公开(公告)号：EP3017149A4

公开(公告)日：2016-07-20

申请号：EP14820101

申请日：2014-07-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SLAVENS THOMAS N ,  MIRONETS SERGEY ,  STAROSELSKY ALEXANDER ,  SNYDER BROOKS E ,  MARTIN THOMAS J

IPC: F01D5/28 ,  B22F5/04 ,  B23P15/04 ,  F01D5/14 ,  F01D5/18

CPC classification number: F01D5/187 ,  B23P15/04 ,  F01D5/147 ,  F01D5/28 ,  F01D5/284 ,  F01D9/041 ,  F01D25/12 ,  F04D29/321 ,  F04D29/325 ,  F04D29/542 ,  F04D29/5846 ,  F05D2220/32 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2300/175 ,  F05D2300/2261 ,  F05D2300/2283

Abstract: A component for use in a gas turbine engine includes a first section, a second section, and a functionally graded section. The first section is made of a metal material. The second section is made of a ceramic material and/or a ceramic matrix composite material. The functionally graded section is disposed between the first section and the second section.

公开(公告)号：EP2855852A4

公开(公告)日：2016-07-20

申请号：EP13826319

申请日：2013-06-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MARTIN THOMAS J ,  STAROSELSKY ALEXANDER ,  ZELESKY MARK F ,  SLAVENS THOMAS N

IPC: F01D5/18 ,  F02C7/12 ,  F02K3/00

CPC classification number: F01D5/186 ,  F01D5/18 ,  F01D5/187 ,  F05D2240/11 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2240/305 ,  F05D2250/611 ,  F05D2260/20 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbomachinery component includes a surface exposed to hot working fluid flow. The surface has an undulating contour formed from a series of alternating protuberances and troughs. A set of three cooling outlets is associated with each trough.

Abstract translation: 涡轮机械部件包括暴露于热工作流体流的表面。 表面具有由一系列交替的突起和槽形成的起伏的轮廓。 一组三个冷却出口与每个槽相关联。

公开(公告)号：EP2855853A4

公开(公告)日：2016-06-15

申请号：EP13826539

申请日：2013-06-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MARTIN THOMAS J ,  STAROSELSKY ALEXANDER ,  SLAVENS THOMAS N ,  ZELESKY MARK F ,  WAGNER JOEL H

IPC: F01D5/18 ,  F01D5/14 ,  F02C7/12 ,  F02K3/00

CPC classification number: F01D5/186 ,  F01D5/145 ,  F05D2240/121 ,  F05D2240/123 ,  F05D2240/303 ,  F05D2240/305 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/294 ,  F05D2260/202 ,  F05D2260/212 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil includes a suction surface, a pressure surface, a first showerhead cooling hole and a second showerhead cooling hole. The suction surface and the pressure surface both extend axially between a leading edge and a trailing edge, as well as radially from a root section to a tip section. The first showerhead cooling hole and the second showerhead cooling hole both extend into pressure surface near the leading edge. The first showerhead cooling hole and the second showerhead cooling hole are angled in opposing directions.

Abstract translation: 翼型件包括抽吸表面，压力表面，第一喷头冷却孔和第二喷头冷却孔。 吸力表面和压力表面都在前缘和后缘之间轴向延伸，以及从根部到末端部的径向延伸。 第一淋浴头冷却孔和第二淋浴头冷却孔两者都延伸到靠近前缘的压力表面。 第一淋浴头冷却孔和第二淋浴头冷却孔在相反的方向成角度。

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：EP2852734A4

公开(公告)日：2016-04-27

申请号：EP13793384

申请日：2013-05-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THORTON LANE ,  SLAVENS THOMAS N

IPC: F01D5/18 ,  F01D11/18 ,  F01D17/00 ,  F01D17/08 ,  F01D25/12 ,  F02C7/14 ,  F02C9/00 ,  F02K3/00

CPC classification number: F01D5/187 ,  F01D5/18 ,  F01D5/188 ,  F01D11/18 ,  F01D17/00 ,  F01D17/085 ,  F02C6/08 ,  F02C7/185 ,  F05D2270/303 ,  F05D2270/3062 ,  F05D2270/42 ,  G05D23/1921

Abstract: An airfoil includes an airfoil body having an internal cavity. A thermostatic valve is located at least partially within the internal cavity. The thermostatic valve is configured to passively control fluid flow into the internal cavity in response to a temperature within the internal cavity.

Abstract translation: 翼型件包括具有内部空腔的翼型件本体。 恒温阀至少部分位于内腔内。 恒温阀被配置为响应于内腔内的温度而被动地控制流入内腔的流体。