航空用エンジンのセラミックタービンと金属部品との接合部構造(熱工学,内燃機関,動力など)

概要

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The turbine inlet temperature of gas turbine engines becomes higher and higher to grow up the power in recent years. The high temperature properties of the ceramic materials offer the potential of higher turbine operating temperatures with no cooling techniques and therefore the ceramic components with higher temperature limits are becoming more attractive. In this study, a ceramic turbine disc is applied to an aircraft gas turbine engine. A tight fit configuration is generally taken for the joint structure between a ceramic turbine and a metal shaft. However, the constrain force is decreased due to the difference of the thermal expansion coefficient between ceramic and metal at the high temperature condition. This paper describes about the design method and the results of the mechanical tests for the joint structure. Furthermore, the ceramic turbine engine tests were demonstrated under full operating condition.
一般社団法人日本機械学会の論文
2003-02-25