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Robust High Temperature Environmental Barrier Coating System for Ceramic Matrix Composite Gas Turbine Components using Affordable Processing Approach Project

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Release Date
9 April 2015
Modified Date
8 July 2015
Publishers
National Aeronautics and Space Administration
Keywords
active, glenn-research-center, project
Identifier
robust-high-temperature-environmental-barrier-coating-system-for-ceramic-matrix-composite-
Landing Page
http://techport.nasa.gov/view/17820
Maintainers
Gary Jahns gary.c.jahns@nasa.gov
Language
en-US

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Description

Research is proposed to demonstrate the use of advanced manufacturing techniques to enable the affordable application of multi-functional thermal / environmental barrier coatings (T/EBCs) having enhanced resistance to high temperature combustion environments. T/EBCs are envisioned to protect the surface of Si-based ceramics against moisture-assisted, oxidation-induced ceramic recession. Current T/EBC systems have been demonstrated in long time exposures at ~2400°F substrate temperatures. However, their use at elevated temperatures (i.e. 2700°F substrate temperatures) is limited by the low temperature stability and high diffusion activity of current T/EBC materials. One approach to increase the temperature capability of these systems is the incorporation of multi-layered T/EBC designs. In this Phase I effort, enhanced processing techniques will be employed to demonstrate the manufacture of robust T/EBC bond coat systems using a physical vapor deposition based processing approach which enables improved coating adhesion and advanced coating architectural, compositional and microstructural control, as well as non-line-of-sight (NLOS) deposition. Scaled processing approaches will then be used to demonstrate the deposition of high temperature capable T/EBC bond coats onto components of interest to gas turbine engine manufacturers. These bond coats will then be incorporated into full high temperature capable T/EBC systems planned in Phase II. Finally, concepts to enable the deposition of T/EBC bond coat systems on NLOS internal regions of hollow components will be investigated. This work will significantly aid the incorporation of Si-based ceramic components in gas turbine engines resulting in reduced weight and increased operating temperatures.

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