GB629044A - Improvements in or relating to compressors, particularly for use with aircraft powerplants - Google Patents

Abstract

629,044. Axial-flow compressors. UNITED AIRCRAFT CORPORATION. Aug. 21, 1947, No. 23178. Convention date, Oct. 30, 1946. [Classes 110(i) and 110(iii)] In an axial flow compressor, lubricating oil from the bearings is circulated through hollow guide blades in front of the first rotor. This serves to cool the oil and to prevent iceing in the compressor inlet. All the guide blades 12, Fig. 1, are hollow and cpen into inner and outer annular ducts 20, 18. Some of the blades are divided internally by partitions 56 to provide outward flow passages 58 for the oil. Oil is taken from a sump 28 by a pump 30 and delivered through a filter 32 to lubricating passages 34, 36, 38 of the bearing 24. Used oil passes through ports 46 and returns to a chamber 50 from which it is drawn by a second pump 52 and delivered to the passages 58 in some of the blades. The oil passes inwards through all the blades and is returned to the sump 28 by pipe 68. In another plant, the compressor shaft has a second bearing up-stream from the rotor and this bearing is supported by hollow streamlined struts which pass through'the annular air inlet duct. The oil from the bearings is passed inwards through the hollow struts and then to the inlet guide blades. The inner and outer ducts communicating with the hollow guide blades are divided by partitions into a number of segments so arranged that the oil passes inwards through some blades, outwards through others and finally inwards through the rest to reach the return to the sump.