公开(公告)号：US20180283185A1

公开(公告)日：2018-10-04

申请号：US16005755

申请日：2018-06-12

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo ,  Brandon W. Spangler

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D5/14 ,  F16L53/00

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body having an internal passage for conveying a fluid flow, the internal passage including first and second passage sections coupled at a turn section. A baffle includes an elongated body arranged in the second passage section to define a pair of opposed cooling flow paths that extend from the turn section along a common length of the second passage section, and a first wedge region extending from the elongated body into the first passage section such that the fluid flow is directed through the turn section between the first passage section and the pair of cooling flow paths.

公开(公告)号：US10082033B2

公开(公告)日：2018-09-25

申请号：US14993765

申请日：2016-01-12

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

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

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/81 ,  F05D2260/202

Abstract: A component for a gas turbine engine is provided. The component having: a platform secured to the component, the platform having an exterior surface in fluid communication with an internal cooling pocket of the platform via a plurality of cooling openings located in the platform; a channel in fluid communication with the internal cooling pocket; an internal cooling cavity in fluid communication with the channel via a feed opening extending through an internal wall of the component, wherein a portion of the channel and the feed opening are located below the internal cooling pocket; and a cover plate sealing the internal cooling pocket and the channel.

公开(公告)号：US20180245472A1

公开(公告)日：2018-08-30

申请号：US15919253

申请日：2018-03-13

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Gina Cavallo

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

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/20 ,  F05D2250/184 ,  F05D2250/185 ,  F05D2250/75 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a wall that extends about a cooling cavity. The cooling cavity is a dual-fed cavity that is fed from at least two different locations. A rib separates the cooling cavity into a first portion and a second portion that is fluidly isolated from the first portion. The component is an airfoil. The first portion is fed with a first cooling fluid from a first coolant source, and the second portion is fed with a second, different cooling fluid from a second coolant source. The first and second coolant sources are separate and distinct from the component.

公开(公告)号：US10060445B2

公开(公告)日：2018-08-28

申请号：US14924210

申请日：2015-10-27

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Gina Cavallo

IPC: F04D29/58 ,  F23R3/02 ,  F01D25/12 ,  F23R3/04 ,  F02C7/18 ,  F04D29/16 ,  F04D29/52 ,  F04D29/54 ,  F04D29/64 ,  F23R3/00 ,  F23R3/06 ,  F01D5/18 ,  F01D9/06

CPC classification number: F04D29/582 ,  F01D5/186 ,  F01D9/065 ,  F01D25/12 ,  F02C7/18 ,  F04D29/164 ,  F04D29/526 ,  F04D29/542 ,  F04D29/644 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/15 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/02 ,  F23R3/04 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/675 ,  Y02T50/676

Abstract: A surface structure having a filmhole pattern is disclosed. The filmhole pattern may be an offset herringbone pattern. For instance, the surface structure may have rows of 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. The adjacent filmrows are arranged to enhance the effectiveness of the convective cooling proximate to the transition regions by causing each filmrow to direct cooling air over the transition region of an adjacent filmrow.

公开(公告)号：US20180202294A1

公开(公告)日：2018-07-19

申请号：US15409613

申请日：2017-01-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler

IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18

CPC classification number: F01D5/187 ,  F01D5/18 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2260/202 ,  Y02T50/676

Abstract: A gas turbine engine component comprises a body having a leading edge and a trailing edge. At least one internal channel is formed within the body, wherein the channel includes an inlet to direct cooling flow into the body. At least one cast slot is formed in the trailing edge. At least one drilled filmhole is formed in the trailing edge, wherein the cast slot and drilled filmhole direct flow from the internal channel to an external location from the body. A gas turbine engine, a method of manufacturing a gas turbine engine component, and a method of controlling flow in a gas turbine engine component

公开(公告)号：US09988934B2

公开(公告)日：2018-06-05

申请号：US14807703

申请日：2015-07-23

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D25/12 ,  F01D9/04 ,  F01D25/24 ,  F01D25/14

CPC classification number: F01D25/12 ,  F01D9/042 ,  F01D25/14 ,  F01D25/246 ,  F05D2260/22141

Abstract: A gas turbine engine is provided. The gas turbine engine includes an engine casing structure and a part retained relative to the engine casing structure by a channel-cooled hook. The channel-cooled hook includes at least a portion of a hook cooling channel. A vane assembly for the gas turbine engine is also provided.

