公开(公告)号：US20160090846A1

公开(公告)日：2016-03-31

申请号：US14892713

申请日：2014-04-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Sarah Riley ,  Sasha M. Moore ,  Jeffrey R. Levine

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

CPC classification number: F01D5/186 ,  F01D5/189 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/122 ,  F05D2240/124 ,  F05D2240/30 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.

Abstract translation: 用于燃气涡轮发动机的翼型件包括提供外表面和多个径向延伸的冷却通道的外翼型壁。 外表面提供由前缘和后缘连接的压力和吸力面。 冷却通道包括设置在后缘通道上游并与后缘通道流体连通的供给通道。 冷却孔从供气通道的外侧翼面壁延伸到吸入侧的外表面。

公开(公告)号：US10982552B2

公开(公告)日：2021-04-20

申请号：US14831997

申请日：2015-08-21

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58

Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. The wall has a wall thickness. A protrusion is arranged on the wall that extends a height beyond the wall thickness and provides a portion of the interior flow path surface. A film cooling hole that has an inlet is provided on the protrusion and extends to an exit on the exterior surface.

公开(公告)号：US10259039B2

公开(公告)日：2019-04-16

申请号：US14766061

申请日：2014-01-16

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Lane Thornton ,  Sasha M. Moore ,  Nicholas M. LoRicco

IPC: B22D19/00 ,  B22D29/00 ,  B22C9/10 ,  B22C9/04 ,  F01D5/18 ,  F01D9/02 ,  F23R3/00

Abstract: A method of manufacturing a component that includes providing a core structure, casting a component about the core structure, removing a first portion of the core structure from the cast component, and leaving a second portion of the core structure in the cast component to provide a reduced cross-section in the cast component.

公开(公告)号：US10253635B2

公开(公告)日：2019-04-09

申请号：US15966049

申请日：2018-04-30

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F01D5/20

Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform extending from a root section, an airfoil section extending radially from the platform to an airfoil tip, a plurality of cooling passages defined in an external wall of the airfoil tip, the plurality of cooling passages extending radially between the airfoil tip and a cavity in the airfoil section bounded by the external wall, and each of the plurality of cooling passages defining an inlet port along the cavity and an exit port adjacent the airfoil tip, and at least one internal feature within each of the plurality of cooling passages that meter flow to the respective exit port.

公开(公告)号：US09957814B2

公开(公告)日：2018-05-01

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 ,  F01D9/04 ,  F01D11/08 ,  F04D29/32 ,  F04D29/54 ,  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.

公开(公告)号：US09957810B2

公开(公告)日：2018-05-01

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: F01D25/14 ,  F01D5/18 ,  B22C9/10 ,  B33Y10/00 ,  B33Y80/00

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.

公开(公告)号：US20160312617A1

公开(公告)日：2016-10-27

申请号：US15102890

申请日：2014-12-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Mosheshe Camara-Khary Blake ,  Timothy J. Jennings ,  Nicholas M. LoRicco ,  Sasha M. Moore ,  Clifford J. Musto

IPC: F01D5/14 ,  F01D5/28 ,  F01D5/18

CPC classification number: F01D5/147 ,  F01D5/187 ,  F01D5/20 ,  F01D5/284 ,  F05D2230/30 ,  F05D2260/202 ,  F05D2300/13 ,  F05D2300/17 ,  F05D2300/6031 ,  F05D2300/6033 ,  F05D2300/606 ,  F05D2300/607

Abstract: A blade for a gas turbine engine includes an airfoil that extends a span from a root to a tip. The airfoil is provided by a first portion near the root and has a metallic alloy. A third portion near the tip has a refractory material. A second portion joins the first and third portions and has a functional graded material.

Abstract translation: 用于燃气涡轮发动机的叶片包括将跨度从根延伸到尖端的翼型件。 机翼由靠近根部的第一部分提供，并具有金属合金。 尖端附近的第三部分具有耐火材料。 第二部分连接第一和第三部分并且具有功能分级材料。

公开(公告)号：US20160076451A1

公开(公告)日：2016-03-17

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 ,  F01D9/02 ,  F02C3/04 ,  F01D5/18

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.

Abstract translation: 描述燃气涡轮发动机部件。 该部件包括具有与冷却剂流相邻的内表面和与气流相邻的外表面的部件壁。 部件壁包括具有由内表面限定的入口和由外表面限定的出口的冷却孔。 冷却孔还具有冷却孔的横截面积最小的计量位置，位于入口和计量位置之间的内部扩散器，内部扩散器的堆积分流器部分和内部扩散器的蓄压器部分。

公开(公告)号：US10954800B2

公开(公告)日：2021-03-23

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 ,  C23F1/16 ,  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：US10415394B2

公开(公告)日：2019-09-17

申请号：US15102890

申请日：2014-12-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Mosheshe Camara-Khary Blake ,  Timothy J. Jennings ,  Nicholas M. LoRicco ,  Sasha M. Moore ,  Clifford J. Musto

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/20 ,  F01D5/28

Abstract: A blade for a gas turbine engine includes an airfoil that extends a span from a root to a tip. The airfoil is provided by a first portion near the root and has a metallic alloy. A third portion near the tip has a refractory material. A second portion joins the first and third portions and has a functional graded material.