公开(公告)号：US10196902B2

公开(公告)日：2019-02-05

申请号：US14854606

申请日：2015-09-15

Applicant: United Technologies Corporation

Inventor： Sasha M. Moore ,  Timothy J. Jennings ,  Thomas N. Slavens ,  Clifford J. Musto ,  Nicholas M. LoRicco ,  Carey Clum ,  John McBrien ,  Christopher Whitfield ,  San Quach

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F04D29/32 ,  F01D9/06

Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.

公开(公告)号：US20180363473A1

公开(公告)日：2018-12-20

申请号：US16100257

申请日：2018-08-10

Applicant: United Technologies Corporation

Inventor： Sasha M. Moore ,  Thomas N. Slavens ,  Nicholas M. Loricco ,  Timothy J. Jennings

IPC: F01D5/18 ,  B24C3/32 ,  C23F1/32 ,  F01D11/08 ,  C23F1/16 ,  F01D25/12 ,  F01D9/02

Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.

公开(公告)号：US10107110B2

公开(公告)日：2018-10-23

申请号：US15037013

申请日：2014-11-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Sasha M. Moore ,  Thomas N. Slavens ,  Nicholas M. Loricco ,  Timothy J. Jennings

IPC: F01D5/18 ,  B24C3/32 ,  C23F1/16 ,  C23F1/32 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12

Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.

公开(公告)号：US10006371B2

公开(公告)日：2018-06-26

申请号：US14827050

申请日：2015-08-14

Applicant: United Technologies Corporation

Inventor： John McBrien ,  Thomas N. Slavens ,  Clifford J. Musto ,  Timothy J. Jennings ,  Nicholas M. LoRicco ,  Sasha M. Moore

IPC: F02C7/18 ,  F01D5/18 ,  F01D9/06 ,  F01D9/02 ,  F02C3/04 ,  F23R3/00

CPC classification number: F02C7/18 ,  F01D5/186 ,  F01D9/023 ,  F01D9/065 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine component is described. The component includes a component wall having an internal surface that is adjacent a flow of coolant and an external surface that is adjacent a flow of gas. The component wall includes a cooling hole that has an inlet defined by the internal surface and an outlet defined by the external surface. The cooling holes also has a metering location having the smallest cross-section area of the cooling hole, an internal diffuser positioned between the inlet and the metering location, an accumulation diverter portion of the internal diffuser and an accumulator portion of the internal diffuser.

公开(公告)号：US09995147B2

公开(公告)日：2018-06-12

申请号：US14619343

申请日：2015-02-11

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo, Jr. ,  Jeffrey R. Levine ,  Kyle C. Lana ,  Sasha M. Moore

IPC: F01D5/18 ,  F01D5/20

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D5/20 ,  F05D2240/307 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform, an airfoil tip, and an airfoil section between the platform and the airfoil tip. The airfoil section has a cavity spaced radially from the airfoil tip and a plurality of cooling passages radially between the cavity and the airfoil tip. Each of the plurality of cooling passages defines an exit port adjacent the airfoil tip. An internal feature within each of the plurality of cooling passages is configured to meter flow to the exit port.

公开(公告)号：US20160258299A1

公开(公告)日：2016-09-08

申请号：US15037013

申请日：2014-11-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Sasha M. Moore ,  Thomas N. Slavens ,  Nicholas M. Loricco ,  Timothy J. Jennings

IPC: F01D5/18 ,  F01D11/08 ,  C23F1/32 ,  B24C3/32 ,  C23F1/16 ,  F01D9/02 ,  F01D25/12

CPC classification number: F01D5/187 ,  B24C3/327 ,  C23F1/16 ,  C23F1/32 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2300/506 ,  Y02T50/673 ,  Y02T50/676

Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.

Abstract translation: 本公开的一个示例性实施例涉及形成发动机部件的方法。 该方法包括形成具有内部通道的发动机部件，内部通路形成初始尺寸。 该方法还包括在内部通道内建立加工流体的流动，所述加工流体改变初始尺寸。

公开(公告)号：US20160177737A1

公开(公告)日：2016-06-23

申请号：US14827453

申请日：2015-08-17

Applicant: United Technologies Corporation

Inventor： Clifford J. Musto ,  Sasha M. Moore ,  Thomas N. Slavens ,  San Quach ,  Nicholas M. LoRicco ,  Timothy J. Jennings ,  John McBrien

IPC: F01D5/18 ,  F01D11/08 ,  F04D29/32 ,  F04D29/54 ,  F01D9/04 ,  F04D29/58

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D9/023 ,  F01D9/041 ,  F01D9/065 ,  F01D11/08 ,  F02K1/822 ,  F04D29/324 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/314 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface. The film cooling hole has a pocket that faces the interior flow path and extends substantially in a longitudinal direction. The film cooling hole has a portion downstream from the pocket and is arranged at an angle relative to the longitudinal direction and extends to the exterior surface.

Abstract translation: 燃气涡轮发动机部件包括提供外表面和内部流路表面的壁。 薄膜冷却孔延伸穿过壁并构造成将内部流动通道表面流体连接到外部表面。 薄膜冷却孔具有面向内部流动路径并且基本上在纵向方向上延伸的凹部。 薄膜冷却孔具有从凹部下游的部分，并且相对于纵向方向以一定角度布置并延伸到外表面。

公开(公告)号：US20160108739A1

公开(公告)日：2016-04-21

申请号：US14852896

申请日：2015-09-14

Applicant: United Technologies Corporation

Inventor： Clifford J. Musto ,  Nicholas M. LoRicco ,  Thomas N. Slavens ,  Timothy J. Jennings ,  Carey Clum ,  Sasha M. Moore ,  John McBrien ,  San Quach ,  Christopher Whitfield

IPC: F01D5/18 ,  B22C9/10

CPC classification number: F01D5/186 ,  B22C9/10 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/187 ,  F05D2230/21 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2240/127 ,  F05D2260/202 ,  F05D2260/2212 ,  Y02T50/676

Abstract: A wall of a gas turbine engine is provided. The wall may comprise an external surface adjacent a gas path and an internal surface adjacent an internal flow path. A film hole may have an inlet at the internal surface and an outlet at the external surface. A flow accumulator adjacent the inlet may protrude from the internal surface. A method of making an engine component is also provided and comprises the step of forming a component wall comprising an accumulator on an internal surface and a film hole defined by the component wall. The film hole may include an opening adjacent the accumulator and defined by the internal surface.

Abstract translation: 提供燃气涡轮发动机的壁。 壁可以包括邻近气体通道的外表面和与内部流动路径相邻的内部表面。 薄膜孔可以在内表面具有入口，在外表面可以具有出口。 靠近入口的流动蓄能器可从内表面突出。 还提供了一种制造发动机部件的方法，包括在内表面上形成包括蓄能器的部件壁和由部件壁限定的薄膜孔的步骤。 薄膜孔可以包括邻近蓄电池并由内表面限定的开口。