Abstract:We have been investigating a new cycle concept for advanced propulsion system, in which hydrogen gas is directly injected from turbine blade surfaces and combusted within turbine blade passages. However, in the previous studies, we found that the aerodynamic performance of the blade is largely deteriorated due to the fuel injection. For the purpose of realizing our concept, turbine blade is required to have the adequate performance even with the hydrogen injection. In the present study, we develop a geometry o… Show more
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