公开(公告)号：US10054055B2

公开(公告)日：2018-08-21

申请号：US14946279

申请日：2015-11-19

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Edward F. Pietraszkiewicz

IPC: F02C7/18 ,  F01D5/08 ,  F01D5/18

CPC classification number: F02C7/18 ,  F01D5/08 ,  F01D5/18 ,  F01D5/187 ,  F05D2230/232 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/205 ,  Y02T50/672 ,  Y02T50/676

Abstract: A platform is disclosed. The platform may include an airfoil section with a cooling passage and a platform. The platform may have various cooling features, such as a platform cooling apparatus. The platform cooling apparatus may have a cooling passage forming a channel disposed at least partially through the platform and the platform cooling apparatus may have an inflow channel in fluidic communication with the channel and the cooling passage so that cooling air may travel from the cooling cavity of the blade airfoil section and into the platform cooling apparatus. Moreover, the platform cooling apparatus may have a cooling cover apparatus at least partially fluidically sealing the platform cooling apparatus.

公开(公告)号：US10053996B2

公开(公告)日：2018-08-21

申请号：US14880620

申请日：2015-10-12

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D9/02

CPC classification number: F01D9/041 ,  F01D5/188 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

Abstract: A vane includes a vane body extending from a root to an opposed tip along a longitudinal axis and first and second baffle bodies. The vane body defines a leading edge and a trailing edge, and a cavity defined between the leading edge, the trailing edge, the root and the tip. The vane body includes at least one vane rib defined between the leading edge and the trailing edge inside the cavity. The first baffle body is defined in one of a leading edge portion and a trailing edge portion of the cavity. The second baffle body is defined in a middle portion of the cavity.

公开(公告)号：US10012106B2

公开(公告)日：2018-07-03

申请号：US14613093

申请日：2015-02-03

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Gina Cavallo

IPC: F01D5/14 ,  F01D25/12 ,  F01D9/02 ,  F01D5/18 ,  F01D9/04

CPC classification number: F01D25/12 ,  F01D5/188 ,  F01D5/189 ,  F01D9/02 ,  F01D9/041 ,  F05D2220/30 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2260/221 ,  Y02T50/676

Abstract: A turbine engine component includes an internal baffle spaced between first and second walls. Each wall may have a plurality of cooling holes in fluid communication with respective upstream and downstream cooling paths defined between the baffle and the respective walls. Cooling air first flows through an upstream end portion of the upstream cooling path, then through a downstream end portion where the air enters a bleed aperture in the baffle. From the bleed aperture, a portion of or all of the cooling air may enter an internal cavity defined by the baffle and, from there, flows through at least one hole that may be a plurality of impingement holes in the baffle, and into the downstream cooling passage where the portion or all of the remaining cooling air may exit the component through the cooling holes in the second wall.

公开(公告)号：US09982543B2

公开(公告)日：2018-05-29

申请号：US14818379

申请日：2015-08-05

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/188 ,  F01D5/189 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2260/20 ,  F05D2260/201

Abstract: An airfoil of a gas turbine engine having a hollow body defining at least one airfoil cavity therein, the hollow body defining an inner diameter and an outer diameter and a baffle positioned within the at least one airfoil cavity and extending over less than an entire length between the inner diameter and the outer diameter, the baffle configured to reduce the cross-sectional area within the at least one airfoil cavity. The at least one airfoil cavity includes a first portion having a length that is defined by an open cavity having a full cross-sectional area and a second portion having a length that is defined by a reduced cross-sectional area, the second portion being the length of the baffle within the at least one airfoil cavity.

公开(公告)号：US09845693B2

公开(公告)日：2017-12-19

申请号：US14822334

申请日：2015-08-10

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D9/04 ,  F01D25/12 ,  F23R3/00 ,  F01D9/06 ,  F01D5/18

CPC classification number: F01D9/042 ,  F01D5/186 ,  F01D9/065 ,  F01D25/12 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  Y02T50/672 ,  Y02T50/676

Abstract: A surface structure having an overlapping herringbone filmhole pattern is disclosed. For instance, the surface structure may have filmholes arranged in filmrows, each filmrow divided into groups of filmholes. A first group may be oriented to direct cooling air generally outward over a surface of the surface structure and a second group may be oriented to direct cooling air generally inward over a surface of the surface structure. Between the first group and the second group of filmholes in each filmrow, a transition region exists. A transition region filmrow group may be disposed within the transition region and may be collinear with or staggered relative to the first group and/or the second group. In this manner, the transition region filmrow group enhances the effectiveness of the cooling proximate to the transition region.

