公开(公告)号：US20190226343A1

公开(公告)日：2019-07-25

申请号：US15876579

申请日：2018-01-22

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco ,  Ricardo Trindade ,  Dominic J. Mongillo, JR.

IPC: F01D5/18 ,  F01D9/04

Abstract: Components for gas turbine engines are provided. The components include a hot external wall that is exposed to hot gaspath air when installed within a gas turbine engine, and an interior impingement wall, wherein the interior impingement wall defines a feed cavity and at least one impingement cavity is defined between the impingement wall and the external wall. The impingement wall includes a plurality of impingement holes that fluidly connect the feed cavity to the at least one impingement cavity, the external wall includes a plurality of film holes that fluidly connect the at least one impingement cavity to an exterior surface of the external wall, and wherein the only source of cooling air within the at least one impingement cavity is the feed cavity.

公开(公告)号：US20190078787A1

公开(公告)日：2019-03-14

申请号：US15699514

申请日：2017-09-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Benjamin D Bellows ,  Brandon W Spangler ,  David J Hyland ,  Dennis M Moura ,  James B Hoke ,  Ricardo Trindade ,  Stephen K Kramer ,  Steven Bruce Gautschi

IPC: F23R3/60 ,  F23R3/00

CPC classification number: F23R3/60 ,  F23R3/002 ,  F23R2900/03041

Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.

公开(公告)号：US10227927B2

公开(公告)日：2019-03-12

申请号：US14900730

申请日：2014-07-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Ricardo Trindade

IPC: F01D9/06 ,  F02C7/18 ,  F01D5/08 ,  F01D25/12 ,  F01D25/08 ,  F01D25/14 ,  F02C3/04 ,  F02C6/08

Abstract: In a featured embodiment, a gas turbine engine has a compressor section having a downstream rotor and a diffuser downstream of the compressor section. A combustor receives air downstream of the diffuser. A turbine section has at least one component to be cooled. A conduit is spaced from the diffuser and defines a cooling airflow path. The cooling airflow path is separate from an airflow downstream the diffuser, and passing to the combustor. The conduit passes cooling air to the component to be cooled.

公开(公告)号：US20180283687A1

公开(公告)日：2018-10-04

申请号：US15476431

申请日：2017-03-31

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Mark F. Zelesky ,  Atul Kohli ,  Dustin W. Davis ,  Ricardo Trindade ,  Steven Bruce Gautschi ,  Brandon W. Spangler ,  Trevor Rudy ,  Benjamin Bellows ,  Dave J. Hyland ,  James B. Hoke ,  Stephen K. Kramer ,  Dennis M. Moura

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F16B43/00 ,  F23R3/06 ,  F23R3/60 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.