Strain tolerant corrosion protecting coating and spray method of application

A corrosion resistant coating for gas turbine engine includes a glassy ceramic matrix wherein the glassy matrix is silica-based, and includes corrosion resistant particles selected from refractory particles and non-refractory MCrAlX particles, and combinations thereof. The corrosion resistant partic...

Full description

Saved in:
Bibliographic Details
Main Authors WEIMER MICHAEL J, BOJANOWSKI BRYAN T, MURPHY JANE A, HAZEL BRIAN T, SKOOG ANDREW J
Format Patent
LanguageEnglish
Published 13.07.2010
Subjects
Online AccessGet full text

Cover

Loading…
More Information
Summary:A corrosion resistant coating for gas turbine engine includes a glassy ceramic matrix wherein the glassy matrix is silica-based, and includes corrosion resistant particles selected from refractory particles and non-refractory MCrAlX particles, and combinations thereof. The corrosion resistant particles are substantially uniformly distributed within the matrix, and provide the coating with corrosion resistance. Importantly the coating of the present invention has a coefficient of thermal expansion (CTE) greater than that of alumina at engine operating temperatures. The CTE of the coating is sufficiently close to the substrate material such that the coating does not spall after frequent engine cycling at temperatures above 1200° F.
Bibliography:Application Number: US20050311720