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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：US08439629B2
公开(公告)日：2013-05-14
申请号：US11712812
申请日：2007-03-01
申请人： Edward F. Pietraszkiewicz , John C. Calderbank , Joseph A. Peto , Lisa P. O'Neill , Michael J. Bruskotter
发明人： Edward F. Pietraszkiewicz , John C. Calderbank , Joseph A. Peto , Lisa P. O'Neill , Michael J. Bruskotter
CPC分类号： F01D11/08 , F01D9/04 , F01D25/246 , F02C7/18 , F05D2230/80 , F05D2230/90 , F05D2240/11 , F05D2260/201 , F05D2260/95 , F05D2300/611
摘要： A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating forward and aft cavity portions.
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公开(公告)号：US08123466B2
公开(公告)日：2012-02-28
申请号：US11712863
申请日：2007-03-01
申请人： Edward F. Pietraszkiewicz , John C. Calderbank , Joseph A. Peto , Lisa P. O'Neill , Michael J. Bruskotter
发明人： Edward F. Pietraszkiewicz , John C. Calderbank , Joseph A. Peto , Lisa P. O'Neill , Michael J. Bruskotter
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F01D9/04 , F01D25/246 , F02C7/18 , F05D2230/80 , F05D2230/90 , F05D2240/11 , F05D2260/201 , F05D2260/95 , F05D2300/611
摘要： A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating circumferentially and fore-aft offset cavity portions.
摘要翻译： 涡轮发动机叶片外部空气密封段具有具有基部的主体。 基部具有横向凹入的ID面，前端，后端以及第一和第二圆周边缘。 主体至少有一个安装钩。 至少一个盖板固定到主体以限定至少一个空腔。 盖板具有多个供给孔。 多个出口孔穿过基座部分延伸到ID面。 底座部分和盖板中的至少一个包括突出部分，该突出部分突出到腔体中以形成沿周向和前后偏移空腔部分分开的部分限制。
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公开(公告)号：US20080211192A1
公开(公告)日：2008-09-04
申请号：US11712863
申请日：2007-03-01
申请人： Edward F. Pietraszkiewicz , John C. Calderbank , Joseph A. Peto , Lisa P. O'Neill , Michael J. Bruskotter
发明人： Edward F. Pietraszkiewicz , John C. Calderbank , Joseph A. Peto , Lisa P. O'Neill , Michael J. Bruskotter
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F01D9/04 , F01D25/246 , F02C7/18 , F05D2230/80 , F05D2230/90 , F05D2240/11 , F05D2260/201 , F05D2260/95 , F05D2300/611
摘要： A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating circumferentially and fore-aft offset cavity portions.
摘要翻译： 涡轮发动机叶片外部空气密封段具有具有基部的主体。 基部具有横向凹入的ID面，前端，后端以及第一和第二圆周边缘。 主体至少有一个安装钩。 至少一个盖板固定到主体以限定至少一个空腔。 盖板具有多个供给孔。 多个出口孔穿过基座部分延伸到ID面。 底座部分和盖板中的至少一个包括突出部分，该突出部分突出到腔体中以形成沿周向和前后偏移空腔部分分开的部分限制。
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公开(公告)号：US20090067994A1
公开(公告)日：2009-03-12
申请号：US11712812
申请日：2007-03-01
申请人： Edward F. Pietraszkiewicz , John C. Calderbank , Joseph A. Peto , Lisa P. O'Neill , Michael J. Bruskotter
发明人： Edward F. Pietraszkiewicz , John C. Calderbank , Joseph A. Peto , Lisa P. O'Neill , Michael J. Bruskotter
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F01D9/04 , F01D25/246 , F02C7/18 , F05D2230/80 , F05D2230/90 , F05D2240/11 , F05D2260/201 , F05D2260/95 , F05D2300/611
摘要： A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating forward and aft cavity portions.
摘要翻译： 涡轮发动机叶片外部空气密封段具有具有基部的主体。 基部具有横向凹入的ID面，前端，后端以及第一和第二圆周边缘。 主体至少有一个安装钩。 至少一个盖板固定到主体以限定至少一个空腔。 盖板具有多个供给孔。 多个出口孔穿过基座部分延伸到ID面。 基部和盖板中的至少一个包括突出部分，突出到空腔中以形成分离前后空腔部分的部分限制。
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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：US09388700B2
公开(公告)日：2016-07-12
申请号：US13421894
申请日：2012-03-16
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/12 , F05D2250/185 , F05D2260/205 , F05D2260/2212 , F05D2260/22141
摘要： An airfoil for a gas turbine engine according to one exemplary embodiment includes an airfoil body that extends between a leading edge and a trailing edge. A cooling circuit can be defined within the airfoil body. The cooling circuit can include at least one trip strip disposed within a cavity of the cooling circuit between a leading edge inner wall and a first rib. The at least one trip strip can include an increasing height in a direction from the first rib toward the leading edge inner wall.
摘要翻译： 根据一个示例性实施例的用于燃气涡轮发动机的翼型件包括在前缘和后缘之间延伸的翼型体。 可以在翼型体内限定冷却回路。 冷却回路可以包括设置在前缘内壁和第一肋之间的冷却回路的空腔内的至少一个跳闸条。 至少一个跳闸带可以包括在从第一肋朝向前缘内壁的方向上的增加的高度。
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公开(公告)号：US09145780B2
公开(公告)日：2015-09-29
申请号：US13326720
申请日：2011-12-15
CPC分类号： F01D5/186 , F01D9/041 , F05D2240/12 , F05D2250/185 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes an airfoil body and a cooling circuit defined within the airfoil body. The cooling circuit includes at least a first cavity in fluid communication with a second cavity. A first portion of the first cavity extends between an outer diameter and an inner diameter of the airfoil body and a second portion of the first cavity extends across a space between a leading edge and a trailing edge of the airfoil body.
摘要翻译： 用于燃气涡轮发动机的翼型件包括翼型体和限定在翼型体内的冷却回路。 冷却回路包括至少与第二腔流体连通的第一空腔。 第一空腔的第一部分在翼型件主体的外径和内径之间延伸，并且第一腔的第二部分延伸穿过机翼本体的前缘和后缘之间的空间。
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公开(公告)号：US09024226B2
公开(公告)日：2015-05-05
申请号：US13544031
申请日：2012-07-09
申请人： Glenn Levasseur , Edward F. Pietraszkiewicz , Mark F. Zelesky , Dominic J. Mongillo, Jr. , Kevin J. Klinefelter , Stephen D. Doll , Markus W. Fritch
发明人： Glenn Levasseur , Edward F. Pietraszkiewicz , Mark F. Zelesky , Dominic J. Mongillo, Jr. , Kevin J. Klinefelter , Stephen D. Doll , Markus W. Fritch
CPC分类号： B23H9/10 , B23H1/00 , B23H7/26 , B23H9/14 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/676
摘要： A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges.
摘要翻译： 用于形成从壁的第一表面上的入口延伸到壁的第二表面上的出口的冷却孔的方法包括：通过放电加工形成冷却孔的扩散部分和出口上的后缘， 并在扩散段中形成纵向凸起。 计量部分从壁的第一表面上的入口延伸到壁的第二表面。 扩散部分从出口延伸到位于入口和出口之间的计量部分的一端。 出口在后缘处基本上是线性的或凸起的，并且叶片由纵向脊部分开。
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