Optimum Design of Turboprop Engines Using Genetic Algorithm

摘要

TURBOPROP engines came intowide usewith a need for highernthrust levels and reduced fuel consumption at relatively lownflight speeds. However, their development has to be reconsiderednbecause they were quite modest. Higher compressor pressure ratiosn(CPRs) and turbine inlet temperatures (TITs) are still difficult tonachieve, owing to small blades in the rear stages of the compressornand the turbine which do not allow using sophisticated cooling techniques. Morris [1] showed that if size effects were ignored, anCPR in excess of 30 and a TIT of 1700 K could be reached. Brooksnand Hirschkron [2] arrived at a CPR of 17–20 and a TIT of 1535–n1590 K, based on turboprops for commuter aircraft.