design of an axial transonic rotor by modified spanwise loading distribution

Improving the aerodynamic performance of the transonic fan in a turbofan engine can be beneficial for boththe fuel consumption and maneuverability of an airplane. deep insight into the supersonic aerodynamics isneeded for the simultaneous improvement of all operating parameters of a transonic rotor, including thepressure ratio, efficiency, and surge margin. a design method was developed for an axial transonic rotor byusing a combination of radial equilibrium theory, the free vortex method, and a distributed span-wisediffusion factor. the loading distribution obtained by this method was the highest in the hub section andgradually decreased in the tip section. to evaluate the method, a transonic rotor was designed using thegeometric parameters and operating conditions of nasa rotor 67. a code was developed to determine ageometry for the new rotor and to modify it. the code was coupled with a rans flow solver for 3dmodification of the new designed rotor. only standard multi- and double-circular arc airfoils were applied indifferent radial sections of the new rotor with no blade profile optimization. the results of the ransequations solution for the new designed rotor showed 1.5% higher efficiency, 3% higher pressure ratio, andmore than 1.5 times larger operating range in comparison to nasa rotor 67. the new designed method seemsto be an efficient approach that not only improved the efficiency and pressure ratio but also increased theoperating range of an axial transonic rotor.