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Kazan, Russia

Mikheev N.I.,Akademenergo | Kochetkov A.O.,OAO Kazanskoe OKB Soyuz
Russian Aeronautics

A method for shaping a supersonic part of a compact multinozzle cluster of a solid propellant rocket engine (SPRE) with out-of-round nozzles integrated into the common bell mouth is proposed. Also presented is an approach to evaluation of basic components of the total thrust impulse losses. © Allerton Press, Inc., 2010. Source

Guzachev D.S.,Kazan State Technical University | Kratirov D.V.,Kazan State Technical University | Zorin V.A.,Scientific Research Institute of Polymer Materials | Mikheev N.I.,Akademenergo
Russian Aeronautics

The method of analyzing the small-size rocket liftoff is presented. Under consideration is a system that consists of a rocket with an operating rocket engine, a launch tube, and an operating gas generator mounted in the tube under the rocket. The liftoff parameters including the rocket motion velocity inside the tube and the loads applied are calculated. The calculated and experimental data were compared and their adequate agreement is presented with respect both dynamics of rocket impulse-reaction liftoff from the launch tube and the launch velocity. © Allerton Press, Inc., 2011. Source

Kirsanov Yu.A.,Kazan State Power Engineering University | Nazipov R.A.,Akademenergo | Ivanova E.I.,Akademenergo
Russian Aeronautics

A technique of designing a heat exchanger with porous inserts that is the development of the classical method for thermal design of recuperative finned heat exchangers is presented. A criterion equation was suggested to calculate the effective length of a rib, which is equivalent to a porous insert; the given equation takes into account the influence of the heat carriers flow regime, their thermo-physical properties, geometrical and thermo-physical parameters of porous inserts. Using a hot water calorifer as an example, we compared the thermal design techniques as well as the mass-dimensional indicators and heat and power effectiveness of the heat exchanger with porous inserts with similar characteristics of a standard plate-type one. © 2013 Allerton Press, Inc. Source

Zaripov D.I.,Akademenergo | Mikheev N.I.,Akademenergo | Dushin N.S.,Akademenergo
Russian Aeronautics

In this paper, a technique for simulation of the space-time flow parameters in branched channels under transient boundary conditions is presented. The technique is based on the solution of one-dimensional nonstationary equations of gas dynamics. We suggest the conditions of channel junction with regard for distinctive features of a fluid flow in the adjacent region and compare the data on the flow simulation in the channel with a lateral branch by using one-dimensional and three-dimensional models. Comparing the data obtained with the experimental results, we show that the technique being suggested adequately simulates the real processes in the branched channels. © 2013 Allerton Press, Inc. Source

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