公开(公告)号：US20160376897A1

公开(公告)日：2016-12-29

申请号：US14752143

申请日：2015-06-26

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D9/04 ,  F01D5/02 ,  F01D25/12

CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D5/187 ,  F01D5/188 ,  F01D5/189 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2240/126 ,  F05D2250/185 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A vane includes a forward rib and an aft rib positioned axially aft of the forward rib. The vane also includes a middle rib positioned axially between the forward rib and the aft rib, such that the forward rib and the middle rib define a forward passage configured to receive a forward baffle and the middle rib and the aft rib define an aft passage configured to receive an aft baffle. The vane also includes an inner surface extending axially from the forward rib to the aft rib, being radially separated from the middle rib via a gap such that air can flow between the aft passage and the forward passage via the gap, and having a radially outward curve from the forward rib to the middle rib and having a radially inward curve from the middle rib to the aft rib.

Abstract translation: 叶片包括位于前肋的轴向后方的前肋和后肋。 叶片还包括轴向地定位在前肋和后肋之间的中间肋，使得前肋和中间肋限定了前通道，其构造成容纳前挡板，中肋和后肋限定了后通道构造 收到一个后挡板。 叶片还包括从前肋向后肋轴向延伸的内表面，其经由间隙与中间肋径向分开，使得空气可以经由间隙在后通道和前通道之间流动，并且具有径向向外 从前肋到中肋处的曲线，并且具有从中肋到后肋的径向向内的曲线。

公开(公告)号：US20160376896A1

公开(公告)日：2016-12-29

申请号：US14903467

申请日：2014-06-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Dominic J. Mongillo, JR.

IPC: F01D5/18 ,  F01D11/08 ,  F01D25/12 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/21 ,  F05D2240/81 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/205 ,  Y02T50/676

Abstract: A gas turbine engine component includes a structure having a wall that provides an exterior surface. A first cooling passage is arranged adjacent to and interiorly of the wall. A second cooling passage is arranged in the wall and provides a first fluid flow direction. A resupply channel is arranged in the wall and is fluidly interconnected to the second cooling passage. A resupply hole fluidly interconnects the first cooling passage and the resupply channel. The resupply channel is transverse relative to the second cooling passage to provide a second fluid flow direction that extends from the resupply hole to the second cooling passage.

Abstract translation: 燃气涡轮发动机部件包括具有提供外表面的壁的结构。 第一冷却通道布置成与壁的内部和内部相邻。 第二冷却通道布置在壁中并提供第一流体流动方向。 补给通道布置在壁中并且流体地互连到第二冷却通道。 补给孔流体地互连第一冷却通道和补给通道。 补给通道相对于第二冷却通道是横向的，以提供从补给孔延伸到第二冷却通道的第二流体流动方向。

公开(公告)号：US20160273369A1

公开(公告)日：2016-09-22

申请号：US15167162

申请日：2016-05-27

Applicant: United Technologies Corporation

Inventor： John McBrien ,  Lea Kennard Castle ,  Brandon W. Spangler ,  JinQuan Xu

IPC: F01D5/28 ,  B22C9/06 ,  B22D25/02 ,  B22D27/04 ,  B22D23/06 ,  F01D9/02 ,  B22F3/11 ,  B22F3/24 ,  B23K15/00 ,  B23K26/342 ,  F23R3/28 ,  F01D5/14 ,  B22C9/10 ,  B22F3/105

CPC classification number: F01D5/28 ,  B22C7/02 ,  B22C9/02 ,  B22C9/043 ,  B22C9/061 ,  B22C9/10 ,  B22C9/101 ,  B22C9/108 ,  B22C9/22 ,  B22C9/24 ,  B22D23/06 ,  B22D25/02 ,  B22D27/04 ,  B22D27/045 ,  B22F3/1055 ,  B22F3/11 ,  B22F3/24 ,  B22F5/04 ,  B22F2003/248 ,  B22F2998/00 ,  B22F2998/10 ,  B23K15/0006 ,  B23K15/0086 ,  B23K26/342 ,  B32B1/08 ,  B32B3/08 ,  B32B3/26 ,  B32B5/16 ,  B32B9/005 ,  B32B2250/03 ,  B32B2264/105 ,  B32B2603/00 ,  B33Y10/00 ,  B33Y80/00 ,  C30B11/00 ,  C30B29/52 ,  F01D5/147 ,  F01D5/18 ,  F01D5/187 ,  F01D5/282 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2300/175 ,  F05D2300/211 ,  F05D2300/607 ,  F23R3/28 ,  Y02P10/292 ,  Y02P10/295 ,  B22F2003/242 ,  C30B11/14

Abstract: An intermediate component with an internal passageway includes a solid metallic additively manufactured component with an internal passageway in a near finished shape. The component has voids greater than 0 percent but less than approximately 15 percent by volume and up to 15 percent additional material by volume in the near finished shape compared to a desired finished configuration. Also included are a ceramic core disposed within the internal passageway of the component and an outer ceramic shell mold encasing an entirety of the component, such that an entire external surface of the component is covered by the outer ceramic shell mold.

