公开(公告)号：EP2948634A4

公开(公告)日：2016-04-27

申请号：EP13872487

申请日：2013-01-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： QUACH SAN ,  SLAVENS THOMAS N

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/187 ,  F01D5/147 ,  F05D2250/185 ,  F05D2250/314 ,  F05D2260/201

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion that includes a first wall spaced apart from a second wall. At least one rib extends between the first wall and the second wall and at least one aperture extends through the at least one rib. The at least one aperture is angled relative to a radial axis of the at least one rib.

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主体部分，其包括与第二壁间隔开的第一壁。 至少一个肋在第一壁和第二壁之间延伸，并且至少一个孔延伸穿过至少一个肋。 所述至少一个孔相对于所述至少一个肋的径向轴线成角度。

公开(公告)号：EP3063388A4

公开(公告)日：2017-06-14

申请号：EP14857112

申请日：2014-10-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： QUACH SAN ,  SLAVENS THOMAS N

IPC: F02C7/12 ,  F01D5/18 ,  F01D25/12 ,  F01D25/28 ,  F02C7/18 ,  F02C7/20

CPC classification number: F02C7/18 ,  F01D5/187 ,  F01D25/12 ,  F05D2250/181 ,  F05D2250/20 ,  F05D2250/23 ,  F05D2250/25 ,  F05D2250/281 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.

Abstract translation: 燃气涡轮发动机部件包括第一侧壁和与第一侧壁间隔开的第二侧壁。 在第一和第二侧壁之间形成至少一个内部冷却通道。 至少一个基座定位在至少一个冷却通道内并具有从连接到第一侧壁的第一端延伸到连接到第二侧壁的第二端的主体。 该主体包括至少一个突起。

公开(公告)号：EP3011140A4

公开(公告)日：2017-01-25

申请号：EP14834595

申请日：2014-06-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： QUACH SAN ,  PROPHETER-HINCKLEY TRACY A ,  DEVORE MATTHEW A

IPC: F01D5/14 ,  B22C9/10 ,  F01D5/18

CPC classification number: F01D5/186 ,  B22C9/103 ,  F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F02C3/04 ,  F04D29/324 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2240/12 ,  F05D2240/125 ,  F05D2240/30 ,  F05D2240/307 ,  F05D2240/35 ,  F05D2260/202 ,  F05D2260/22141

公开(公告)号：EP2964932A4

公开(公告)日：2016-10-12

申请号：EP14760123

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： QUACH SAN ,  DEVORE MATTHEW A

IPC: F02C7/18 ,  F01D5/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. A stagnation line is located on the pressure side wall aft of the leading edge. A cooling passage is provided between the pressure and suction side walls. Forward-facing cooling holes are provided adjacent to the stagnation line on the pressure side wall and oriented toward the leading edge.

Abstract translation: 用于燃气涡轮发动机的翼型件包括在前缘和后缘处彼此连接的压力和吸力侧壁。 停滞线位于前缘的压力侧壁后方。 在压力侧和吸力侧壁之间设有冷却通道。 靠近压力侧壁上的停滞线设置面向前的冷却孔并朝向前缘定向。

公开(公告)号：EP2946079A4

公开(公告)日：2016-06-22

申请号：EP13872174

申请日：2013-01-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PROPHETER-HINCKLEY TRACY A ,  QUACH SAN ,  DEVORE MATTHEW A

IPC: F01D5/18 ,  B22D30/00 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F23R3/00

CPC classification number: F01D5/186 ,  B22D30/00 ,  F01D5/187 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/22141 ,  F23R3/002

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion that includes a first wall spaced apart from a second wall and disposed about a centerline axis. At least one rib extends between the first wall and the second wall. The at least one rib extends along a rib axis that is transversely angled relative to the centerline axis. At least one impingement hole extends through the at least one rib.

公开(公告)号：EP2847435A4

公开(公告)日：2016-05-11

申请号：EP13788383

申请日：2013-02-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： QUACH SAN ,  GAUTSCHI STEVEN BRUCE ,  BOTNICK CHRISTINA E

IPC: F01D5/18 ,  F01D5/14 ,  F01D25/10 ,  F02C7/12

CPC classification number: F01D5/145 ,  F01D5/187 ,  F05D2240/81 ,  F05D2250/23 ,  F05D2250/231 ,  F05D2250/232 ,  F05D2250/324 ,  F05D2260/201

Abstract: The cooling system for a turbine may include a plurality of platform cooling openings positioned in a platform of the turbine airfoil. In particular, the first set of cooling openings may create a first cooling path and a second set of cooling openings may be placed in the path of the first cooling path where the first cooling flow will cool the second set of cooling openings.

Abstract translation: 涡轮机的冷却系统可以包括定位在涡轮机翼型平台中的多个平台冷却开口。 特别地，第一组冷却开口可以产生第一冷却路径，并且第二组冷却开口可以放置在第一冷却路径的路径中，其中第一冷却流将冷却第二组冷却开口。