Patent ID: 6134874
Filing Date: 2000-10-24
Classification: B01D,F02C,Y02T

Abstract:
In a radial intake gas turbine engine having a longitudinal axis, an annular compressor duct defined between an outer compressor duct wall and an inner compressor duct wall, wherein the improvement comprises:a bifurcated axially symmetric radial intake with an inward end in communication with the compressor duct and an outward end including a peripherally open inlet, the radial intake having:a continuous convex rear surface extending between a rear edge of the inlet and the outer compressor duct wall; anda discontinuous concave forward surface extending between a forward edge of the inlet and the inner compressor duct wall, the radial intake forward surface including: a bypass duct downstream of the inlet; and flow separator means, downstream of the bypass duct, for diverting a bypass air flow into the bypass duct;an annular bypass manifold in communication with the bypass duct;air pumping means, in communication with the bypass manifold, for evacuating air from the bypass manifold; andradial intake forward surface de-icing means for heating the radial intake forward surface.