公开(公告)号：US20160298464A1

公开(公告)日：2016-10-13

申请号：US14685410

申请日：2015-04-13

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Gina Cavallo

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

Abstract: An airfoil having a cooling hole pattern is disclosed. The cooling hole pattern may be an offset herringbone pattern. For instance, the airfoil may have rows of cooling holes arranged in filmrows, each filmrow divided into groups of cooling holes. A first group may be oriented to direct cooling air generally radially outward over a surface of the airfoil and a second group may be oriented to direct cooling air generally radially inward over a surface of the airfoil. Between the first group and the second group of cooling holes in each filmrow, a transition region exists. The adjacent filmrows are staggered to enhance the effectiveness of the convective cooling proximate to the transition regions by causing each filmrow to direct cooling air over the transition region of an adjacent filmrow.

Abstract translation: 公开了具有冷却孔图案的翼型件。 冷却孔图案可以是偏移的人字形图案。 例如，翼型件可以具有排列在薄膜中的一排冷却孔，每个薄膜分成一组冷却孔。 第一组可以被定向成将冷却空气大致径向向外引导到翼型件的表面上，并且第二组可以被定向成将冷却空气大致径向向内引导到翼型件的表面上。 在每个成膜中的第一组和第二组冷却孔之间存在过渡区。 相邻的薄膜交错，以通过使每个薄膜引导冷却空气在相邻薄膜的过渡区域上来提高靠近过渡区域的对流冷却的有效性。

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。