The Influence of On-design Bypass Turbine Engine Parameters on Multipurpose Aircraft Missions Energy-consuming

In the article there was presented a quality assessment of parameters selection of bypass turbine engine for a multipurpose aircraft. It was assumed that the assessment criterion results from the energy-consumption of a flight. The criteria of energy-consumption range were defined as the relation of sum of energy supplied to the aircraft on the driven stages to the distance during a mission. The second criterion of unitary energy-consumption is defined as the relation of the movement energy-consumption to the product of the aircraft mass and the route during the elementary stage of the flight. With t he use of the already worked out models of the power unit (bypass turbine engine with jet mixer and afterburner) of an aircraft (already k nown mass and aerodynamic characteristics) there were determined the ranges of thrust which are indispensable for a flight and available for the engine at each stage of the mission: take off, climb, subsonic and supersonic flight and turn with different overload factor. On the example of three chosen aircraft missions (Lo-Lo-Lo, Hi-Lo-Hi and Hi-Hi-Hi) the models of mission energy-consumption were developed. For the accepted change ranges of the comparative cycle parameters of the turbine engine the run of energy-consumption was tested. It was stated that for the assumed data the most energy-consuming mission is Lo-Lo-Lo, wherefore the increase of the compression and the rate of bypass reduces the energy-consumption of the mission.