公开(公告)号：US20150285096A1

公开(公告)日：2015-10-08

申请号：US14613093

申请日：2015-02-03

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Gina Cavallo

IPC: F01D25/12 ,  F01D9/02

CPC classification number: F01D25/12 ,  F01D5/188 ,  F01D5/189 ,  F01D9/02 ,  F01D9/041 ,  F05D2220/30 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2260/221 ,  Y02T50/676

Abstract: A turbine engine component includes an internal baffle spaced between first and second walls. Each wall may have a plurality of cooling holes in fluid communication with respective upstream and downstream cooling paths defined between the baffle and the respective walls. Cooling air first flows through an upstream end portion of the upstream cooling path, then through a downstream end portion where the air enters a bleed aperture in the baffle. From the bleed aperture, a portion of or all of the cooling air may enter an internal cavity defined by the baffle and, from there, flows through at least one hole that may be a plurality of impingement holes in the baffle, and into the downstream cooling passage where the portion or all of the remaining cooling air may exit the component through the cooling holes in the second wall.

Abstract translation: 涡轮发动机部件包括在第一和第二壁之间间隔开的内部挡板。 每个壁可以具有与限定在挡板和相应的壁之间的相应的上游和下游冷却通道流体连通的多个冷却孔。 冷却空气首先流过上游冷却通道的上游端部分，然后通过下游端部分，空气进入挡板中的放气孔。 从排出孔中，冷却空气的一部分或全部可以进入由挡板限定的内部空腔，并且从那里流过至少一个孔，该孔可以是挡板中的多个冲击孔，并且流入下游 冷却通道，其中剩余冷却空气的一部分或全部可以通过第二壁中的冷却孔离开部件。

公开(公告)号：US09115590B2

公开(公告)日：2015-08-25

申请号：US13627072

申请日：2012-09-26

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Mark F. Zelesky ,  Edwin Otero

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that extends between a leading edge, a trailing edge, a pressure side wall and a suction side wall. A cooling circuit is disposed inside of the airfoil. The cooling circuit includes a first core cavity that radially extends inside of the airfoil. A first axial skin core is in fluid communication with the first core cavity at a first location of the first axial skin core and a second core cavity is in fluid communication with the first axial skin core at a second location of the first axial skin core.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘，后缘，压力侧壁和吸力侧壁之间延伸的翼型件。 冷却回路设置在翼型的内部。 冷却回路包括在翼型件内径向延伸的第一芯腔。 第一轴向皮肤芯在第一轴向皮肤芯的第一位置处与第一芯腔流体连通，并且第二芯腔在第一轴向皮肤芯的第二位置处与第一轴向皮肤芯流体连通。

公开(公告)号：US20140314581A1

公开(公告)日：2014-10-23

申请号：US14250692

申请日：2014-04-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John McBrien ,  Lea Kennard Castle ,  Brandon W. Spangler

IPC: F01D5/28 ,  B22F3/24 ,  B22F5/10 ,  F01D5/18

CPC classification number: F01D5/28 ,  B22C7/02 ,  B22C9/02 ,  B22C9/043 ,  B22C9/061 ,  B22C9/10 ,  B22C9/101 ,  B22C9/108 ,  B22C9/22 ,  B22C9/24 ,  B22D23/06 ,  B22D25/02 ,  B22D27/04 ,  B22D27/045 ,  B22F3/1055 ,  B22F3/11 ,  B22F3/24 ,  B22F5/04 ,  B22F2003/248 ,  B22F2998/00 ,  B22F2998/10 ,  B23K15/0006 ,  B23K15/0086 ,  B23K26/342 ,  B32B1/08 ,  B32B3/08 ,  B32B3/26 ,  B32B5/16 ,  B32B9/005 ,  B32B2250/03 ,  B32B2264/105 ,  B32B2603/00 ,  B33Y10/00 ,  B33Y80/00 ,  C30B11/00 ,  C30B29/52 ,  F01D5/147 ,  F01D5/18 ,  F01D5/187 ,  F01D5/282 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2300/175 ,  F05D2300/211 ,  F05D2300/607 ,  F23R3/28 ,  Y02P10/292 ,  Y02P10/295 ,  B22F2003/242 ,  C30B11/14

Abstract: A method of forming a metal single crystal turbine component with internal passageways includes forming a polycrystalline turbine blade with internal passageways by additive manufacturing and filling the passageways with a core ceramic slurry. The ceramic slurry is then treated to harden the core and the turbine component is encased in a ceramic shell which is treated to form a ceramic mold. The turbine component in the mold is then melted and directionally solidified in the form of a single crystal. The outer shell and inner ceramic core are then removed to form a finished single crystal turbine component with internal passageways.

Abstract translation: 形成具有内部通道的金属单晶涡轮机部件的方法包括通过添加剂制造形成具有内部通道的多晶涡轮机叶片，并用核心陶瓷浆料填充通道。 然后处理陶瓷浆料以硬化芯部，并且将涡轮机部件封装在经过处理以形成陶瓷模具的陶瓷壳体中。 然后将模具中的涡轮机部件以单晶的形式熔化并定向凝固。 然后去除外壳和内陶瓷芯以形成具有内部通道的成品单晶涡轮机部件。

公开(公告)号：US20140127013A1

公开(公告)日：2014-05-08

申请号：US13627072

申请日：2012-09-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Mark F. Zelesky ,  Edwin Otero

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that extends between a leading edge, a trailing edge, a pressure side wall and a suction side wall. A cooling circuit is disposed inside of the airfoil. The cooling circuit includes a first core cavity that radially extends inside of the airfoil. A first axial skin core is in fluid communication with the first core cavity at a first location of the first axial skin core and a second core cavity is in fluid communication with the first axial skin core at a second location of the first axial skin core.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘，后缘，压力侧壁和吸力侧壁之间延伸的翼型件。 冷却回路设置在翼型的内部。 冷却回路包括在翼型件内径向延伸的第一芯腔。 第一轴向皮肤芯在第一轴向皮肤芯的第一位置处与第一芯腔流体连通，并且第二芯腔在第一轴向皮肤芯的第二位置处与第一轴向皮肤芯流体连通。