Персона:
Аксенов, Виктор Серафимович

Организационные подразделения

Организационная единица

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.

Фамилия

Аксенов

Имя

Виктор Серафимович

Полная страница элемента

Результаты поиска

Теперь показываю 1 - 10 из 23

Только метаданные
Rocket Engine with Continuously Rotating Liquid-Film Detonation
(2020) Gusev, P. A.; Zelensky, V. A.; Evstratov, E. V.; Alymov, M. I.; Frolov, S. M.; Shamshin, I. O.; Aksenov, V. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
© 2018, © 2018 Taylor & Francis. The possibility of organizing a continuous-detonation combustion of a liquid fuel film in an annular combustor of a detonation liquid-propellant rocket engine has been demonstrated. The near-limit mode of the longitudinally pulsating “film” detonation and the continuous spinning “film” detonation modes with one and two detonation waves circulating in the annular gap of the combustor are recorded in the fire tests.
Только метаданные
Pulsed detonation hydroramjet: simulations and experiments
(2020) Avdeev, K. A.; Frolov, F. S.; Sadykov, I. A.; Tukhvatullina, R. R.; Frolov, S. M.; Aksenov, V. S.; Shamshin, I. O.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
© 2019, Springer-Verlag GmbH Germany, part of Springer Nature.A water transportation engine of a new type—a pulsed detonation hydroramjet (PDH)—has been designed, manufactured, and tested. The PDH is a pulsed detonation tube (DT) inserted in an open-ended water guide. The thrust is developed by shock-induced pulsed water jets periodically emanating from the water guide nozzle. Numerical simulations indicate that valveless and valved PDH models can produce thrust with the specific impulse on the level ranging from 600 to 2400 s. Test firings of PDH models of various designs with a 2-liter DT were carried out on a specially designed test rig, which provides the approaching water flow in the form of a submerged jet at a speed of up to 10 m/s. The measured average specific impulse of valveless and valved PDH models was on the level of 350–400 s when the first operation cycle was not considered. The measured values of the average thrust and specific impulse in the first operation cycle were shown to be always much higher than those in the subsequent cycles: In the tests, the average value of thrust in the first cycle varied from 300 to 480 N, and the value of the specific impulse varied from 960 to 2690 s, which indicates the potential of increasing the thrust performance.
Только метаданные
Detonability of fuel–air mixtures
(2020) Zvegintsev, V. I.; Bilera, I. V.; Kazachenko, M. V.; Shamshin, I. O.; Frolov, S. M.; Aksenov, V. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
© 2020, Springer-Verlag GmbH Germany, part of Springer Nature.A new experimental method for evaluating the detonability of fuel–air mixtures (FAMs) based on measuring the deflagration-to-detonation (DDT) run-up distance and/or time in a standard pulse detonation tube (SDT) is used to rank gaseous premixed and non-premixed FAMs by their detonability under substantially identical thermodynamic and gasdynamic conditions. In the experiments, FAMs based on hydrogen, acetylene, ethylene, propylene, propane–butane, n-pentane, and natural gas of various compositions, as well as FAMs based on the gaseous pyrolysis products of polypropylene (PP), are used: from extremely fuel-lean to extremely fuel-rich at normal temperatures and pressures. The concept of equivalent FAMs exhibiting the same or similar detonability under the same conditions is proposed. Equivalent FAMs can be used for predictive physical modeling of detonation processes involving FAMs of other fuels. The ranking of FAMs in terms of their relative detonability allows choosing a propylene FAM for physical modeling of the operation process in the PP-fueled solid-fuel ramjets operating on detonative combustion.
Только метаданные
Deflagration-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.
Только метаданные
Pulsed Detonation Hydroramjet: Design Optimization
(2022) Frolov, S. M.; Avdeev, K. A.; Aksenov, V. S.; Frolov, F. S.; Sadykov, I. A.; Shamshin, I. O.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
