| 摘要 |
A gas turbine engine (10) is provided with a plurality of shafts (18, 19, 20) interconnecting its compressor portions (11, 12, 13) with its turbine portions (15, 16, 17). Each shaft (18, 19, 20) is supported in the hotter part of the engine by electromagnetic bearings (26, 28, 32) and by rolling element bearings (24, 27, 29, 31, 33) in the remainder of the engine (10). The arrangement provides a simplified liquid lubrication system for the rolling element bearings (24, 27, 29, 31, 33) which reduces the likelihood of lubricant thermal degradation of the lubricant. <IMAGE> |
