NDLI: Thermal barrier coating evaluation needs

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Thermal barrier coating evaluation needs

Content Provider	NASA Technical Reports Server (NTRS)
Author	Miller, Robert A. Brindley, William J.
Copyright Year	1990
Description	A 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.
File Size	4657654
Page Count	9
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19910006077
Archival Resource Key	ark:/13960/t5v74bj9h
Language	English
Publisher Date	1990-01-01
Access Restriction	Open
Subject Keyword	Metallic Materials Nondestructive Tests Thermal Control Coatings Cooling Marine Propulsion Diesel Engines Gas Turbine Engines Thermal Insulation Durability Airfoils Aircraft Engines Operating Temperature Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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