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US08757974B2 Cooling circuit flow path for a turbine section airfoil 有权
涡轮机翼型的冷却回路流路

Cooling circuit flow path for a turbine section airfoil
Abstract:
A cooled airfoil includes an impingement rib having a multiple of openings which supply a cooling airflow from a cooling circuit flow path toward an airfoil leading edge. The multiple of openings are offset in the impingement rib opposite an outer airfoil wall which includes gill holes. Offsetting the multiple of openings opposite an outer airfoil wall which includes the gill holes focuses the cooling airflow across turbulators to increase the cooling airflow dwell time to increase the thermal transfer therefrom in higher temperature airfoil areas.
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