Performance Analysis of an Aircraft Gas Turbine Engine using Particle Swarm Optimization

Abstract

A turbo fan engine performance analysis and the optimization using particle swarm optimization(PSO) algorithm have been conducted to investigate the effects of major performance design parameters of an aircraft gas turbine engine. The FJ44-2C turbofan engine, which is widely used in the small business jet, CJ2 has been selected as the basic model. The design parameters consists of the bypass ratio, burner exit temperature, HP compressor ratio, fan inlet mass flow, and nozzle cooling air ratio. The sensitivity analysis of the parameters has been evaluated and the optimization of the parameters has been performed to achieve high net thrust or low specific fuel consumption.

Optimization of energy and exergy parameters for a conceptual after burning turbojet engine

“…It is well known that on the contrary to turbofan engine, turbojet engines generate high thrust from exhaust gases with high speed. The basic working principle of turbojet engine are Turbofan Energy/Exergy [18] Turbofan Energy/Environment/ Enviroeconomic [19] Turbojet Energy/Exergy [20] Turbojet Energy/optimization [21] Turbofan Performance/ optimization [22] Turbojet Performance/ optimization [23] Turbojet Performance/ optimization [24] Turbojet Energy/Exergy/ optimization [25] Turbojet with afterburner Energy/Exergy [13] Turbojet with afterburner Energy/Exergy [14] Turbojet with afterburner Energy/Exergy/ optimization Present study to perform performance analysis for TJEAB at sea level condition-zero Mach.…”

“…They expressed that inlet and outlet geometry parameters can be modified to reduce fuel and decreasing of turbine blade temperature also leads to reduce fuel flow while keeping nominal thrust value. Choi and Sung [22] investigated optimum ranges of several design parameters of small-scaled turbofan engine for maximum net thrust and minimum SFC employing particle swarm optimization. The authors expressed that SFC of the FJ44-2C turbofan engine could be decreased up to 11 % by optimum variables of BPR and HPC PR.…”

Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm

“…[4][5][6][7][8][9][10]. In addition, optimization problems related with gas turbine engine performance have been studied in literature in many cases [11][12][13][14][15][16][17][18][19][20][21][22]. Most of these studies focused on "engine only" and without aircraft considerations (effect on gross weight, performance, total fuel weight etc.).…”

Energy and Exergy Analysis and Optimization of Turbofan Engine-TF30-P414

“…For these two reasons, the turbine can be run. Hence, it discharges at the nozzle, the thrust force is generated due to the velocity and pressure at the nozzle output and output surface area [1][2][3].…”