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 decreased 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 the shape optimization procedure for turbine blade with air injection. Our procedure is based on the gradient method, and composed of some elements, including CFD, geometry modification and design point arrangement, in which design points are automatically clustered around the complicated surface. The validity of our approach is demonstrated by applying the geometry optimization to 2 types of turbine blade with different injection.
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