Персона: Фролов, Сергей Михайлович
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Институт лазерных и плазменных технологий
Стратегическая цель Института ЛаПлаз – стать ведущей научной школой и ядром развития инноваций по лазерным, плазменным, радиационным и ускорительным технологиям, с уникальными образовательными программами, востребованными на российском и мировом рынке образовательных услуг.
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- ПубликацияТолько метаданныеDirect Numerical Simulation of Turbulent Combustion of Hydrogen-Air Mixtures of Various Compositions in a Two-Dimensional Approximation(2019) Basevich, V. Ya.; Belyaev, A. A.; Frolov, F. S.; Frolov, S. M.; Фролов, Сергей МихайловичA technique of two-dimensional direct numerical simulation of turbulent flame propagation in reacting gas mixtures under stationary homogeneous isotropic turbulence conditions is proposed. This technique is based on a detailed kinetic mechanism of combustion of a multicomponent mixture and uses no fitting parameters. It is applied to the calculation of turbulent combustion of a hydrogen-air mixture. A condition is proposed to compare the results of two-dimensional calculations (dependences of flame propagation velocity on turbulence intensity) with the data of actual three-dimensional experiments. The obtained agreement between the calculated and measured dependences confirmed the validity of the proposed condition. The effects of pressure on the flame propagation velocity were considered. The calculated concentrations of the active reaction centers-hydroxyl (OH) and H and O atoms-in turbulent flame are lower than those in laminar flame, which also agrees with experimental results.
- ПубликацияТолько метаданныеDeflagration-to-Detonation Transition in Air Mixtures of Polypropylene Pyrolysis Products(2019) Zvegintsev, V. I.; Bilera, I. V.; Kazachenko, V. M.; Shamshin, I. O.; Frolov, S. M.; Aksenov, V. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович© 2019, Pleiades Publishing, Ltd.Abstract: A new method to determine fuel detonability has been proposed, which is based on measuring the length and time of a deflagration-to-detonation transition (DDT) in a calibration pulsed-detonation wind tunnel (CPDWT). The fuel was polypropylene granules (PG). A test stand was designed and built, which included the CPDWT and a gas generator to obtain PG pyrolysis products (PGPP) at a decomposition temperature to 800°C. Experiments for studying DDT in PGPP–air mixtures were carried out. It was shown that the detonability of PGPP is close to that of a stoichiometric mixture of autogas liquefied petroleum gas with air under normal conditions.
- ПубликацияТолько метаданныеHow to utilize the kinetic energy of pulsed detonation products?(2019) Smetanyuk, V. A.; Gusev, P. A.; Nabatnikov, S. A.; Frolov, S. M.; Koval, A. S.; Фролов, Сергей Михайлович; Коваль, Алексей Сергеевич© 2018 Elsevier Ltd The possibility of utilizing the kinetic energy of detonation products by a pulse turbine of the simplest water-wheel-like design during the implementation of the Zel'dovich thermodynamic cycle with pulse detonation combustion of fuel is investigated computationally and experimentally. The coefficients of utilization of the momentum and kinetic energy of detonation products in the pulse turbine with unoptimized mass and dimensions are found to be as low as 8%–16%. To improve the efficiency of the pulse turbine, it is necessary to take measures for eliminating unnecessary reflections of shock waves, to select the optimal mass and dimensions of the turbine rotor and the number of blades, to profile the blades and to select the optimal angle of attack, to optimize the size of the lateral gap between the rotor and the housing, and to select the optimum location of the exhaust duct. It is expected that the efficiency of a combined cycle including the optimized pulse turbine and conventional gas and/or steam turbines attached to the exhaust duct could be higher than the efficiency of a conventional hybrid cycle by at most 9%.
- ПубликацияТолько метаданныеThree-Dimensional Direct Numerical Simulation of Turbulent Combustion of Hydrogen-Air Mixtures in a Synthetic Turbulent Field(2019) Basevich, V. Y.; Belyaev, A. A.; Ivanov, V. S.; Medvedev, S. N.; Frolov, S. M.; Фролов, Сергей Михайлович© 2019, Pleiades Publishing, Ltd.Abstract: In this paper, we propose a method of three-dimensional direct numerical simulation of turbulent flame propagation in gas-reacting mixtures under stationary, homogeneous, and isotropic turbulence conditions. This method is based on the detailed kinetic mechanism of combustion of a multicomponent mixture, does not contain any adjustable parameters, and is applied to the calculation of turbulent combustion of fuel-lean hydrogen–air mixtures. The calculated propagation speeds of the turbulent flame are in satisfactory agreement with the measured values. The calculated concentrations of the reaction active centers, such as OH, H, and O, in a turbulent flame are lower than those in a laminar flame, which also agrees with the experimental results.
- ПубликацияТолько метаданныеAir-breathing pulsed detonation thrust module: Numerical simulations and firing tests(2019) Zangiev, A. E.; Frolov, S. M.; Aksenov, V. S.; Ivanov, V. S.; Shamshin, I. O.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович© 2019 Elsevier Masson SAS The air-breathing pulsed detonation thrust module (TM) for an aircraft designed for a subsonic flight at a speed of up to 120 m/s when operating on a standard aviation kerosene was developed using the analytical estimates and parametric multivariant three-dimensional (3D) calculations. The TM consists of an air intake with a check valve, a fuel supply system, a prechamber-jet ignition system and a combustion chamber with an attached detonation tube. An experimental sample of TM was fabricated, and its firing tests were carried out on a test rig with a thrust-measuring table. In firing tests, TM characteristics are obtained in the form of dependencies of effective thrust, aerodynamic drag and fuel-based specific impulse on fuel consumption at different speeds of the approaching air flow. It has been experimentally shown that the fuel-based specific impulse of the TM reaches 1000-1200 s, and the effective thrust developed by it reaches 180–200 N.