What's inside?
The development and application of a three-dimensional inverse methodology in which the blade geometry is computed on the basis of the specification of static pressure loading distribution is presented. The methodology is based on the intensive use of computational fluid dynamics (CFD) to account for three-dimensional subsonic and transonic viscous flows.
The application of the method is explored using a transonic test case, NASA rotor 67. From an understanding of the dynamics of the flow in the fan in relation to its pressure loading distributions,simple guidelines can be developed for the inverse method in
order to weaken the shock formation.
In this publication, you will:
- Discover the design technics to redesign two NASA rotor 67 fan blades.
- See how to improve the overall quality of the flow aerodynamics and how to get larger working ranges with an efficiency of 0.6 per cent higher than the original fan at the design point.
- Understand why such an approach leads to a substantial reduction of the computational cost compared to the direct method.
