公开(公告)号：WO2014164888A1

公开(公告)日：2014-10-09

申请号：PCT/US2014/023709

申请日：2014-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： CORCORAN, Christopher ,  GHIGLIOTTY, Jaime, G. ,  PEREZ, Rafael, A. ,  PIETRASZKIEWICZ, Edward, F.

IPC: F01D5/18 ,  F02C7/12

CPC classification number: F01D5/186 ,  F01D5/187 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2260/202 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A rotor blade comprises a root section, an airfoil section, a leading edge cooling cavity, an intermediate cooling cavity, and a trailing edge cooling cavity. The leading edge, intermediate, and trailing edge cooling cavities each extend spanwise through the airfoil section from a coolant inlet passage in the root section, and each terminate proximate the airfoil tip.

Abstract translation: 转子叶片包括根部，翼型部分，前缘冷却腔，中间冷却腔和后缘冷却腔。 前缘，中间和后缘冷却空腔各自从根部中的冷却剂入口通道翼展方向穿过翼型部分，并且各自终止于翼型末端附近。

公开(公告)号：WO2013138129A1

公开(公告)日：2013-09-19

申请号：PCT/US2013/029289

申请日：2013-03-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： PROPHETER-HINCKLEY, Tracy, A. ,  PIETRASZKIEWICZ, Edward, F. ,  PEREZ, Rafael, A. ,  BANKS, Anton, G.

IPC: F01D5/18 ,  F02C7/16

CPC classification number: F01D5/187 ,  F05D2240/12 ,  F05D2250/185 ,  F05D2260/205 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: 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.

Abstract translation: 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。