Various refractory coating systems were evaluated for rocket nozzle applications by actual rocket test firings. A reference is noted which identifies failure mechanisms and gives results of the firing tests for 18 coating systems. Iridium, iridium-rhenium, and hafnium oxide-zirconium oxide coatings show most promising results

Peterson, D. A.

Winter, J. M.

English

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NASA TECH BRIEF 
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November 1970	 Brief 70-10634 
NASA Tech Briefs announce new technology derived from the U.S. space program. They are issued to encourage commercial 
application. Tech Briefs are available on a subscription basis from the Clearinghouse for Federal Scientific and Technical 
Information, Springfield, Virginia 22151. Requests for individual copies or questions relating to the TechBrief program may 
be directed to the Technology Utilization Division, NASA, Code UT, Washington, D.C. 20546. 
High-Temperature Oxidation and Erosion- Resistant Refractory Coatings 
Various refractory coating systems have been 
evaluated for rocket nozzle application by actual 
rocket test firings. A coating system consists of the 
refractory coating bonded to a particular substrate. 
The results of these tests may be of interest not only 
for applications in the severe environment imposed by 
the rocket firings, but also for other applications where 
high melting temperature, thermal stability, oxidation 
resistance and/or erosion resistance are required. 
Results of the firing tests for 18 such coating sys-
tems are presented in the reference noted below. 
Failure mechanisms are identified, and promising 
concepts for future developments are derived from the 
tests. Several of the coatings exhibited desirable char-
acteristics which could broaden their applicability. 
Among the coatings showing promising results were 
iridium, iridium-rhenium, and hafnium oxide-zir-
conium oxide. The iridium metal was particularly suc-
cessful in resisting oxidation. The bonding of the 
coatings to various substrates by the gas-pressure-
bonding technique was shown to be promising. 
Notes: 
1. The results of these tests may be of interest in 
tooling design for high pressure molding, for flu-
clear reactor liners, and for general applications 
requiring a high degree of oxidation resistance. 
The following documentation is available from: 
Clearinghouse for Federal Scientific 
and Technical Information 
Springfield, Virginia 22151 
Single document price $3.00 
(or microfiche $0.65) 
Reference: 
NASA-TN-D-4964 (N69-3348 1), Development 
of Improved Throat Inserts for Ablative 
Rocket Engines 
Technical qUestions may be directed to: 
Technology Utilization Officer 
Lewis Research Center 
21000 Brookpark Road 
Cleveland, Ohio 44135 
Reference: TSP70- 10634 
Patent status: 
No patent action is contemplated by NASA. 
Source: Donald A. Peterson and Jerry M. Winter 
Lewis Research Center 
(LEW-1122 1) 
Category 04 
This document was prepared under the sponsorship of the National 
Aeronautics and Space Administration. Neither the United States 
Government nor any person acting on behalf of the United -States
Government assumes any liability resulting from the use of the 
information contained in this document, or warrants that such use 
will be free from privately owned-rights.
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High-temperature oxidation and erosion-resistant refractory coatings

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