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。