公开(公告)号：US20180073737A1

公开(公告)日：2018-03-15

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 ,  F23R3/44 ,  F02C7/12

CPC classification number: F23R3/002 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2300/611 ,  F23R3/06 ,  F23R3/44 ,  F23R3/50 ,  F23R2900/00005 ,  F23R2900/03045

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：US20160201913A1

公开(公告)日：2016-07-14

申请号：US14886973

申请日：2015-10-19

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  James B. Hoke ,  Monica Pacheco-Tougas ,  Timothy S. Snyder ,  Dennis M. Moura ,  Anthony Van

IPC: F23R3/06 ,  F23R3/00

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.

Abstract translation: 本公开的方面涉及一种用于包含在飞行器的衬套中的冷却设计特征，包括：多个成角度的孔，以及分开任何两个成角度孔的所有组合的至少一个通孔，其中所述至少一个 通孔以基本上垂直于衬套的表面的角度定向，并且其中多个成角度孔中的每一个不平行于至少一个通孔。

公开(公告)号：US20160131365A1

公开(公告)日：2016-05-12

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 ,  B64D27/10 ,  F02C7/18

Abstract: Aspects of the disclosure are directed to a liner associated with an engine of an aircraft. 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.

Abstract translation: 本公开的方面涉及与飞行器的发动机相关联的衬管。 该衬套包括一个面板和一组凸起，其被构造成增强面板的冷却并且分布在对应于面板的冷侧的面板的第一侧的至少一部分上。

公开(公告)号：US11236677B2

公开(公告)日：2022-02-01

申请号：US16413347

申请日：2019-05-15

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F02C7/28 ,  F02C7/32

Abstract: A diffuser case support structure 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. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.

公开(公告)号：US11175041B2

公开(公告)日：2021-11-16

申请号：US16598941

申请日：2019-10-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： San Quach ,  John S. Tu ,  Robert M. Sonntag ,  Robert Selinsky, Jr. ,  John J. Rup, Jr. ,  Anthony Van

IPC: F23R3/00

Abstract: A combustor panel of a combustor may include a combustion facing surface, a cooling surface opposite the combustion facing surface, and heat transfer pins extending from the cooling surface. A grouping of the heat transfer pins may include a metallic coating.

公开(公告)号：US20180038593A1

公开(公告)日：2018-02-08

申请号：US15228029

申请日：2016-08-04

Applicant: United Technologies Corporation

Inventor： San Quach ,  Brian T. Hazel ,  Kaitlin M. Tomeo ,  Robert Selinsky, JR. ,  Aaron S. Butler ,  John S. Tu ,  William F. Werkheiser ,  Jessica L. Serra

IPC: F23R3/00 ,  F02C3/04 ,  F02C7/24

Abstract: A heat shield panel for a gas turbine engine includes a substrate layer having a first substrate surface and a second substrate surface opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness therebetween. One or more thermally protective coating layers are applied to the first substrate surface of the substrate layer. The one or more coating layers have a constant coating layer thickness and the substrate layer thickness tapers along an axial length of the heat shield panel.

公开(公告)号：US09625151B2

公开(公告)日：2017-04-18

申请号：US13626285

申请日：2012-09-25

Applicant: United Technologies Corporation

Inventor： Jonathan M. Jause ,  Dennis John Duhamel ,  James B. Hoke ,  John S. Tu

IPC: F23R3/06 ,  F23R3/00

CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R2900/00005 ,  F23R2900/00012 ,  F23R2900/03042 ,  Y02T50/675 ,  Y10T16/05

Abstract: A combustor liner grommet is disclosed. The grommet may include a peripheral wall defining a hole in a combustor liner and further including at least one cooling air flow channel. The cooling air flow channel in the grommet wall may be a slot or a hole. The channel may increase cooling flow to the grommet and the combustor liner around the grommet to prevent cracking from heat stress.

公开(公告)号：US20160169515A1

公开(公告)日：2016-06-16

申请号：US14908751

申请日：2014-08-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John S. Tu ,  James P. Bangerter ,  Robert Sze ,  James B. Hoke ,  Monica Pacheco-Tougas

IPC: F23R3/06 ,  F23R3/00 ,  F02C7/18

CPC classification number: F23R3/06 ,  F02C7/18 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A combustor panel an increased cooling holes provided at at least one of a pair of circumferential edges, a leading edge, a trailing edge or a hole circumference. The increase may be defined as a reduction in spacing or an increase in density. In another feature, holes at the circumferential edges may extend outwardly to an outlet in alignment with rails.

Abstract translation: 燃烧器面板具有设置在一对周向边缘，前缘，后缘或孔圆周中的至少一个上的增加的冷却孔。 增加可以被定义为间隔的减小或密度的增加。 在另一个特征中，圆周边缘处的孔可以向外延伸到与轨道对准的出口。

公开(公告)号：US20150337682A1

公开(公告)日：2015-11-26

申请号：US14443818

申请日：2013-12-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William Yeager ,  John S. Tu

IPC: F01D25/14 ,  F01D25/30 ,  F01D25/24

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.

Abstract translation: 冷却在工业燃气涡轮发动机中使用的涡轮机排气箱（TEC）包括将冷却气流从外径（OD）提供给内径（ID）空腔，供应具有大于冷却气流压力的压力的二次气流 到ID空腔以与冷却气流混合以提供混合的气流，并且将混合气流引导到蛇形冷却路径中，其包括首先将混合气流径向向外经由空心支柱引导到OD空腔，然后经由空心整流罩径向向内 环绕中空支柱。

公开(公告)号：US20130192268A1

公开(公告)日：2013-08-01

申请号：US13753821

申请日：2013-01-30

Applicant: United Technologies Corporation

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

IPC: F01D25/24

CPC classification number: F02C7/20 ,  F01D25/12 ,  F01D25/14 ,  F01D25/16 ,  F01D25/162 ,  F01D25/24 ,  F01D25/246 ,  F02C7/12 ,  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.