Requirements for increased power output and improved fuel economy demand higher turbine inlet temperature for gas turbine engines. The application of ceramic components in turbine material enables higher turbine operatingtemperature with no cooling techniques. However, the ceramic materials have several unfavorable properties, such as thebrittleness, the low reliability of the ceramic parts. In this study, the ceramic turbine wheel which had a tip diameter greaterthan 200mm was developed for the aircraft gas turbine engine. The design of ceramic turbine components is influenced by thecharacteristic material properties of ceramic. The rotational rig test was carried out and the engine test was demonstratedunder full load operating conditions. The successful testing of the ceramic turbine components in the aircraft gas turbineengine has been accomplished. The test results indicate that the ceramic turbine is capable of operating under the actual usecondition of the aircraft ceramic turbine engine.
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