公开(公告)号：EP3021999A4

公开(公告)日：2017-04-05

申请号：EP14825685

申请日：2014-07-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PROPHETER-HINCKLEY TRACY A ,  MONGILLO DOMINIC J JR ,  FISK BENJAMIN T

IPC: B22F5/04 ,  B22F3/00 ,  B22F3/105 ,  B22F3/24 ,  B22F5/00 ,  C04B35/64 ,  F01D5/14 ,  F01D5/18 ,  F01D5/28

CPC classification number: B22C9/04 ,  B22F3/1055 ,  B22F3/24 ,  B22F5/009 ,  B22F2003/244 ,  B28B1/001 ,  B28B7/346 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/147 ,  F01D5/187 ,  F01D5/284 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2230/22 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2260/202 ,  F05D2300/211 ,  F05D2300/2112 ,  Y02P10/295 ,  Y02T50/671 ,  Y02T50/676

Abstract: A method of preparing a casting article for use in manufacturing a gas turbine engine part according to an exemplary aspect of the present disclosure includes, among other things, communicating a powdered material to an additive manufacturing system and preparing a casting article that includes at least one trunk and a skin core that extends from the at least one trunk out of the powdered material.

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：EP2841701A4

公开(公告)日：2016-07-20

申请号：EP13781545

申请日：2013-04-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PROPHETER-HINCKLEY TRACY A ,  ZELESKY MARK F ,  MONGILLO JR DOMINIC J ,  DEVORE MATTHEW A ,  GAUTSCHI STEVEN BRUCE ,  FISK BENJAMIN T

IPC: F01D5/12 ,  B22C9/04 ,  B22C9/10 ,  B22C9/24 ,  F01D5/18 ,  F01D9/00 ,  F02C7/12

CPC classification number: B22C9/04 ,  B22C9/10 ,  B22C9/24 ,  B22F3/1017 ,  B22F3/105 ,  B22F3/1055 ,  B22F5/04 ,  B23K15/0086 ,  B33Y10/00 ,  B33Y80/00 ,  C21D9/0068 ,  F01D5/187 ,  F05D2240/303 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  Y02P10/292 ,  Y02P10/295

Abstract: An airfoil has a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A leading edge wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the leading edge wall to provide an impingement cavity between the leading edge wall and the impingement wall and multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil, and producing the airfoil.

Abstract translation: 机翼具有主体，其包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。 前缘壁在前缘提供外部翼型表面。 冲击壁与前缘壁一体地形成，以在前缘壁和冲击壁之间提供冲击腔，并且多个冲击孔设置在冲击壁中。 撞击孔横向穿过冲击壁。 一种制造翼型件的方法包括以下步骤：将多层粉末金属沉积到彼此上，参考与翼型的特定横截面相关的CAD数据并将翼片相互连接，并产生翼型件。

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：EP2892671A4

公开(公告)日：2016-05-18

申请号：EP13835530

申请日：2013-05-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PROPHETER-HINCKLEY TRACY A

IPC: B22C9/10 ,  B22C9/22 ,  B22C9/24

CPC classification number: B22D25/02 ,  B22C7/02 ,  B22C9/04 ,  B22C9/103 ,  B22C9/108 ,  B22C9/24 ,  B22D23/00 ,  F01D5/18 ,  F01D5/186 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2300/13

Abstract: A core assembly for forming a cast component includes a refractory metal core and a ceramic core element. The refractory metal core includes first and second ends and sides extending from the first end to the second end. The ceramic core element includes a slot positioned between first and second lands, each land having an inner surface facing the slot and an adjacent outer surface. The first end of the refractory metal core is secured within the slot with an adhesive, and the refractory metal core extends from the ceramic core element in both a longitudinal and a transverse direction. The slot, lands, and refractory metal core form a core assembly providing access paths to the sides of the refractory metal core. Surplus adhesive is removed from the refractory metal core via the access paths. Investment casting provides the component with an internal passage and an internal cooling circuit.

公开(公告)号：EP2841702A4

公开(公告)日：2016-03-16

申请号：EP13781752

申请日：2013-04-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FISK BENJAMIN T ,  PROPHETER-HINCKLEY TRACY A ,  DOLANSKY GREGORY M ,  TRACY ANITA L

IPC: F01D5/12 ,  F01D5/14 ,  F01D5/18 ,  F01D9/00 ,  F02C7/12 ,  F02K3/00

CPC classification number: F01D5/147 ,  F05D2230/31

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first sidewall. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. At least one of the first side wall and the second side wall includes at least one longitudinally elongated buttress that tapers longitudinally. The at least one longitudinally elongated buttress defines an increased thickness of, respectively, the first side wall or the second sidewall. The at least one longitudinally elongated buttress projects partially across the cavity toward the other of the first side wall or the second sidewall.

公开(公告)号：EP2946081A4

公开(公告)日：2016-03-09

申请号：EP13871926

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G ,  SURACE RAYMOND ,  PROPHETER-HINCKLEY TRACY A

IPC: F01D17/16 ,  F01D5/14 ,  F01D5/18

CPC classification number: F01D17/162 ,  F01D5/145 ,  F01D5/187

公开(公告)号：EP2841700A4

公开(公告)日：2016-03-02

申请号：EP13781223

申请日：2013-04-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PROPHETER-HINCKLEY TRACY A ,  HOUSTON DAVID P ,  TRACY ANITA L

IPC: F01D5/12 ,  B22F5/04 ,  F01D5/18 ,  F02C7/00 ,  F02K3/00

CPC classification number: F01D5/147 ,  B22F3/1055 ,  B22F5/04 ,  B33Y80/00 ,  F04D29/324 ,  F04D29/388 ,  F05D2230/30 ,  Y02P10/295 ,  Y02T50/673 ,  Y10T29/49236

Abstract: A support for an airfoil includes a trunk and a limb extending from the trunk for distribution within the airfoil.

Abstract translation: 在翼型件支持A包括躯干和肢体从后备箱的翼型件内的分布扩展。

公开(公告)号：EP2841709A4

公开(公告)日：2015-04-29

申请号：EP13781623

申请日：2013-04-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FISK BENJAMIN T ,  PROPHETER-HINCKLEY TRACY A ,  DOLANSKY GREGORY M ,  HOUSTON DAVID P ,  TRACY ANITA L

IPC: F01D5/16

CPC classification number: F01D5/16

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.

公开(公告)号：EP2841705A4

公开(公告)日：2015-04-29

申请号：EP13782220

申请日：2013-04-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FISK BENJAMIN T ,  PROPHETER-HINCKLEY TRACY A ,  HOUSTON DAVID P ,  TRACY ANITA L

IPC: F01D5/16

CPC classification number: F01D5/16 ,  B22F3/1055 ,  B22F5/04 ,  B22F5/10 ,  F01D9/041 ,  F01D25/04 ,  F04D29/38 ,  F04D29/542 ,  F04D29/668 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2240/50 ,  F05D2250/232 ,  Y02P10/295

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is loose within the cavity.