B-3 マイクロセラミックガスタービンの試験運転(ガスタービンシステムI,一般講演)

概要

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A series of operation tests of a micro ceramic gas turbine has been successfully carried out. The baseline machine is a small turbojet engine (J-850, Sophia Precision, Co., Ltd.) with a centrifugal compressor and a radial turbine. Inconel 713C alloy turbine rotor was replaced into a ceramic rotor (SN-235, Kyocera Corporation). The Inconel turbine nozzle and casing were replaced into the ceramic parts (SN-01, Otsuka Ceramics Co., Ltd.). The ceramic nozzle and case is supported by metal parts. Through the tests with ceramic nozzle, it transpired that one of the key technologies to develop ceramic gas turbines is the design of the interface between the ceramic components and the metallic components, because the difference between the coefficient of linear thermal expansion of ceramic and metal produces large thermal stress at their interface at the high temperature condition. A metal ring spring was inserted at the interface between ceramic and metal. This engine operated for 65 minitues at the condition that the turbine inlet temperature was over 1000℃.
社団法人日本ガスタービン学会の論文
2005-09-01