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.

公开(公告)号：US10408061B2

公开(公告)日：2019-09-10

申请号：US14769800

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Mark Zelesky ,  Mosheshe Camara-Khary Blake

IPC: F01D5/14 ,  F01D9/04 ,  B23P15/04 ,  B22F7/06 ,  B22F7/08 ,  B22F5/04 ,  B23K1/00 ,  B23K31/02 ,  B22F3/105 ,  B23K101/00

Abstract: An article includes a body that has a first section and a second section bonded with the first section. The first section is formed with a first material that has a first microstructure and the second section is formed of a second material that has a second, different microstructure.

公开(公告)号：US20190271229A1

公开(公告)日：2019-09-05

申请号：US16408751

申请日：2019-05-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Mark F. Zelesky

IPC: F01D5/14 ,  B21K3/04 ,  F01D5/18 ,  B22F3/105 ,  B22F7/08 ,  B23K1/00 ,  B23K15/00 ,  B23K26/34 ,  B23K31/02 ,  B22F3/24 ,  B22D25/02 ,  B22D21/00 ,  B22F5/04 ,  B23K26/342 ,  B23K10/02 ,  B23K26/00

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.

公开(公告)号：US20190211691A1

公开(公告)日：2019-07-11

申请号：US16353563

申请日：2019-03-14

Applicant: United Technologies Corporation

Inventor： Lane Thornton ,  Thomas N. Slavens

IPC: F01D5/18 ,  F02C7/12 ,  F02C3/04 ,  F01D5/28

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D5/28 ,  F02C3/04 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2300/175 ,  F05D2300/505 ,  Y02T50/676

Abstract: In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.

公开(公告)号：US10301967B2

公开(公告)日：2019-05-28

申请号：US15028468

申请日：2014-10-17

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Steven Bruce Gautschi

IPC: F01D5/20 ,  F01D25/12 ,  F01D17/16 ,  F01D5/02 ,  F01D5/12 ,  F01D9/04 ,  F01D17/14 ,  F02C3/04 ,  F01D11/04 ,  F16J15/00 ,  F01D11/00

Abstract: A turbine vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about a first axis transverse to an engine longitudinal axis. The airfoil includes an endwall and at least one protrusion disposed on the endwall configured for obstructing flow through a gap between the endwall and a static structure of the gas turbine engine.

公开(公告)号：US20190118245A1

公开(公告)日：2019-04-25

申请号：US16217908

申请日：2018-12-12

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  James Tilsley Auxier

IPC: B22C9/10 ,  B22F5/00 ,  B22F3/105 ,  B33Y10/00 ,  B33Y80/00 ,  B22D23/06 ,  B22F7/08 ,  B22D27/04

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component includes a base core portion and an additive core portion additively manufactured to the base core portion. A method of manufacturing a core for use in casting an internal cooling circuit within a gas turbine engine component including additively manufacturing an additive core portion to a base core portion.

公开(公告)号：US10260422B2

公开(公告)日：2019-04-16

申请号：US15148051

申请日：2016-05-06

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Mosheshe Camara-Khary Blake

IPC: F01D13/02 ,  F02C7/18 ,  F02C3/04 ,  F02C9/18 ,  F02K3/115 ,  F02C6/08 ,  F28F9/02 ,  F28D21/00

Abstract: A heat exchanger assembly includes an outer manifold defining an outer cavity. An inner cavity is defined by an inner shell supported within the outer manifold and at least partially surrounded by the outer cavity. The inner shell includes a plurality of impingement openings for directing airflow into the inner cavity. An inner manifold is supported within the inner cavity. The inner manifold is exposed to impingement airflow through the plurality of impingement openings in the inner shell. The inner manifold includes a plurality of flow passages and at least one insulator pocket substantially aligned with the plurality of flow passages. A cooled cooling air system for a gas turbine engine and a gas turbine engine assembly are also disclosed.

公开(公告)号：US10247011B2

公开(公告)日：2019-04-02

申请号：US14923553

申请日：2015-10-27

Applicant: United Technologies Corporation

Inventor： San Quach ,  Christopher King ,  Thomas N. Slavens

IPC: F01D5/18 ,  F01D5/02 ,  F01D9/04 ,  F02C3/04 ,  F02C7/18 ,  F23R3/00 ,  F01D11/08 ,  F01D25/12

Abstract: A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.

公开(公告)号：US10245637B2

公开(公告)日：2019-04-02

申请号：US15248235

申请日：2016-08-26

Applicant: United Technologies Corporation

Inventor： John Joseph Marcin ,  Dilip M. Shah ,  Carl R. Verner ,  Albert Rabinovich ,  Weiduo Yu ,  Thomas N. Slavens

IPC: B22D17/20

Abstract: Shot sleeves for high temperature die casting include a nickel-based alloy having a low modulus single crystal with axi-symmetric orientation.

公开(公告)号：US10208604B2

公开(公告)日：2019-02-19

申请号：US15140093

申请日：2016-04-27

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Brooks E. Snyder

IPC: F01D5/18 ,  B33Y80/00 ,  B33Y10/00

Abstract: An internally cooled component of a gas turbine engine is provided. The component may include a cooling passage at least partially defined by a first wall and a second wall with a first pedestal extending from the first wall to the second wall. The first pedestal may have a chevron geometry. A second pedestal may extend from the first wall to the second wall and also have a chevron geometry. A gap may be defined by the first pedestal and the second pedestal with the gap oriented between the first pedestal and the second pedestal.