Methods for preliminary estimation of turbofan engine weight

The preliminary estimation of the weight at the conceptual design stage of the turbofan engine is one of the most important stages in designing the turbine gas engines. Hence, in this paper, the methods of preliminary estimation of the turbofan engine weight and then the parameters required for the implementation of each method are discussed. The statistical society in which information about the weight of sixty-four turbofen is presented. Therefore, various methods for estimating the weight of a engine are used to calculate the weighted information obtained from the statistical processing, the comparison and the weight of the engines. Finally, the results of this experiment are compared to the actual engine weight. Based on the results obtained, among the various methods, the error rate is the lowest error in the NASA weight estimation method, which is about 4.8%. In the following, based on the diagrams obtained from this comparison, we examine the effect of different parameters on the weight of the turbofan engine (the initial estimation of the weight is based on the weight of the engine for the state in which the engine is constant but the design of the aircraft is changed.) In the initial estimation method the weight is based on the engine components, allowing the design and weight of each unit separately, hence the design of new engines more than it is used.