Off-Design Modelling of a Turbo Jet Engine with Operative Afterburner  

作　　者：O. O. Ighodaro E. I. Aburime A. A. Erameh O. O. Ighodaro;E. I. Aburime;A. A. Erameh(Department of Mechanical Engineering, State University of Benin, Benin City, Nigeria;Department of Chemical Engineering, University of Benin, Benin City, Nigeria;Department of Mechanical Engineering, Igbinedion University, Okada, Nigeria)

机构地区：[1]Department of Mechanical Engineering, State University of Benin, Benin City, Nigeria [2]Department of Chemical Engineering, University of Benin, Benin City, Nigeria [3]Department of Mechanical Engineering, Igbinedion University, Okada, Nigeria

出　　处：《Open Journal of Energy Efficiency》2022年第3期88-107,共20页能源效率（英文）

摘　　要：Gas turbines are considered as one of the leading internal combustion engines in modern air transportation due to its favourable power to weight ratio and its continuous combustion process. Recent research focus has been concerned with performance improvements aimed at reduced fuel consumption and hence reduced impact on the environment. This study is aimed at using theoretical and computational methods to model the operation and performance a turbojet gas turbine engine. The commercial software GasTurb13 was used for the theoretical simulation while Microsoft Excel was used for the analytical study. GasTurb13 solved the model using pseudo-perfect gas models i.e. component maps since the specific gas ratio could not be inputted into the solver. The effect of changes in the Mach number and altitude on the engine performance was studied. Also the effect of changes in the compressor pressure ratio, the turbine inlet temperature and the afterburner exit temperature were also studied. Results obtained showed the optimum pressure ratio at maximum thrust constraint to be 16.78 for the turbojet engine operating at Mach number (Ma) = 0.8 and altitude = 10,000 m, Turbine inlet temperature (TIT) = 1200 K and Afterburner exit temperature = 1800 K.Gas turbines are considered as one of the leading internal combustion engines in modern air transportation due to its favourable power to weight ratio and its continuous combustion process. Recent research focus has been concerned with performance improvements aimed at reduced fuel consumption and hence reduced impact on the environment. This study is aimed at using theoretical and computational methods to model the operation and performance a turbojet gas turbine engine. The commercial software GasTurb13 was used for the theoretical simulation while Microsoft Excel was used for the analytical study. GasTurb13 solved the model using pseudo-perfect gas models i.e. component maps since the specific gas ratio could not be inputted into the solver. The effect of changes in the Mach number and altitude on the engine performance was studied. Also the effect of changes in the compressor pressure ratio, the turbine inlet temperature and the afterburner exit temperature were also studied. Results obtained showed the optimum pressure ratio at maximum thrust constraint to be 16.78 for the turbojet engine operating at Mach number (Ma) = 0.8 and altitude = 10,000 m, Turbine inlet temperature (TIT) = 1200 K and Afterburner exit temperature = 1800 K.

关 键 词：Turbo Jet Engine MODELLING SIMULATION OFF-DESIGN 

分 类 号：O55[理学—热学与物质分子运动论]