Improving the efficiency of the powerplant of an unmanned aerial vehicle through the use of cryogenic fuel

The article is devoted to increasing the efficiency of the power plant of an unmanned aerial vehicle through the use of cryogenic fuel. It has been substantiated that the creation of a power plant is based on an integrated approach to the Aircraft Power Plant Fuel system and ensures a significant achievement of perfection indicators according to high-level criteria (fuel consumption per hour (kilometer), range, flight duration, etc.) Analysis of energetic properties of some types of aviation fuels showed that gas fuels in their properties are generally superior to liquid ones, except for one thing low density, which requires a large volume of fuel tanks. An unmanned aerial vehicle Tu-143 Reis (Flight) equipped with a pure turbojet engine TR3-117 was chosen as a prototype. The optimization problem of the study was solved. The task was to determine if an engine intended to run on kerosene could operate on propane according to the main parameters of the working process, provided that possible flight conditions were maintained. The obtained altitude and speed characteristics indicate that the conversion of engines from kerosene to cryogenic propane is possible without changing their design by modernizing the combustion chamber and individual elements of the automatic fuel metering system

Development of a new collector device for gas turbine engine afterburner

The paper presents an analysis of the peculiarities of operation of gas-turbine engines with an afterburner. The main shortcomings of the existing afterburners are described. The structural design of afterburners is analyzed. It is shown that the existing afterburners do not provide efficient control of the working process throughout the operational range of heights and speeds of flight. Methods of calculating the parameters of the working process organization in the afterburners are specified. The necessity to control the place and the angle of supply of fuel upstream of the flame stabilizer is proved. New operating factors are proposed for the system of automatic control of the afterburner. The use of new structural designs of collector devices incorporated in the afterburner is justified. These devices allow efficient control of the organization of the working process in them throughout the operational range of heights and speeds of flight. The classification of afterburners is specified and the advantages of gas-turbine engines incorporating afterburners with adaptive fuel supply collector devices are justified