公开(公告)号：US20170145832A1

公开(公告)日：2017-05-25

申请号：US14961112

申请日：2015-12-07

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo ,  Brandon W. Spangler

IPC: F01D5/18 ,  F02C7/18 ,  B23P15/04

CPC classification number: F01D5/186 ,  B23P15/04 ,  F01D5/187 ,  F02C7/18 ,  F05D2230/232 ,  F05D2240/81 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/205 ,  F05D2260/22141 ,  Y02T50/672 ,  Y02T50/676

Abstract: A platform is disclosed. The platform may include an airfoil section with a cooling cavity and a platform. The platform may have various cooling features, such as a platform cooling apparatus. The platform cooling apparatus may have a cooling chamber 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 chamber and the cooling cavity 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：US20170130590A1

公开(公告)日：2017-05-11

申请号：US14938310

申请日：2015-11-11

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Dominic J. Mongillo ,  Edward F. Pietraszkiewicz

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

CPC classification number: F01D5/18 ,  F01D5/187 ,  F01D9/02 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/12 ,  F05D2240/81 ,  F05D2250/21 ,  F05D2250/232 ,  F05D2250/26 ,  F05D2250/27 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/60 ,  Y02T50/676

Abstract: An airfoil of a gas turbine engine is provided. The airfoil includes an airfoil body having at least one internal flow passage, the body having a first surface and a second surface, the first surface defining a wall of the at least one internal flow passage and a bleed port fluidly connecting the at least one internal flow passage to the second surface. The bleed port includes a bleed orifice extending from the second surface toward the internal flow passage and a bleed port cavity extending from the first surface toward the second surface, the bleed port cavity and the bleed orifice fluidly connected. The bleed port cavity is defined by a bleed port cavity wall and a base wall surrounding the bleed orifice. The bleed port cavity wall extends from the first surface to the base wall.

公开(公告)号：US20170074116A1

公开(公告)日：2017-03-16

申请号：US14794861

申请日：2015-07-09

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Douglas M. Berczik

IPC: F01D25/12 ,  F01D25/28 ,  F23R3/00 ,  F01D11/10 ,  F01D5/18 ,  F01D25/00 ,  F01D9/06

CPC classification number: F01D25/12 ,  B23P15/04 ,  F01D5/147 ,  F01D5/186 ,  F01D9/04 ,  F01D9/041 ,  F01D9/065 ,  F01D11/10 ,  F01D25/005 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/236 ,  F05D2230/60 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2300/131 ,  F23R3/002 ,  Y02T50/672 ,  Y02T50/676

Abstract: A method for forming a gas turbine engine component comprises the steps of forming a first portion from a high temperature alloy material, and forming a second portion from the high temperature alloy material, the first and second portions each defining an external surface and an internal surface. At least one heat transfer feature is formed directly on the internal surface of at least one of the first and second portions. The first and second portions are attached together to form a component. A component for a gas turbine engine is also disclosed.

Abstract translation: 一种形成燃气涡轮发动机部件的方法包括以下步骤：从高温合金材料形成第一部分，并从高温合金材料形成第二部分，第一和第二部分各自限定外表面和内表面 。 至少一个传热特征直接形成在第一和第二部分中的至少一个的内表面上。 第一和第二部分附接在一起以形成部件。 还公开了一种用于燃气涡轮发动机的部件。

公开(公告)号：US20170044913A1

公开(公告)日：2017-02-16

申请号：US14822334

申请日：2015-08-10

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D9/04 ,  F01D25/12

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.

Abstract translation: 公开了具有重叠的人字形薄膜孔图案的表面结构。 例如，表面结构可以具有布置在薄膜中的薄膜孔，每个薄膜分成薄膜孔组。 第一组可以被定向以将冷却空气大致向外引导到表面结构的表面上，并且第二组可以被定向成将冷却空气大致向内引导到表面结构的表面上。 在每个电影中的第一组和第二组薄膜之间，存在过渡区。 过渡区成膜组可以设置在过渡区域内，并且可以相对于第一组和/或第二组共线或交错。 以这种方式，过渡区域电影组提高了靠近过渡区域的冷却效果。