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1. 发明授权

US07150601B2 Turbine airfoil cooling passageway 有权
标题翻译：涡轮翼型冷却通道
公开(公告)号：US07150601B2
公开(公告)日：2006-12-19
申请号：US11021152
申请日：2004-12-23
申请人： Edward F. Pietraszkiewicz , John C. Calderbank , Andrew D. Milliken , Jeffrey R. Levine
发明人： Edward F. Pietraszkiewicz , John C. Calderbank , Andrew D. Milliken , Jeffrey R. Levine
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。

2. 发明授权

US08439629B2 Blade outer air seal 有权
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
IPC分类号： F01D1/04 , F01D9/06 , F01D25/14
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.

3. 发明申请

US20090067994A1 Blade outer air seal 有权
标题翻译：刀片外部空气密封
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。

4. 发明授权

US08123466B2 Blade outer air seal 有权
标题翻译：刀片外部空气密封
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。

5. 发明申请

US20080211192A1 Blade outer air seal 有权
标题翻译：刀片外部空气密封
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。

6. 发明授权

US5413458A Turbine vane with a platform cavity having a double feed for cooling fluid 失效
标题翻译：具有平台腔的涡轮叶片具有用于冷却流体的双进料
公开(公告)号：US5413458A
公开(公告)日：1995-05-09
申请号：US219316
申请日：1994-03-29
申请人： John C. Calderbank
发明人： John C. Calderbank
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D5/187 , F05D2240/10 , F05D2240/81
摘要： A turbine vane for a gas turbine engine includes a platform with a cavity along the trailing edge having a double feed arrangement for injecting cooling fluid into the cavity. Various construction details are developed that provide a cavity having improved heat transfer due to the elimination of dead zones. In a particular embodiment, a turbine vane includes a platform cavity having a first inlet located on the pressure side of the platform and forward of an attachment rail and a second inlet located on the suction side and forward of the attachment rail. The cavity includes a plurality of trip strips and a plurality of film cooling passages. The trip strips extend from the corners of the cavity and are angled to encourage cooling fluid to flow into the corners. The film cooling passages direct the exiting cooling fluid to form a film of cooling fluid over the platform flow surface.
摘要翻译：用于燃气涡轮发动机的涡轮叶片包括具有沿着后缘的空腔的平台，具有用于将冷却流体注入空腔的双重进给装置。开发了各种构造细节，其提供了由于消除死区而具有改进的热传递的空腔。在特定实施例中，涡轮叶片包括平台腔，该平台腔具有位于平台的压力侧上的第一入口和连接轨道的前部，以及位于吸入侧和连接轨道前方的第二入口。空腔包括多个跳闸条和多个膜冷却通道。脱扣条从腔体的角部延伸并且成角度以促使冷却流体流入拐角。薄膜冷却通道引导排出的冷却流体在平台流动表面上形成冷却流体膜。

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