PRELIMINARY DESIGN AND PERFORMANCE ANALYSIS OF THE TURBOSHAFT ENGINE

Abstract

This project is aimed to determine and study the altitude and speed characteristics of the turboshaft engine suitable for helicopter applications, about specific fuel consumption and power available when operated at off-design condition and non-standard flight conditions, and that through a preliminary engine design. Initially, the design parameters were obtained by an existing Russian engine specifications (TV3-117-VMA series (2)). Then the parametric cycle were studied at on-design condition to specify air and gas properties at all sections of the engine. Graphs were plotted showing the variation of the properties along the engine. Then the flow through the machine and the results from the components study were considered, to determine the major dimensions of the engine, turbine and compressor number of stages. By using the computer program Autocad, the final configuration of the engine were drafted. At the end, the performance cycle were analyzed when operated at off—design condition and non-standard flight conditions by range the temperature from (-50-50 〖ᵒC〗^ ) for every specified altitude to 3000 m. finally the altitude and speed characteristic of the engine performance were determined at design condition and off-design condition, and represented by graphs and discussed. As a result, the resulting configuration of the engine has the same components dimensions and descriptions of the actual engine . Also the engine performance characteristics shows that the variation in engine specific fuel consumption and power output have a reduction sense when increasing altitude temperature andMach number, and vice versa.