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    Gas turbine engine turbine blade tip cooling
    2.
    发明授权
    Gas turbine engine turbine blade tip cooling 有权
    燃气涡轮发动机涡轮叶片尖端冷却

    公开(公告)号：US09453419B2

    公开(公告)日：2016-09-27

    申请号：US13729110

    申请日：2012-12-28

    Applicant: United Technologies Corporation

    Inventor： James T. Auxier ,  Jason L. O'Hearn ,  Thomas N. Slavens ,  Yafet Girma

    IPC: F01D5/18 ,  F01D5/20 ,  F01D11/08

    CPC classification number: F01D5/186 ,  F01D5/20 ,  F01D11/08 ,  F05D2240/307 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘连接的压力和吸力壁，以提供具有沿径向方向延伸到尖端的外表面的翼型件。 尖端处的弧形线从前缘延伸到后缘。 压力和吸力侧搁板分别设置在压力侧和吸力侧壁的外倾线的相对侧的外表面上。 高原是为压力和吸力侧货架感到自豪和分离。 平台沿着弧形线布置并延伸到前缘。

    GAS TURBINE ENGINE TURBINE BLADE TIP COOLING
    3.
    发明申请
    GAS TURBINE ENGINE TURBINE BLADE TIP COOLING 有权
    气体涡轮发动机涡轮叶片冷却

    公开(公告)号：US20140212298A1

    公开(公告)日：2014-07-31

    申请号：US13729110

    申请日：2012-12-28

    Applicant: United Technologies Corporation

    Inventor： James T. Auxier ,  Jason L. O'Hearn ,  Thomas N. Slavens ,  Yafet Girma

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F01D5/20 ,  F01D11/08 ,  F05D2240/307 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘连接的压力和吸力壁，以提供具有沿径向方向延伸到尖端的外表面的翼型件。 尖端处的弧形线从前缘延伸到后缘。 压力和吸力侧搁板分别设置在压力侧和吸力侧壁的外倾线的相对侧的外表面上。 高原是为压力和吸力侧货架感到自豪和分离。 平台沿着弧形线布置并延伸到前缘。

    STAGGERED CROSSOVERS FOR AIRFOILS
    5.
    发明申请
    STAGGERED CROSSOVERS FOR AIRFOILS 审中-公开

    公开(公告)号：US20160160657A1

    公开(公告)日：2016-06-09

    申请号：US14820786

    申请日：2015-08-07

    Applicant: United Technologies Corporation

    Inventor： Scott D. Lewis ,  Yafet Girma ,  Christopher Corcoran

    IPC: F01D5/18 ,  B22C9/10 ,  F01D25/12 ,  F01D5/14 ,  F01D9/04

    CPC classification number: F01D5/187 ,  B22C9/10 ,  F01D5/147 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2250/314 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

    Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The plurality of crossover passages are distributed in the spanwise direction and arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity. The plurality of crossover passages include a first set of crossover passages and a second set of crossover passages positioned on opposite sides of the first reference plane. The passage axis of each of the first set of crossover passages is arranged at a first vertical angle relative to a spanwise axis, and the passage axis of each of the second set of crossover passages is arranged at a second, different vertical angle relative to the spanwise axis. A casting core for an airfoil is also disclosed.

    Abstract translation: 根据本公开的示例性方面的翼型件尤其包括具有外壁和内壁的翼型部分。 内壁限定在翼展方向上延伸并穿过内壁的厚度的第一参考平面。 第一腔和第二腔由内壁分开。 内壁内的多个交叉通道将第一腔连接到第二腔。 多个交叉通道中的每一个限定通道轴线。 多个交叉通道沿翼展方向分布，并且布置成使得多个冷却通道中的每一个的通道轴线与第二腔体的表面相交。 多个交叉通道包括第一组交叉通道和位于第一参考平面的相对侧上的第二组交叉通道。 第一组交叉通道中的每一个的通道轴线相对于翼展方向轴线以第一垂直角度布置，并且第二组交叉通道中的每一个的通道轴线相对于第二组交叉通道布置成第二不同的垂直角度 翼展轴。 还公开了一种用于翼型的铸芯。

