公开(公告)号：US20160195273A1

公开(公告)日：2016-07-07

申请号：US14972208

申请日：2015-12-17

Applicant: United Technologies Corporation

Inventor： Steven W. Burd ,  John S. Tu

IPC: F23R3/00 ,  F23R3/06

Abstract: A combustor includes a combustion chamber and a combustor wall that at least partially bounds the combustion chamber. The combustor wall includes a first side that faces the combustion chamber and a second side that faces away from the combustion chamber. The second side includes an array of geometric surface features for thermal transfer. A metallic coating is disposed on at least a portion of the second side of the combustor wall.

Abstract translation: 燃烧器包括至少部分地限定燃烧室的燃烧室和燃烧器壁。 燃烧器壁包括面向燃烧室的第一侧和面向燃烧室的第二侧。 第二面包括用于热转印的几何表面特征阵列。 金属涂层设置在燃烧器壁的第二侧的至少一部分上。

公开(公告)号：US20160025342A1

公开(公告)日：2016-01-28

申请号：US14773990

申请日：2014-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nurhak Erbas-Sen ,  James B. Hoke ,  John S. Tu ,  Monica Pacheco-Tougas

IPC: F23R3/00 ,  F02C7/18

CPC classification number: F23R3/002 ,  F02C7/18 ,  F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.

Abstract translation: 根据本公开的一个公开的非限制性实施例的用于燃气涡轮发动机的燃烧器的衬套组件包括具有多个索环冷却通道的索环。

公开(公告)号：US20140137534A1

公开(公告)日：2014-05-22

申请号：US14166320

申请日：2014-01-28

Applicant: United Technologies Corporation

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

IPC: F01D25/14

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，以及位于轴向 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：US20140102106A1

公开(公告)日：2014-04-17

申请号：US13649581

申请日：2012-10-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Timothy S. Snyder ,  John S. Tu

IPC: F02C1/00

CPC classification number: F23R3/002 ,  F23R3/04 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A bulkhead panel is disclosed. The bulkhead panel may comprise a body having a body having a front surface and an opposite back surface, a fuel nozzle opening in the body and communicating through the front and back surfaces, and a plurality of effusion holes disposed in at least one row that surrounds and is generally concentric to the fuel nozzle opening. Each effusion hole may extend from the back surface to the front surface at an incline angle. Each effusion hole may be positioned at a clock angle from a reference line radially extending from a center of the fuel nozzle opening through a center of the effusion hole.

Abstract translation: 公开了一种隔板。 舱壁板可以包括具有主体的主体，该主体具有前表面和相对的后表面，在主体中的燃料喷嘴开口并通过前表面和后表面连通，并且多个排出孔设置在至少一排中， 并且通常与燃料喷嘴开口同心。 每个渗出孔可以以倾斜角从后表面延伸到前表面。 每个渗出孔可以从从燃料喷嘴开口的中心径向延伸穿过渗出孔的中心的参考线以时钟角定位。