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公开(公告)号：US07150601B2
公开(公告)日：2006-12-19
申请号：US11021152
申请日：2004-12-23
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/18 , F01D5/187 , F01D5/188 , F05D2230/80 , F05D2240/12
摘要： An internally cooled gas turbine engine turbine vane has an outboard shroud and an airfoil extending from an outboard end at the shroud to an inboard end. A cooling passageway has an inlet in the shroud, a first turn at least partially within the airfoil, a first leg extending from the inlet inboard through the airfoil to the first turn, and a second leg extending from the first turn. A dividing wall is in the passageway and has an upstream end in an outboard half of a span of the airfoil and has a plurality of vents. The vane may be formed as a reengineering of a baseline configuration lacking the dividing wall.
摘要翻译： 内部冷却的燃气涡轮发动机涡轮叶片具有外侧护罩和从护罩的外侧端部延伸到内侧端部的翼型件。 冷却通道在护罩中具有入口，至少部分地在翼型内的第一匝，从内侧的入口穿过翼型件延伸到第一匝的第一腿部，以及从第一匝延伸的第二腿部。 分隔壁在通道中，并且在翼型的跨度的外侧半部中具有上游端，并且具有多个通风口。 叶片可以形成为缺少分隔壁的基线构型的再造。
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公开(公告)号：US20140219813A1
公开(公告)日：2014-08-07
申请号：US13618178
申请日：2012-09-14
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
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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。
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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。
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公开(公告)号：US20070297917A1
公开(公告)日：2007-12-27
申请号：US11473894
申请日：2006-06-22
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/12 , F05D2240/121 , F05D2240/303 , F05D2250/70 , F05D2260/2212 , F05D2260/22141
摘要： A turbine engine component has an airfoil portion having a leading edge, a suction side, and a pressure side and a radial flow leading edge cavity through which a cooling fluid flows for cooling the leading edge. The turbine engine component further has a first set of trip strips and a second set of trip strips which meet at the leading edge nose portion of the leading edge cavity to form a plurality of chevron shaped trip strips and for generating a vortex in the leading edge cavity which impinges on the nose portion of the leading edge cavity and enhances convective heat transfer.
摘要翻译： 涡轮发动机部件具有翼型部分，其具有前缘，吸力侧以及冷却流体流过的用于冷却前缘的压力侧和径向流前缘腔。 涡轮发动机部件还具有第一组跳闸带和第二组跳闸条，其在前缘腔的前缘鼻部处相交，以形成多个人字形的跳闸带，并且用于在前缘中产生涡流 撞击在前缘腔的鼻部上并增强对流热传递的空腔。
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公开(公告)号：US09157329B2
公开(公告)日：2015-10-13
申请号：US13591773
申请日：2012-08-22
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。
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公开(公告)号：US20140056717A1
公开(公告)日：2014-02-27
申请号：US13591773
申请日：2012-08-22
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。
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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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公开(公告)号：US20070297916A1
公开(公告)日：2007-12-27
申请号：US11473893
申请日：2006-06-22
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/12 , F05D2240/121 , F05D2240/303 , F05D2260/2212 , F05D2260/22141
摘要： A turbine engine component has an airfoil portion having a leading edge, a suction side, and a pressure side and a radial flow leading edge cavity through which a cooling fluid flows for cooling the leading edge. The turbine engine component further has a staggered arrangement of trip strips for generating a vortex in the leading edge cavity which impinges on a nose portion of the leading edge cavity.
摘要翻译： 涡轮发动机部件具有翼型部分，其具有前缘，吸力侧以及冷却流体流过的用于冷却前缘的压力侧和径向流前缘腔。 涡轮发动机部件还具有交错排列的交错排列，用于在前缘腔中产生涡流，撞击前缘腔的鼻部。
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公开(公告)号：US09145775B2
公开(公告)日：2015-09-29
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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