel. The damper is selectively received within the channel.
摘要翻译：提供了一种用于转子组件的转子叶片，其包括根部，翼型件和阻尼器。翼型件包括基座，尖端，压力侧壁，吸力侧壁和设置在其间的空腔。空腔基本上在基部和尖端之间延伸，并且包括第一空腔部分，第二空腔部分和设置在第一空腔部分和第二空腔部分之间的通道。多个第一基座设置在与通道相邻的第一空腔部分内，并且多个第二基座设置在邻近通道的第二空腔部分内。阻尼器选择性地接收在通道内。

10. 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。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式