Optmizaton And Analysis Of Axial Compressor Blade

Cascades are the basic unit of heat-work conversion in turbomachinery, and therefor its aerodynamic design theory and methodology have been the key subject in the area of turbomachinery aerothermodynamics all over the world. With the rapid development of computational fluid dynamics and optimization algorithm, the optimization techniques of turbomachinery have been developed speedly. But the aerodynamic optimization of the turbomachinery blade, especially the transonic compressor blade, is still a challenge area. In this paper, optimization design of the transonic compressor, rotor 37, is carried out for the minimization of the total pressure loss coefficient, based on the software of Design3D-a presentation of the Numeca design and optimization enviroment of turbomachinery blades. These studies mainly consist of the following aspects:First, the detailed numerical simulation on the reference compressor is done, the numerical results agreed very well with the given experimental data, which ensures the computational reliability and establishes the base on following aerodynamic optimization work.Second, the parameterized blade is obtained by stacking four blade sections along the span(hub, 27.5%span, 63.4%span, and tip), with the help of Autoblade^TM Each blade section can be defined by the suction side and pressure side mode. Both suction and pressure sides are constructed in the form of a high degree Bezier Curve with respect to the camber line. And the camber line is parameterized by a four-order Bezier curve. This will also provide variables for the following optimization..Third, the optimization design of a three dimensional blade profile was carried out for the reference transonic compressor. And it is based on the method that consists of three dimensiona Navier-Stokes flow computation, mesh generated automatically, three dimensional blade section parameterization and genetic...