Сalculation of characteristics of atomization of liquid supplied at an angle to the flow direction and justification of adjusting the angle of the nozzle inclination relative to the gas flow

Abstract


In the context of solving the problem of increasing the efficiency of aircraft with the capability to fly at supersonic speed, an important aspect is to reduce the amount of fuel consumed in this flight mode, since this is the most promising direction in the development of aviation and these modes are accompanied by a number of significant problems that require joint efforts of leading organizations in this field. To solve the problem of expanding the range of use of the afterburner during the flight of the aircraft and reducing the amount of fuel required for this flight, we suggest the angle of inclination of the fuel supply should be adjusted relative to the direction of gas flow. The results of calculating the distribution of the afterburner fuel over the volume of the afterburner, supported by known experimental data, are presented. The analysis of characteristic points on the graphs of the dependence of the main variables is carried out and possible reasons for the peculiar characteristics of the working process in the afterburner in the case of changing the nozzle mounting angle are indicated. Possible options of controlling the working process in the afterburner are suggested.


About the authors

D. N. Teslya

Military Educational and Scientific Center of the Air Force Academy named after Professor N.E. Zhukovsky and Yu.A. Gagarin

Author for correspondence.
Email: patmi@rambler.ru

Russian Federation

Lecturer

S. V. Mityaev

Military Educational and Scientific Center of the Air Force Academy named after Professor N.E. Zhukovsky and Yu.A. Gagarin

Email: sergey2798@mail.ru

Russian Federation

Cadet

P. A. Drobyshev

Military Educational and Scientific Center of the Air Force Academy named after Professor N.E. Zhukovsky and Yu.A. Gagarin

Email: pot.gres.fy@gmail.com

Russian Federation

Cadet

References

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