Patent ID: 7647761
Filing Date: 2010-01-19
Classification: F01D,F02C,F05D,F16C,Y02T

Abstract:
1. A system for deicing the nose cone of an aircraft turbojet, said turbojet having a bearing which supports, in rotation and in thrust, a hollow low pressure compressor shaft of axis Z-Z of the engine, said low-pressure compressor shaft having slots and inter-slot spaces, two slots being separated by an inter-slot space, said bearing being lubricated with oil by two nozzles located outside the compressor shaft, said system comprises: a feed tube fastened to the nose cone of the engine, said feed tube connecting the low-pressure compressor shaft to the engine nose cone and having a radius r; a skin lining the wall of the engine nose cone, leaving a passage for circulation of the oil; a plurality of radial oil-return tubes placed between the most eccentric part of the skin relative to the Z-Z axis and the bearing, for returning the oil to the bearing; and a centrifugal oil recovery scoop provided between the bearing and the low-pressure shaft, wherein, when one of said nozzles faces one of said slots, oil passes through said slot toward said nose cone, wherein, when one of said nozzles faces one of said inter-slot spaces, oil is reflected by said inter-slot space and picked up by the centrifugal scoop and directed under effect of a centrifugal force toward channels for lubricating said bearing, and wherein a return of the oil into the bearing is located at a distance R from the Z-Z axis larger than the radius r of the feed tube.