公开(公告)号：US11022144B2

公开(公告)日：2021-06-01

申请号：US16361938

申请日：2019-03-22

Applicant: United Technologies Corporation

Inventor： Matthew Andrew Hough ,  John S. Tu ,  Stephen C. Harmon ,  Paul F. Croteau ,  Russell B. Hanson ,  Joshua C. Rathgeb

IPC: F04D29/54 ,  F01D9/02

Abstract: A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.

公开(公告)号：US20200300103A1

公开(公告)日：2020-09-24

申请号：US16361938

申请日：2019-03-22

Applicant: United Technologies Corporation

Inventor： Matthew Andrew Hough ,  John S. Tu ,  Stephen C. Harmon ,  Paul F. Croteau ,  Russell B. Hanson ,  Joshua C. Rathgeb

IPC: F01D9/02

Abstract: A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.

公开(公告)号：US10598382B2

公开(公告)日：2020-03-24

申请号：US14935076

申请日：2015-11-06

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  James B. Hoke ,  Monica Pacheco-Tougas ,  Alexander W. Williams

IPC: F23R3/16 ,  F23R3/00 ,  F23R3/06 ,  F23M5/08 ,  B64D27/10 ,  F02C7/18

Abstract: A liner associated with an engine of an aircraft is described. The liner includes a panel and an array of projections configured to enhance a cooling of the panel and distributed on at least part of a first side of the panel that corresponds to a cold side of the panel.

公开(公告)号：US20170254538A1

公开(公告)日：2017-09-07

申请号：US15062440

申请日：2016-03-07

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  James B. Hoke ,  David Kwoka ,  Jonathan Jeffery Eastwood

IPC: F23R3/00 ,  F02C3/04

CPC classification number: F23R3/002 ,  F05D2240/15 ,  F05D2260/201 ,  F23M5/00 ,  F23M5/04 ,  F23M5/08 ,  F23M5/085 ,  F23R3/005 ,  F23R3/04 ,  F23R3/06 ,  F23R2900/00005 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03044

Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.

公开(公告)号：US20170044985A1

公开(公告)日：2017-02-16

申请号：US15340353

申请日：2016-11-01

Applicant: United Technologies Corporation

Inventor： Paul K. Sanchez ,  Kalpendu J. Parekh ,  William A. Daniels ,  John S. Tu

IPC: F02C7/20 ,  F02K3/04 ,  F02C7/12

CPC classification number: F01D25/14 ,  F01D25/12 ,  F01D25/16 ,  F01D25/162 ,  F01D25/24 ,  F01D25/246 ,  F02C7/12 ,  F02C7/20 ,  F02K3/04 ,  F05D2220/36 ,  F05D2260/20

Abstract: A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid-turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid-turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.

Abstract translation: 涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器部分，与燃烧器流体连通的高压涡轮机，与高压涡轮机流体连通的低压涡轮机和位于 轴向在高压涡轮机和低压涡轮机之间。 中间涡轮机框架包括外框架壳体，内框架壳体和多个中空轮辐，其将负载从内框架壳体分配到外框架壳体。 轮辐是中空的，以允许冷却气流通过轮辐供应到内框架壳体。

公开(公告)号：US20160362993A1

公开(公告)日：2016-12-15

申请号：US15245798

申请日：2016-08-24

Applicant: United Technologies Corporation

Inventor： Paul K. Sanchez ,  John S. Tu ,  Kalpendu J. Parekh ,  William A. Daniels

IPC: F01D9/06 ,  F02C3/04 ,  F01D25/12 ,  F01D25/28 ,  F01D25/24

CPC classification number: F01D9/065 ,  F01D25/12 ,  F01D25/162 ,  F01D25/24 ,  F01D25/28 ,  F02C3/04 ,  F02C6/08 ,  F02C7/12 ,  F05D2240/14 ,  F05D2240/55 ,  F05D2260/20 ,  Y02T50/676

Abstract: A mid-turbine frame (MTF) for a gas turbine engine includes an inner manifold directing air to a turbine rotor of the gas turbine engine. The MTF includes an outer MTF case and an inner MTF case. The inner manifold of the MTF is located in the inner case of the MTF.

