Patent ID: 7685713
Filing Date: 2010-03-30
Classification: F05D,G06F,Y02T,Y10T

Abstract:
1. A method of designing adjacent transonic airfoils to minimize downstream shock induced flowfield disturbance in an engine having a rotational axis, each transonic airfoil having an adjacent airfoil, and further having a pressure surface, a suction surface, a predetermined airfoil exit mach number, an exit flow angle, a pressure side trailing edge wedge angle, a suction side trailing edge wedge angle, and a suction side throat angle, the method comprising the steps of: selecting an airfoil exit deviation angle, the airfoil exit deviation angle having a magnitude; determining a combined shock induced flowfield disturbance at a position that corresponds to a leading edge of a downstream airfoil, the combined shock induced flowfield disturbance resulting, at least in part, from a suction side shock and a reflected shock, the suction side shock being a shock that emanates from the airfoil trailing edge suction side, the reflected shock resulting from a cross passage shock that emanates from the airfoil trailing edge pressure side and reflects off an adjacent airfoil suction side; and varying the airfoil exit deviation angle until the combined shock induced flowfield disturbance at the position that corresponds to a leading edge of a downstream airfoil is minimized, wherein: