The dynamical model of the fuel-rate to thrust of a laboratory turbo reactor engine is experimentally identified. By applying recursive least squares identification several linear models corresponding to various operating conditions are obtained. In addition, the analysis of the characteristics of the engine shows the presence of a hysteresis loop. These models are combined in order to form a nonlinear dynamical model of the process. The resulting nonlinear model captures the dynamics over the whole operating range of the engine. The results are validated through real time experimental tests. Although there are several reports on gas-turbo-engine identification, models of the fuel-ratio to thrust dynamics are not commonly reported.