公开(公告)号：US10309230B2

公开(公告)日：2019-06-04

申请号：US14773945

申请日：2013-12-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G McCaffrey

IPC: B28B1/24 ,  F01D5/14 ,  F01D5/22 ,  F01D5/28 ,  F01D5/30 ,  F01D9/04

Abstract: A co-formed element includes a core structure which has a root portion and is formed from a high thermal conductivity ceramic matrix composite material, and a low thermal conductivity layer co-formed with the core structure and surrounding the root portion of the core structure.

公开(公告)号：US20180142971A1

公开(公告)日：2018-05-24

申请号：US15357467

申请日：2016-11-21

Applicant: United Technologies Corporation

Inventor： Michael G McCaffrey ,  Matthew A Devore

IPC: F28F21/08 ,  F28F9/02 ,  F01D25/12

CPC classification number: F28F21/087 ,  F01D25/12 ,  F02C7/18 ,  F02K3/115 ,  F05D2220/32 ,  F05D2250/75 ,  F05D2260/213 ,  F05D2300/1723 ,  F05D2300/175 ,  F05D2300/177 ,  F05D2300/607 ,  F28D1/05316 ,  F28D1/05325 ,  F28D2021/0026 ,  F28F9/02 ,  F28F2265/00 ,  Y02T50/675

Abstract: A staged high temperature heat exchanger (HEX) may comprise a first stage made from a first material and a second stage made from a second material. The first stage may comprise an inlet manifold configured to receive a flow of fluid. The second stage may comprise an outlet manifold whereby the flow of fluid exits the HEX. The first stage is configured to withstand the temperature of the flow of fluid entering the inlet manifold and configured to reduce the temperature of the flow of fluid to an intermediate temperature before the flow of fluid reaches the second stage. In various embodiments, the first material may comprise a nickel-based superalloy having at least 40% of a Ni3(Al,X) precipitate phase, X being a metallic or refractory element other than Al.

公开(公告)号：US20160053619A1

公开(公告)日：2016-02-25

申请号：US14933290

申请日：2015-11-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G McCaffrey

IPC: F01D5/28 ,  F01D5/14

CPC classification number: F01D5/282 ,  B29C65/006 ,  B29C65/48 ,  B29C65/565 ,  B32B18/00 ,  C04B37/003 ,  C04B2235/5224 ,  C04B2235/524 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2237/16 ,  C04B2237/341 ,  C04B2237/343 ,  C04B2237/348 ,  C04B2237/36 ,  C04B2237/365 ,  C04B2237/366 ,  C04B2237/368 ,  C04B2237/38 ,  C04B2237/61 ,  C04B2237/76 ,  C04B2237/86 ,  F01D5/147 ,  F01D5/28 ,  F01D5/284 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2300/6012 ,  F05D2300/6033 ,  Y10T29/49316

Abstract: A method of forming a component for use in a gas turbine engine includes the steps of forming an airfoil/root assembly; creating a platform assembly structure having an opening; inserting the airfoil/root assembly into the opening; and bonding the platform assembly structure to the airfoil/root assembly to form the component.

公开(公告)号：US20160017723A1

公开(公告)日：2016-01-21

申请号：US14773945

申请日：2013-12-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G McCaffrey

IPC: F01D5/28 ,  B28B1/24 ,  F01D9/04 ,  F01D5/22 ,  F01D5/14

CPC classification number: F01D5/282 ,  B28B1/24 ,  F01D5/147 ,  F01D5/225 ,  F01D5/28 ,  F01D5/284 ,  F01D5/3007 ,  F01D5/3092 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2230/51 ,  F05D2260/231 ,  F05D2300/2261 ,  F05D2300/2283 ,  F05D2300/6033

Abstract: A co-formed element includes a core structure which has a root portion and is formed from a high thermal conductivity ceramic matrix composite material, and a low thermal conductivity layer co-formed with the core structure and surrounding the root portion of the core structure.

Abstract translation: 共同形成的元件包括具有根部并由高导热性陶瓷基复合材料形成的芯结构，以及与芯结构共同形成并围绕芯结构的根部的低热导层。

公开(公告)号：US20150275690A1

公开(公告)日：2015-10-01

申请号：US14609926

申请日：2015-01-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G McCaffrey

IPC: F01D25/12 ,  F01D1/02

CPC classification number: F01D25/12 ,  F01D1/02 ,  F01D5/081 ,  F01D5/087 ,  F01D11/001 ,  F01D11/02 ,  F01D11/025 ,  F02C7/18 ,  F05D2260/14 ,  F05D2260/601 ,  F05D2260/6022 ,  Y02T50/673 ,  Y02T50/676

Abstract: An on-board injector that delivers discharge air toward a turbine rotor of a gas turbine engine includes a second wall spaced form a first wall to define an annular inlet about an engine longitudinal axis and a multiple of airfoil shapes between the first wall and the second wall to segregate discharge air from the annular inlet, and a multiple of bypass apertures each along a radial axis transverse to the engine longitudinal axis through each of the multiple of airfoil shapes and the respective first wall, the second wall.

Abstract translation: 向燃气涡轮发动机的涡轮机转子输送排放空气的车载喷射器包括间隔开形成第一壁以限定围绕发动机纵向轴线的环形入口的第二壁和在第一壁和第二壁之间的多个翼型形状 隔离从环形入口排出空气的多个旁路孔，以及多个旁路孔，每个旁路孔沿垂直于发动机纵向轴线的径向轴线穿过多个翼型形状和相应的第一壁，第二壁。