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Thermal barrier coating evaluation needsA 0.025 cm (0.010 in) thick thermal barrier coating (TBC) applied to turbine airfoils in a research gas turbine engine provided component temperature reductions of up to 190 C. These impressive temperature reductions can allow increased engine operating temperatures and reduced component cooling to achieve greater engine performance without sacrificing component durability. The significant benefits of TBCs are well established in aircraft gas turbine engine applications and their use is increasing. TBCs are also under intense development for use in the Low Heat Rejection (LHR) diesel engine currently being developed and are under consideration for use in utility and marine gas turbines. However, to fully utilize the benefits of TBCs it is necessary to accurately characterize coating attributes that affect the insulation and coating durability. The purpose there is to discuss areas in which nondestructive evaluation can make significant contributions to the further development and full utilization of TBCs for aircraft gas turbine engines and low heat rejection diesel engines.
Document ID
19910006077
Document Type
Conference Paper
Authors
Brindley, William J.
(NASA Lewis Research Center Cleveland, OH, United States)
Miller, Robert A.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1990
Subject Category
Metallic Materials
Report/Patent Number
NAS 1.15:103708
NASA-TM-103708
E-5596
Meeting Information
Meeting: Conference on Nondestructive Evaluation of Modern Ceramics
Location: Columbus, OH
Country: United States
Start Date: July 9, 1990
End Date: July 12, 1990
Sponsors: American Ceramic Society, American Society of Nondestructive Testing
Accession Number
91N15390
Funding Number(s)
PROJECT: RTOP 505-63-1A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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