To provide a coating composition preventing the corrosion of turbine engine components.
A corrosion resistant coating (64) for gas turbine engine includes a glassy ceramic matrix (63) wherein the glassy matrix is silica-based, and includes corrosion resistant particles (65) selected from refractory particles and non-refractory MCrAlX particles, and combinations thereof. The corrosion resistant particles (65) are substantially uniformly distributed within the matrix (63), and provide the coating (64) with corrosion resistance. Importantly the coating (64) has a coefficient of thermal expansion (CTE) greater than that of alumina at engine operating temperatures. The CTE of the coating (64) is sufficiently close to the substrate material (60) such that the coating (64) does not spall after frequent engine cycling at temperatures above 648.9°C (1,200°F).
MURPHY JANE A
SKOOG ANDREW J
JP2002256452A | 2002-09-11 | |||
JP2002115084A | 2002-04-19 | |||
JPH0874068A | 1996-03-19 | |||
JP2002530525A | 2002-09-17 | |||
JPS5837146A | 1983-03-04 | |||
JPS6456880A | 1989-03-03 | |||
JPH07238353A | 1995-09-12 |
Hirokazu Ogura
Toshihisa Kurokawa
Arakawa Satoshi
Next Patent: SYSTEM FOR APPLYING COATING AND METHOD FOR APPLYING COATING