Abstract translation: 具有内部通道的中间部件包括具有接近完成形状的内部通道的固体金属加成制造部件。 该组分具有大于0％但小于约15体积％的空隙，并且与所需的最终配置相比，在接近完成的形状中具有高达15％的体积附加材料。 还包括设置在部件的内部通道内的陶瓷芯体和包围整个部件的外部陶瓷壳体模具，使得部件的整个外表面被外部陶瓷壳体模具覆盖。

公开(公告)号：US09415438B2

公开(公告)日：2016-08-16

申请号：US14250692

申请日：2014-04-11

Applicant: United Technologies Corporation

Inventor： John McBrien ,  Lea Kennard Castle ,  Brandon W. Spangler

IPC: B22C7/02 ,  B22D23/06 ,  F01D5/28 ,  F01D5/18 ,  B22F3/105 ,  B22F5/04 ,  C30B11/00 ,  C30B29/52 ,  B22C9/04 ,  B22C9/02 ,  B22C9/10 ,  B22C9/22 ,  B23K15/00 ,  B32B1/08 ,  B32B3/08 ,  B32B3/26 ,  B32B5/16 ,  B32B9/00 ,  B33Y10/00 ,  B33Y80/00

CPC classification number: F01D5/28 ,  B22C7/02 ,  B22C9/02 ,  B22C9/043 ,  B22C9/061 ,  B22C9/10 ,  B22C9/101 ,  B22C9/108 ,  B22C9/22 ,  B22C9/24 ,  B22D23/06 ,  B22D25/02 ,  B22D27/04 ,  B22D27/045 ,  B22F3/1055 ,  B22F3/11 ,  B22F3/24 ,  B22F5/04 ,  B22F2003/248 ,  B22F2998/00 ,  B22F2998/10 ,  B23K15/0006 ,  B23K15/0086 ,  B23K26/342 ,  B32B1/08 ,  B32B3/08 ,  B32B3/26 ,  B32B5/16 ,  B32B9/005 ,  B32B2250/03 ,  B32B2264/105 ,  B32B2603/00 ,  B33Y10/00 ,  B33Y80/00 ,  C30B11/00 ,  C30B29/52 ,  F01D5/147 ,  F01D5/18 ,  F01D5/187 ,  F01D5/282 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2300/175 ,  F05D2300/211 ,  F05D2300/607 ,  F23R3/28 ,  Y02P10/292 ,  Y02P10/295 ,  B22F2003/242 ,  C30B11/14

Abstract: A method of forming a metal single crystal turbine component with internal passageways includes forming a polycrystalline turbine blade with internal passageways by additive manufacturing and filling the passageways with a core ceramic slurry. The ceramic slurry is then treated to harden the core and the turbine component is encased in a ceramic shell which is treated to form a ceramic mold. The turbine component in the mold is then melted and directionally solidified in the form of a single crystal. The outer shell and inner ceramic core are then removed to form a finished single crystal turbine component with internal passageways.

Abstract translation: 形成具有内部通道的金属单晶涡轮机部件的方法包括通过添加剂制造形成具有内部通道的多晶涡轮机叶片，并用核心陶瓷浆料填充通道。 然后处理陶瓷浆料以硬化芯部，并且将涡轮机部件封装在经过处理以形成陶瓷模具的陶瓷壳体中。 然后将模具中的涡轮机部件以单晶的形式熔化并定向凝固。 然后去除外壳和内陶瓷芯以形成具有内部通道的成品单晶涡轮机部件。

公开(公告)号：US20160208621A1

公开(公告)日：2016-07-21

申请号：US14915513

申请日：2014-08-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Edwin Otero

IPC: F01D5/18 ,  B28B7/34 ,  B28B1/30 ,  F01D9/04 ,  F01D25/12

CPC classification number: F01D5/187 ,  B22C9/04 ,  B22C9/046 ,  B22C9/103 ,  B28B1/30 ,  B28B7/34 ,  F01D5/188 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2250/232 ,  F05D2250/75 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2300/20 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

Abstract translation: 燃气涡轮发动机部件包括包括沿第一方向延伸到端壁的间隔开的第一和第二外壁的结构。 第一和第二外壁在端壁处连接以提供冷却腔。 叉骨挡板布置在冷却腔中，并且包括分别邻近第一和第二外壁的第一和第二内壁。 第一和第二内壁沿第一方向延伸并由顶点连接以提供第一腔。 叉骨挡板将第一腔与设置在顶点和端壁之间的第二腔分开。