COMBUSTOR FOR A GAS TURBINE ENGINE

A heat shield panel (68) for a gas turbine engine (10) includes a substrate layer (86) having a first substrate surface (76) and a second substrate surface (78) opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness (96)...

Full description

Saved in:
Bibliographic Details
Main Authors QUACH, San, TU, John S, WERKHEISER, William F, TOMEO, Kaitlin M, HAZEL, Brian T, SELINSKY, Robert, Jr, BUTLER, Aaron S, SERRA, Jessica L
Format Patent
LanguageEnglish
French
German
Published 31.03.2021
Subjects
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:A heat shield panel (68) for a gas turbine engine (10) includes a substrate layer (86) having a first substrate surface (76) and a second substrate surface (78) opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness (96) therebetween. One or more thermally protective coating layers (88) are applied to the first substrate surface of the substrate layer. The one or more coating layers have a constant coating layer thickness (92) and the substrate layer thickness tapers along an axial length of the heat shield panel.
Bibliography:Application Number: EP20170184794