公开(公告)号：US10808936B2

公开(公告)日：2020-10-20

申请号：US16020736

申请日：2018-06-27

Applicant: United Technologies Corporation

Inventor： Steven D Porter ,  John T Ols ,  Fumitaka Ichihashi

IPC: F23R3/50 ,  F23R3/06 ,  F23R3/00

Abstract: A heat shield panel for a gas turbine engine combustor may comprise a perimetrical rail extending at least partially around a perimeter of the heat shield panel and defining a main backside cavity, a plurality of air admittance holes, each air admittance hole extending along a hole axis, and a midrail dividing the main backside cavity into a first backside cavity and a second backside cavity, wherein at least a portion of the midrail is axially offset from at least one of the hole axes.

公开(公告)号：US20200003423A1

公开(公告)日：2020-01-02

申请号：US16020736

申请日：2018-06-27

Applicant: United Technologies Corporation

Inventor： Steven D Porter ,  John T Ols ,  Fumitaka Ichihashi

IPC: F23R3/50 ,  F23R3/06

Abstract: A heat shield panel for a gas turbine engine combustor may comprise a perimetrical rail extending at least partially around a perimeter of the heat shield panel and defining a main backside cavity, a plurality of air admittance holes, each air admittance hole extending along a hole axis, and a midrail dividing the main backside cavity into a first backside cavity and a second backside cavity, wherein at least a portion of the midrail is axially offset from at least one of the hole axes.

公开(公告)号：US10107118B2

公开(公告)日：2018-10-23

申请号：US14900737

申请日：2014-06-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John T Ols ,  Richard N Allen ,  Paul K Sanchez ,  Steven D Porter ,  Jonathan Lemoine

IPC: F01D11/02 ,  F01D9/04 ,  F01D5/08 ,  F01D11/00

Abstract: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.