公开(公告)号：SG11201405597PA

公开(公告)日：2014-11-27

申请号：SG11201405597P

申请日：2013-03-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PROPHETER-HINCKLEY TRACY A ,  PIETRASZKIEWICZ EDWARD F ,  PEREZ RAFAEL A ,  BANKS ANTON G

IPC: F01D5/18

公开(公告)号：EP2825732A4

公开(公告)日：2016-03-30

申请号：EP13762007

申请日：2013-03-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PROPHETER-HINCKLEY TRACY A ,  PIETRASZKIEWICZ EDWARD F ,  PEREZ RAFAEL A ,  BANKS ANTON G

IPC: F01D5/18

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件本体。 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从第一肋朝向前缘内壁的方向上的增加的高度。

公开(公告)号：EP2971545A4

公开(公告)日：2017-02-01

申请号：EP14779667

申请日：2014-03-11

Applicant: UNITED TECHNOLOGIES CORP

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.