Accession Number : AD0718291

Title :   Optimum Cycle Parameters for Turbofan Engines,

Corporate Author : ROYAL MILITARY COLL OF CANADA KINGSTON (ONTARIO) DEPT OF MECHANICAL ENGINEERING

Personal Author(s) : Moffatt,W. C.

Report Date : 16 JAN 1970

Pagination or Media Count : 8

Abstract : The paper presents 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. The 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. The effects of differing gas properties in different portions of the engine are included in the analysis. (Author)

Descriptors :   (*TURBOFAN ENGINES, OPTIMIZATION), PRESSURE, COMPRESSORS, THRUST, MATHEMATICAL ANALYSIS, CANADA

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE