公开(公告)号：US10549338B2

公开(公告)日：2020-02-04

申请号：US16214651

申请日：2018-12-10

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  James T. Auxier

IPC: B22C9/10 ,  B22C9/12 ,  B22C9/18 ,  B22C9/24

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a core body for at least partially forming an internal passage architecture of a component; and forming an outer skin on the core body in which a core body binder is locally eliminated.

公开(公告)号：US10406596B2

公开(公告)日：2019-09-10

申请号：US14702136

申请日：2015-05-01

Applicant: United Technologies Corporation

Inventor： Matthew S. Gleiner ,  Bret M. Teller ,  James T. Auxier

IPC: F01D5/14 ,  F01D5/18 ,  B22C9/10 ,  B22D15/00 ,  B22D17/00 ,  B22C9/06 ,  B22D25/02 ,  F01D5/02 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12

Abstract: A casting core for an airfoil according to an example of the present disclosure includes, among other things, a first portion extending in a first direction and corresponding to a first cavity of an airfoil. The first portion defines a reference plane along a parting line formed by a casting die. The first portion defines a plurality of grooves corresponding to a plurality of trip strips of the airfoil. Each of the plurality of grooves defines a respective groove axis, and the plurality of grooves are distributed in the first direction along a first side of the reference plane such that one or more of the groove axes are oriented with respect to a pull direction of the casting die. A method for fabricating a gas turbine engine component is also disclosed.

公开(公告)号：US20180161851A1

公开(公告)日：2018-06-14

申请号：US14616940

申请日：2015-02-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  James T. Auxier ,  Eric A. Hudson

IPC: B22C9/10

CPC classification number: B22C9/10 ,  B22C7/02 ,  B22C21/14

Abstract: A core assembly for a casting system according to an exemplary aspect of the present disclosure includes, among other things, a core that includes a body and at least one hole formed through the body and a spacer that extends through the at least one hole. The spacer includes a stud portion and a chaplet portion configured to abut a surface of the body that circumscribes the at least one hole.

公开(公告)号：US20160319674A1

公开(公告)日：2016-11-03

申请号：US14702136

申请日：2015-05-01

Applicant: United Technologies Corporation

Inventor： Matthew S. Gleiner ,  Bret M. Teller ,  James T. Auxier

IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  B22D17/00 ,  B22C9/10 ,  B22D15/00 ,  B22D25/02 ,  F01D5/02 ,  F01D25/12

CPC classification number: B22C9/101 ,  B22C9/06 ,  B22C9/103 ,  B22D15/00 ,  B22D17/00 ,  B22D25/02 ,  F01D5/02 ,  F01D5/14 ,  F01D5/147 ,  F01D5/187 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2260/202

Abstract: A casting core for an airfoil according to an example of the present disclosure includes, among other things, a first portion extending in a first direction and corresponding to a first cavity of an airfoil. The first portion defines a reference plane along a parting line formed by a casting die. The first portion defines a plurality of grooves corresponding to a plurality of trip strips of the airfoil. Each of the plurality of grooves defines a respective groove axis, and the plurality of grooves are distributed in the first direction along a first side of the reference plane such that one or more of the groove axes are oriented with respect to a pull direction of the casting die. A method for fabricating a gas turbine engine component is also disclosed.

Abstract translation: 根据本公开的示例的用于翼型的铸造芯部尤其包括沿第一方向延伸并对应于翼型件的第一腔的第一部分。 第一部分沿着由铸模形成的分型线限定参考平面。 第一部分限定对应于翼型件的多个跳闸条的多个槽。 多个槽中的每一个限定相应的槽轴线，并且多个槽沿着参考平面的第一侧在第一方向上分布，使得一个或多个槽轴线相对于 铸造模具 还公开了一种用于制造燃气涡轮发动机部件的方法。

公开(公告)号：US10960460B2

公开(公告)日：2021-03-30

申请号：US15112009

申请日：2015-01-23

Applicant: United Technologies Corporation

Inventor： Brooks E. Snyder ,  Thomas N. Slavens ,  Mark F. Zelesky ,  James T. Auxier

IPC: B22C9/04 ,  B33Y80/00 ,  B22C7/02 ,  B22C9/10 ,  B22F5/00 ,  B22F3/105 ,  B22F7/06 ,  B22C21/14 ,  B33Y10/00 ,  B22C1/00 ,  B29L31/00 ,  B29C64/153

Abstract: A mold for manufacturing a casted workpiece is, at least in-part, manufactured utilizing an additive manufacturing process. The mold may have a core having non-line-of-sight features that are additively manufactured and in contact with an outer shell of a wax mold and/or an outer shell of a casting mold of the mold. The outer shell of either the wax or casting molds may also be additively manufactured, and the shell of the casting mold may be additively manufactured as one unitary piece to the core.

