Abstract
In order to demonstrate the applicability of an inverse cascade design method for blade design for an axial turbomachine, rotor and stator blades of a single stage axial fan are designed and tested. This design concept, proposed in the previous reports, is based on an inverse boundary layer method and an inverse cascade method. Overall performance and the rotor exit flow field are measured and are compared with a conventional fan designed using NACA 65 series cascade. The inversely designed fan obtains higher efficiency and a wider operating range compared with the conventional one. The midspan wake of the rotor blade in the trailing edge region reveals an extremely low velocity defect, a low wake shape factor, and low momentum thickness. boundary layer separation on the rotor blade suction surface seems to be avoided and the losses are low. The experimental results show the validity of the practical aplication of the inverse design concept, especially for rotating blades.
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