抄録
Compressors in small gas turbines are usually composed of single stage centrifugal compressors, and their high efficiency and wide operation range are very important for the gas turbines. Although much research on fundamental technique have been reported by many researchers, there are questions to solve by practice in designing high pressure ratio machines. In this paper the authors relate the aerodynamic design and the experimental result of the advanced high pressure ratio centrifugal compressor for gas turbines.