Abstract translation: 用于燃气涡轮发动机的中涡轮机架（MTF）包括将空气引导到燃气涡轮发动机的涡轮机转子的内部歧管。 MTF包括外部MTF情况和内部MTF情况。 MTF的内部歧管位于MTF的内部情况。

公开(公告)号：US20160195272A1

公开(公告)日：2016-07-07

申请号：US14971573

申请日：2015-12-16

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  Philip J. Kirsopp ,  David A. Litton ,  Mark F. Zelesky ,  Dennis M. Moura ,  Aaron S. Butler

IPC: F23R3/00 ,  C23C14/08 ,  C23C4/11 ,  C23C4/134 ,  F02C7/28 ,  C23C4/129 ,  C23C14/32 ,  F01D5/28 ,  F01D9/02 ,  C23C14/30 ,  C23C28/00

CPC classification number: F23R3/002 ,  C23C4/02 ,  C23C4/11 ,  C23C4/129 ,  C23C4/134 ,  C23C4/18 ,  C23C14/08 ,  C23C14/083 ,  C23C14/30 ,  C23C14/325 ,  F01D5/288 ,  F05D2230/90 ,  F23R3/007 ,  F23R2900/00018 ,  Y02E20/344 ,  Y02T50/672

Abstract: The present disclosure relates to methods for coating gas turbine engine components, such as combustor panels. In one embodiment, a method includes forming a first layer to a substrate to form a bond coat, and forming a second layer over the first layer. The second layer may be formed by a material having a thermal conductivity within the range of 4.45 to 30 Kcal/(m hoC). According to one or more embodiments, the first layer may be formed by at least one of a high velocity oxy-fuel (HVOF) source, an electric-arc source and low pressure plasma spraying. According to one or more embodiments, the second layer, and as a result a thermal barrier coating, may be formed by at least one of air plasma spraying, suspension plasma spraying, and electronic beam physical vapor deposition.

Abstract translation: 本公开涉及用于涂覆燃气涡轮发动机部件（例如燃烧器面板）的方法。 在一个实施方案中，一种方法包括将第一层形成至基底以形成粘合涂层，以及在第一层上形成第二层。 第二层可以由导热率在4.45至30Kcal /（m·hoC）范围内的材料形成。 根据一个或多个实施例，第一层可以由高速氧 - 燃料（HVOF）源，电弧源和低压等离子体喷涂中的至少一种形成。 根据一个或多个实施例，可以通过空气等离子体喷涂，悬浮等离子体喷涂和电子束物理气相沉积中的至少一种来形成第二层，并由此形成热障涂层。

公开(公告)号：US10746403B2

公开(公告)日：2020-08-18

申请号：US14939619

申请日：2015-11-12

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  Steven W. Burd

IPC: F23M5/00 ,  F23R3/00 ,  F23M5/08 ,  F23R3/06

Abstract: A wall assembly that may be for a combustor of a gas turbine engine includes a liner having a hot face that defines a combustion chamber, an opposite cold face, and a plurality of effusion holes. A shell of the assembly is spaced outward from the cold face and includes a plurality of impingement holes each having a centerline orientated substantially normal to the cold face. A plurality of cooling member arrays of the liner each include a first plurality of members that may be pins projecting outward from the cold face to conduct heat out of the liner. Each array is spaced between adjacent effusion holes and is symmetrically orientated about the respective centerline.

公开(公告)号：US10386067B2

公开(公告)日：2019-08-20

申请号：US15266036

申请日：2016-09-15

Applicant: United Technologies Corporation

Inventor： San Quach ,  Scott A. Elliott ,  Robert M. Sonntag ,  John S. Tu ,  Anthony Van ,  Joseph J. Sedor ,  Robert Selinsky, Jr. ,  John J. Rup, Jr. ,  Neil B. Ridgeway ,  Gerard V. Cadieux ,  Jeffrey Leon ,  Monica Pacheco-Tougas ,  Lisa A. Jenkins ,  Lisa Tse ,  Andrew Cervoni ,  Frank J. Trzcinski

IPC: F23R3/00 ,  F23R3/06 ,  F02C7/12 ,  F23R3/44 ,  F23R3/50

Abstract: A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.

公开(公告)号：US09945251B2

公开(公告)日：2018-04-17

申请号：US14443818

申请日：2013-12-17

Applicant: United Technologies Corporation

Inventor： William Yeager ,  John S. Tu

IPC: F01D25/14 ,  F01D25/16 ,  F01D25/30 ,  F01D25/24 ,  F01D9/06 ,  F02C7/12 ,  F02C7/20

CPC classification number: F01D25/14 ,  F01D9/065 ,  F01D25/162 ,  F01D25/24 ,  F01D25/30 ,  F02C7/12 ,  F02C7/20 ,  F05D2250/185 ,  F05D2260/20 ,  Y02T50/675

Abstract: Cooling a turbine exhaust case (TEC) employed in an industrial gas turbine engine includes supplying cooling airflow from an outer diameter (OD) to an inner diameter (ID) cavity, supplying a secondary airflow having a pressure greater than the pressure of the cooling airflow to the ID cavity for mixing with the cooling airflow to provide a mixed airflow, and directing the mixed airflow in a serpentine cooling path that includes first directing the mixed airflow radially outward via hollow struts to an OD cavity, then radially inward via hollow fairings that surround the hollow struts.