A new type of marine transportation engine, the pulsed detonation hydroramjet (PDH), which was first designed, manufactured, and tested by the present authors, has been further investigated in terms of the potential improvement of its propulsive performance. PDH is composed of a pulsed detonation tube (DT) inserted in the flow-through water guide. Thrust is developed by shock-induced pulsed water jets which are periodically emitted from the water guide nozzle. The measured values of the time-averaged thrust and specific impulse in the first operation cycle were shown to always be considerably higher than those in subsequent cycles, indicating the possibility of improving the overall thrust performance. The present manuscript is aimed at clarifying the reasons for, and eliminating, cycle-to-cycle variability during PDH operation, as well as optimization of the PDH design. An experimental model of the PDH with an optically transparent water guide was designed and manufactured. The cycle-to-cycle variability was found to be caused by the overexpansion of gaseous detonation products in the DT due to the inertia of water column in the water guide. Gas overexpansion caused the reverse flow of the gasвЂ“water mixture which filled the water guide and penetrated the DT, thus exerting a strong effect on PDH operation. To eliminate the cycle-to-cycle variability, a new PDH model was developed, manufactured, and tested. The model was equipped with a passive flap valve and active rotary valve and operated on the stochiometric propaneвЂ“oxygen mixture. Its test firing showed that use of the valves made it possible to eliminate the cycle-to-cycle variability and nearly double the time-averaged thrust and specific impulse reaching 40 N and 550 s, respectively.
Только метаданные
Interaction of Shock Waves with Water Saturated by Nonreacting or Reacting Gas Bubbles
(2022) Frolov, S. M.; Avdeev, K. A.; Aksenov, V. S.; Sadykov, I. A.; Shamshin, I. O.; Frolov, F. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
A compressible medium represented by pure water saturated by small nonreactive or reactive gas bubbles can be used for generating a propulsive force in large-, medium-, and small-scale thrusters referred to as a pulsed detonation hydroramjet (PDH), which is a novel device for underwater propulsion. The PDH thrust is produced due to the acceleration of bubbly water (BW) in a water guide by periodic shock waves (SWs) and product gas jets generated by pulsed detonations of a fuel-oxidizer mixture. Theoretically, the PDH thrust is proportional to the operation frequency, which depends on both the SW velocity in BW and pulsed detonation frequency. The studies reported in this manuscript were aimed at exploring two possible directions of the improvement of thruster performances, namely, (1) the replacement of chemically nonreacting gas bubbles by chemically reactive ones, and (2) the increase in the pulsed detonation frequency from tens of hertz to some kilohertz. To better understand the SW-to-BW momentum transfer, the interaction of a single SW and a high-frequency (в‰€7 kHz) sequence of three SWs with chemically inert or active BW containing bubbles of air or stoichiometric acetylene-oxygen mixture was studied experimentally. Single SWs and SW packages were generated by burning or detonating a gaseous stoichiometric acetylene-oxygen or propane-oxygen mixture and transmitting the arising SWs to BW. The initial volume fraction of gas in BW was varied from 2% to 16% with gas bubbles 1.5-4 mm in diameter. The propagation velocity of SWs in BW ranged from 40 to 580 m/s. In experiments with single SWs in chemically active BW, a detonation-like mode of reaction front propagation ( bubbly quasidetonation ) was realized. This mode consisted of a SW followed by the front of bubble explosions and was characterized by a considerably higher propagation velocity as compared to the chemically inert BW. The latter could allow increasing the PDH operation frequency and thrust. Experiments with high-frequency SW packages showed that on the one hand, the individual SWs quickly merged, feeding each other and increasing the BW velocity, but on the other hand, the initial gas content for each successive SW decreased and, accordingly, the SW-to-BW momentum transfer worsened. Estimates showed that for a small-scale water guide 0.5 m long, the optimal pulsed detonation frequency was about 50-60 Hz.
Только метаданные
AUTOTHERMAL NATURAL GAS CONVERSION AND ALLOTHERMAL GASIFICATION OF LIQUID AND SOLID ORGANIC WASTES BY ULTRASUPERHEATED STEAM
(2022) Frolov, S. M.; Smetanyuk V. A.; Sadykov I. A.; Silant'ev A. S.; Aksenov, V. S.; Shamshin I. O.; Avdeev K. A.; Frolov F. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
Только метаданные
Kinetic Model and Experiment for Self-Ignition of Triethylaluminum and Triethylborane Droplets in Air
(2022) Frolov, S. M.; Aksenov, V. S.; Basevich, V.Y.; Belyaev, A. A.; Shamshin, I. O.; Frolov, F. S.; Storozhenko, P. A.; Guseinov, S. L.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