    Staggered crossovers for airfoils
    7.
    发明授权
    Staggered crossovers for airfoils 有权

    公开(公告)号：US10145246B2

    公开(公告)日：2018-12-04

    申请号：US14820786

    申请日：2015-08-07

    Applicant: United Technologies Corporation

    Inventor： Scott D. Lewis ,  Yafet Girma ,  Christopher Corcoran

    IPC: F01D5/18 ,  F01D9/04 ,  F01D5/14 ,  F01D25/12 ,  B22C9/10

    Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The plurality of crossover passages are distributed in the spanwise direction and arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity. The plurality of crossover passages include a first set of crossover passages and a second set of crossover passages positioned on opposite sides of the first reference plane. The passage axis of each of the first set of crossover passages is arranged at a first vertical angle relative to a spanwise axis, and the passage axis of each of the second set of crossover passages is arranged at a second, different vertical angle relative to the spanwise axis. A casting core for an airfoil is also disclosed.

    Reversible blade damper
    8.
    发明授权
    Reversible blade damper 有权
    可逆叶片阻尼器

    公开(公告)号：US09151165B2

    公开(公告)日：2015-10-06

    申请号：US13657190

    申请日：2012-10-22

    Applicant: United Technologies Corporation

    Inventor： Brandon S. Donnell ,  Yafet Girma ,  Gina C. O'Dell

    IPC: F01D5/26 ,  F01D5/22 ,  F01D11/00

    CPC classification number: F01D5/22 ,  F01D5/26 ,  F01D11/005 ,  F01D11/006 ,  F01D11/008 ,  F05D2260/36

    Abstract: A damper body extends between an axial first end, an opposing axial second end, a first lateral side, and an opposing second lateral side. A first pair of lugs are disposed at the first axial end and a second pair of lugs are disposed at the second axial end. In the first lug pair, a lug has an axially outermost foot which extends laterally beyond a lateral wall. The second lug pair has a lug with an axial outermost point with a foot extending laterally beyond a lateral wall. The foot on the first axial end and the foot on the second axial end are on opposed lateral sides.

    Abstract translation: 阻尼体在轴向第一端，相对的轴向第二端，第一侧面和相对的第二侧面之间延伸。 第一对凸耳设置在第一轴向端部，第二对凸耳设置在第二轴向端部处。 在第一凸耳对中，凸耳具有横向延伸超过侧壁的轴向最外侧的脚。 第二凸耳对具有具有轴向最外点的凸耳，其具有横向延伸超过侧壁的脚。 第一轴向端部的脚和第二轴向端部上的脚在相对的侧面上。

    Reversible Blade Damper
    9.
    发明申请
    Reversible Blade Damper 有权
    可逆式叶片阻尼器

    公开(公告)号：US20140112786A1

    公开(公告)日：2014-04-24

    申请号：US13657190

    申请日：2012-10-22

    Applicant: United Technologies Corporation

    Inventor： Brandon S. Donnell ,  Yafet Girma ,  Gina C. O'Dell

    IPC: F01D5/22 ,  F01D11/00

    CPC classification number: F01D5/22 ,  F01D5/26 ,  F01D11/005 ,  F01D11/006 ,  F01D11/008 ,  F05D2260/36

    Abstract: A damper body extends between an axial first end, an opposing axial second end, a first lateral side, and an opposing second lateral side. A first pair of lugs are disposed at the first axial end and a second pair of lugs are disposed at the second axial end. In the first lug pair, a lug has an axially outermost foot which extends laterally beyond a lateral wall. The second lug pair has a lug with an axial outermost point with a foot extending laterally beyond a lateral wall. The foot on the first axial end and the foot on the second axial end are on opposed lateral sides.

    Abstract translation: 阻尼体在轴向第一端，相对的轴向第二端，第一侧面和相对的第二侧面之间延伸。 第一对凸耳设置在第一轴向端部，第二对凸耳设置在第二轴向端部处。 在第一凸耳对中，凸耳具有横向延伸超过侧壁的轴向最外侧的脚。 第二凸耳对具有具有轴向最外点的凸耳，其具有横向延伸超过侧壁的脚。 第一轴向端部的脚和第二轴向端部上的脚在相对的侧面上。

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