公开(公告)号：US10294823B2

公开(公告)日：2019-05-21

申请号：US15161742

申请日：2016-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon Spangler ,  David J. Candelori

IPC: F02C3/04 ,  F01D25/24 ,  F01D25/32 ,  F01D5/18 ,  F01D9/04 ,  F01D19/00 ,  F01D21/00 ,  F01D25/12

Abstract: A system for reducing debris in a gas turbine engine includes a component that defines a component cooling channel for receiving a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris evacuation door coupled to the casing and having an open state in which the debris can exit the casing and a closed state.

公开(公告)号：US20180230814A1

公开(公告)日：2018-08-16

申请号：US15433130

申请日：2017-02-15

Applicant: United Technologies Corporation

Inventor： Brandon Spangler ,  Dominic Mongillo

IPC: F01D5/18 ,  F01D9/06 ,  F01D9/04 ,  F01D25/12

Abstract: An airfoil may comprise an airfoil body having a leading edge, a trailing edge, an inner diameter end wall and an outer diameter end wall. A first cooling structure may be disposed within the airfoil body. The first cooling structure may comprise a first rib extending between the inner diameter end wall and the outer diameter end wall and may define a first radial passage configured to conduct a cooling airflow in a radial direction through the airfoil body. A second cooling structure may be disposed within the airfoil body. The second cooling structure may comprise a first baffle defining an axial passage configured to conduct the cooling airflow in an axial direction toward the trailing edge of the airfoil body.

公开(公告)号：US20170335722A1

公开(公告)日：2017-11-23

申请号：US15161807

申请日：2016-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David J. Candelori ,  Brandon Spangler

IPC: F01D25/32 ,  F01D9/04 ,  F01D25/00 ,  F01D25/12 ,  F01D11/08

CPC classification number: F01D25/32 ,  F01D9/041 ,  F01D11/08 ,  F01D19/00 ,  F01D25/005 ,  F01D25/12 ,  F05D2220/32 ,  F05D2260/202 ,  F05D2260/607 ,  F05D2300/17 ,  Y02T50/675

Abstract: A system for circumferentially distributing debris in a gas turbine engine includes a component that defines a component cooling channel that has an opening and is configured to receive a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris distribution surface positioned radially between the casing and the opening.

公开(公告)号：US20170335721A1

公开(公告)日：2017-11-23

申请号：US15161742

申请日：2016-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon Spangler ,  David J. Candelori

IPC: F01D25/32 ,  F01D21/00 ,  F02C3/04 ,  F01D5/18 ,  F01D25/12 ,  F01D9/04

CPC classification number: F01D25/32 ,  F01D5/187 ,  F01D9/041 ,  F01D19/00 ,  F01D21/003 ,  F01D25/12 ,  F01D25/24 ,  F02C3/04 ,  F05D2220/32 ,  F05D2260/202 ,  F05D2260/607 ,  F05D2260/85 ,  Y02T50/675

Abstract: A system for reducing debris in a gas turbine engine includes a component that defines a component cooling channel for receiving a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris evacuation door coupled to the casing and having an open state in which the debris can exit the casing and a closed state.

公开(公告)号：US10669861B2

公开(公告)日：2020-06-02

申请号：US15433130

申请日：2017-02-15

Applicant: United Technologies Corporation

Inventor： Brandon Spangler ,  Dominic Mongillo

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/04 ,  F01D9/06

Abstract: An airfoil may comprise an airfoil body having a leading edge, a trailing edge, an inner diameter end wall and an outer diameter end wall. A first cooling structure may be disposed within the airfoil body. The first cooling structure may comprise a first rib extending between the inner diameter end wall and the outer diameter end wall and may define a first radial passage configured to conduct a cooling airflow in a radial direction through the airfoil body. A second cooling structure may be disposed within the airfoil body. The second cooling structure may comprise a first baffle defining an axial passage configured to conduct the cooling airflow in an axial direction toward the trailing edge of the airfoil body.

公开(公告)号：US10316698B2

公开(公告)日：2019-06-11

申请号：US15161807

申请日：2016-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David J. Candelori ,  Brandon Spangler

IPC: F01D9/04 ,  F01D11/08 ,  F01D19/00 ,  F01D25/00 ,  F01D25/12 ,  F01D25/32

Abstract: A system for circumferentially distributing debris in a gas turbine engine includes a component that defines a component cooling channel that has an opening and is configured to receive a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris distribution surface positioned radially between the casing and the opening.