Triethylaluminum Al(C2H5)3, TEA, and triethylborane, B(C2H5)3, TEB, are transparent, colorless, pyrophoric liquids with boiling points of approximately 190 В°C and 95 В°C, respectively. Upon contact with ambient air, TEA, TEB, as well as their mixtures and solutions, in hydrocarbon solvents, ignite. They can also violently react with water. TEA and TEB can be used as hypergolic rocket propellants and incendiary compositions. In this manuscript, a novel scheme of the heterogeneous interaction of gaseous oxygen with liquid TEA/TEB microdroplets accompanied by the release of light hydrocarbon radicals into the gas phase is used for calculating the self-ignition of a spatially homogeneous mixture of fuel microdroplets in ambient air at normal pressure and temperature (NPT) conditions. In the primary initiation step, TEA and TEB react with oxygen, producing an ethyl radical, which can initiate an autoxidation chain. The ignition delay is shown to decrease with the decrease in the droplet size. Preliminary experiments on the self-ignition of pulsed and continuous TEA-TEB sprays in ambient air at NPT conditions are used for estimating the Arrhenius parameters of the rate-limiting reaction. Experiments confirm that the self-ignition delay of TEA-TEB sprays decreases with the injection pressure and provide the data for estimating the activation energy of the rate-limiting reaction, which appears to be close to 2 kcal/mol.
Только метаданные
Pulsed combustion of fuel–air mixture in a cavity above water surface: modeling and experiments
(2022) Platonov, S. V.; Avdeev, K. A.; Ivanov, V. S.; Zangiev, A. E.; Frolov, S. M.; Aksenov, V. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
© 2021, The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature.A mathematical model for simulating combustion and detonation of a fuel–air mixture in the gas cavity above the free water surface is developed. The model is based on solving the conservation equations of mass, momentum, and energy for a two-phase reacting gas–water medium with the phases treated as interacting interpenetrating continua having their own values of velocity, temperature, and turbulence characteristics. The model is validated by laboratory experiments. The test rig included a transparent cylindrical tube with one closed-end, a pool with an optically transparent window, as well as power, ignition, control, and measurement systems. The tube was vertically immersed with its open end in water and filled with a gaseous explosive mixture. In the experiments, a stoichiometric propane–air mixture was ignited and burned in the semi-closed 60 mL cylindrical volume above the free surface of water. The model is shown to predict satisfactorily the lift force acting on the tube, the time history of pressure in the volume, and the dynamics of the flame and gas–water interface motion during combustion in the volume. The model is intended to be applied for the design of boats with propulsion solely by combustion/detonation of fuel–air mixture in cavities constructed into a bottom surface of the boat. This propulsion system replaces conventional propellers, thereby reducing hydrodynamic resistance.
Только метаданные
Pulsed combustion of fuel–air mixture in a cavity under the boat bottom: modeling and experiments
(2022) Platonov, S. V.; Avdeev, K. A.; Ivanov, V. S.; Zangiev, A. E.; Frolov, S. M.; Aksenov, V. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
© 2021, The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature.The physical and mathematical model for simulating combustion and detonation of fuel mixture in the semi-confined gas volumes above the free surface of water is applied for modeling the transient two-phase reactive flow in the gas cavity under the bottom of a ship/boat. With the proper organization of the combustion/detonation process in the gas cavity, thermal expansion of combustion products can provide an additional lifting force that reduces the area of contact of the boat bottom with water, as well as a propulsive force caused by the overpressure of combustion/detonation products on redans—vertical sections of the boat bottom. The model is validated on the set of laboratory experiments with pulsed combustion of propane–air mixture in a semi-closed gas cavity. The model is shown to predict satisfactorily the arising lifting and propulsive forces acting on the volumes, the time histories of pressure in the volumes, and the dynamics of flame and gas–water interface motion during combustion in the volumes. For further model validation in terms of its scaling capability, a set of preliminary experiments with a larger-scale (by a factor of at least 5) towed boat with a bottom gas cavity were conducted on open water. In the experiment, the hydrogen–air mixture was ignited and burned in the bottom gas cavity in a pulsed mode. These experiments confirmed that pulsed combustion of fuel–air mixture in a gas cavity under the boat bottom creates positive propulsive and lifting forces acting on the boat. Moreover, in some experiments a considerable increase in the propulsive force was registered due to flame acceleration causing a higher overpressure in the cavity. The elevated values of the propulsive force in these conditions can be treated in favor of a pulsed detonation mode, which will be studied later.