公开(公告)号：US20160354953A1

公开(公告)日：2016-12-08

申请号：US14729426

申请日：2015-06-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James T. Auxier ,  Lea Kennard Castle

IPC: B29C41/20

CPC classification number: B29C41/20 ,  B23K26/389 ,  B23K35/0244 ,  B23K35/025 ,  B23K35/3033 ,  B23K2101/001 ,  B23K2103/172 ,  B23P6/007 ,  B23P2700/06 ,  B29L2031/7504 ,  F01D5/005 ,  F01D5/186 ,  F01D5/286 ,  F01D5/288 ,  Y02T50/676

Abstract: A method of remanufacturing a component including at least partially filling an internal passage architecture of a component with a salt-based protective fill; filling at least one of a multiple of cooling holes of the internal passage architecture subsequent to the at least partially filling the internal passage architecture of the component with the salt-based protective fill; and removing the salt-based protective fill subsequent to filling at least one of the multiple of cooling holes.

Abstract translation: 一种再制造组件的方法，包括至少部分地用盐基保护填充物填充部件的内部通道结构; 在用所述盐基保护填充物至少部分地填充所述部件的内部通道结构之后，填充所述内部通道结构的多个冷却孔中的至少一个; 以及在填充所述多个冷却孔中的至少一个之后移除所述盐基保护填充物。

公开(公告)号：US09453419B2

公开(公告)日：2016-09-27

申请号：US13729110

申请日：2012-12-28

Applicant: United Technologies Corporation

Inventor： James T. Auxier ,  Jason L. O'Hearn ,  Thomas N. Slavens ,  Yafet Girma

IPC: F01D5/18 ,  F01D5/20 ,  F01D11/08

CPC classification number: F01D5/186 ,  F01D5/20 ,  F01D11/08 ,  F05D2240/307 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge.

Abstract translation: 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘连接的压力和吸力壁，以提供具有沿径向方向延伸到尖端的外表面的翼型件。 尖端处的弧形线从前缘延伸到后缘。 压力和吸力侧搁板分别设置在压力侧和吸力侧壁的外倾线的相对侧的外表面上。 高原是为压力和吸力侧货架感到自豪和分离。 平台沿着弧形线布置并延伸到前缘。

公开(公告)号：US20140212298A1

公开(公告)日：2014-07-31

申请号：US13729110

申请日：2012-12-28

Applicant: United Technologies Corporation

Inventor： James T. Auxier ,  Jason L. O'Hearn ,  Thomas N. Slavens ,  Yafet Girma

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/20 ,  F01D11/08 ,  F05D2240/307 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge.

Abstract translation: 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘连接的压力和吸力壁，以提供具有沿径向方向延伸到尖端的外表面的翼型件。 尖端处的弧形线从前缘延伸到后缘。 压力和吸力侧搁板分别设置在压力侧和吸力侧壁的外倾线的相对侧的外表面上。 高原是为压力和吸力侧货架感到自豪和分离。 平台沿着弧形线布置并延伸到前缘。

公开(公告)号：US10830054B2

公开(公告)日：2020-11-10

申请号：US16675879

申请日：2019-11-06

Applicant: United Technologies Corporation

Inventor： James T. Auxier ,  Parth Jariwala ,  Bret M. Teller

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

Abstract: A casting core may comprise a tip flag material having a forward cavity and a first spear cavity disposed aft of the forward cavity. A trailing edge discharge material may be separated from the tip flag material and include a first row of cavities. The first row of cavities may comprise a first racetrack cavity. A second row of cavities may be disposed aft of the first row of cavities and include a second racetrack cavity. A third row of cavities may be disposed aft of the second row of cavities and include a circular cavity. A fourth row of cavities may be disposed aft of the third row of cavities and include a second spear cavity.

公开(公告)号：US10508552B2

公开(公告)日：2019-12-17

申请号：US15096243

申请日：2016-04-11

Applicant: United Technologies Corporation

Inventor： James T. Auxier ,  Parth Jariwala ,  Bret M. Teller

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

Abstract: A casting core and/or an airfoil may comprise a tip flag cavity having a forward pedestal and a first spear pedestal disposed aft of the forward pedestal. A trailing edge discharge cavity may be separated from the tip flag cavity and include a first row of pedestals. The first row of pedestals may comprise a first racetrack pedestal. A second row of pedestals may be disposed aft of the first row of pedestals and include a second racetrack pedestal. A third row of pedestals may be disposed aft of the second row of pedestals and include a circular pedestal. A fourth row of pedestals may be disposed aft of the third row of pedestals and include a second spear pedestal.