OPTIMUM CYCLE PARAMETERS FOR TURBOFAN ENGINES

Abstract

Closed-form solutions for optimum compressor pressure ratio, bypass ratio and fan pressure ratio, given the turbine inlet temperature, component efficiencies and flight Mach number for a turbofan engine. In addition a simple procedure is outlined for obtaining the optimum combination of these quantities and a sample calculation is included. Optimum condition is defined as that which maximizes the specific thrust (thrust per pound per second of air flow through the gasifier) of the engine. Effects od differing gas properties in different portions of the engine are included in the analysis.