Investigation of the effect of the output parameters of the flow behind the compressor on the gas dynamics of the separation diffuser of the combustion chamber

2020 ◽  
Author(s):  
M. M. Guryanova ◽  
K. R. Timofeeva ◽  
A. I. Guryanov
Keyword(s):  
Combustion Chamber ◽  
Gas Dynamics

Modelling of a rotating detonation engine combustion chamber

2021 ◽  
pp. 33-49
Author(s):  
Елена Викторовна Михальченко ◽  
Валерий Федорович Никитин ◽  
Любен Иванович Стамов ◽  
Юрий Григорьевич Филиппов
Keyword(s):  
Boundary Conditions ◽  
Combustion Chamber ◽  
Chemical Reactions ◽  
Gas Dynamics ◽  
Turbulent Transport ◽  
Kinetic Equations ◽  
Problem Solution ◽  
Engine Combustion ◽  
Detonation Engine ◽  
Rotating Detonation

Рассмотрено трехмерное численное моделирование камеры сгорания двигателя с непрерывной детонационной волной с помощью авторского программного пакета. Программное обеспечение использует для многокомпонентного химически реактивного газа математическую модель с опциональным подключением модели турбулентности. В основе модели химической кинетики лежит механизм элементарных реакций, в зависимости от механизма меняется число реакций. В программе, в том числе, реализован авторский кинетический механизм. Рассмотрены шесть кинетических механизмов: Мааса-Варнаца-Поупа, Хонга, Вильямса, Gri-Mech 3.0, Ли-Джоу-Казакова-Драера и авторский, проведено их сравнение. Код распараллелен с помощью технологий OpenMP и MPI. В результате работы программы получена оптимальная форма камеры сгорания с самоподдерживающейся детонационной волной на смеси водорода с кислородом. Purpose. To create software for studying the features of the transition from ignition and deflagration to a detonation mode in a three-dimensional configuration, including the formation and propagation of a rotating detonation complex, which takes transient processes into account. Methodology. The software is based on a mathematical model for multi-component gas dynamics with chemical reactions and turbulent transport for diffusion, viscosity, and thermal conductivity. High-order calculation schemes are used. To solve a stiff subsystem of kinetic equations, a hybrid implicit-explicit Novikov method is used (a specific variant of a Rosenbrock method). Findings. Authors created a code which calculates physical processes within a multi-component gas dynamics paradigm. The code accounts for chemical processes and turbulence modelling. The shape of computation domain and the type of boundary conditions is user defined. These include boundary conditions at the wall, as well as inflow and outflow conditions for both subsonic, and supersonic modes. Initial conditions can be set up differently in different regions of the domain. The software consists of several modules: a mesh-building module, initial state creation, calculation of new time layers saving the intermediate and final results at control points with a possibility to resume interrupted calculations, and post-processing modules. Authors developed blocks of solutions for various elementary chemical kinetic mechanisms, one of considered mechanisms is build up by themselves, others are published previously. It was obtained that the details of the 3D transient problem solution significantly depend on the chosen mechanism. Оriginality/value. The software complex makes it possible to process numerical modelling of a detonation engine combustion chamber in a 3D configuration considering chemical reactions and turbulent transport. Different chemical kinetics mechanisms are utilizable, and thrust characteristics could be obtained.

scholarly journals Сalculated analysis of the influence of operation and design factors on the parameters of oxygen-hydrogen low-thrust rocket engines

2019 ◽  
Vol 18 (3) ◽  
pp. 131-142
Author(s):  
V. V. Ryzhkov ◽  
I. I. Morozov
Keyword(s):  
Combustion Chamber ◽  
Gas Dynamics ◽  
Selection Criterion ◽  
Design Parameters ◽  
Rocket Engines ◽  
Low Thrust ◽  
Gaseous Oxygen ◽  
Computational Gas Dynamics ◽  
Design Factors ◽  
Selection Of

The paper presents the results of calculating thermodynamic and thermophysical properties of the combustion products of gaseous oxygen-hydrogen fuel according to the ideal LRE model taking into account the phase state of the components, as well as the parameters of a low-thrust engine according to the model of computational gas dynamics to ensure the selection of operation and design factors that define the design of a thruster for advanced aerospace objects. It is shown that ideal models can be used for the selection of some parameters, such as: the excess oxidant ratio, the pressure in the combustion chamber, the geometric degree of area expansion ratio. High-level computational gas dynamics models need to be used for the selection of some of the parameters of the engine to be designed, such as: design parameters of the propellant injection pattern, reduced length of the combustion chamber and some others. Air specific impulse was used as the selection criterion. The obtained calculation data allow one to choose the main parameters of the engine being designed with account for real processes in the combustion chamber and the nozzle of the engine.

scholarly journals Analyzing Influence of Ignition Gas Flow Pipe of Igniter on Working Process

2018 ◽  
Vol 36 (6) ◽  
pp. 1193-1201
Author(s):  
Jiang Chang ◽  
Gongping Wu ◽  
Haodong Wu ◽  
Xuejie Hao
Keyword(s):  
Numerical Simulation ◽  
Combustion Chamber ◽  
Atmospheric Pressure ◽  
Gas Dynamics ◽  
Gas Flow ◽  
Chamber Pressure ◽  
Steady State Flow ◽  
Working Process ◽  
Working Performance ◽  
Velocity Pressure

Based on gas dynamics and computational fluid dynamics, the numerical simulation of the steady-state flow field of igniter working in the two conditions was conducted with FLUENT. The numerical simulation results were validated by experiments. Influences of ignition gas flow pipe on the igniter's working performance were analyzed on the basis of test validation. The analysis results show that the combustion chamber pressure has atmospheric pressure and that the igniter works with ignition gas flow pipe. The velocity of throat is lower than the speed of sound and the sonic position moves to the position of ignition gas flow pipe; the velocity, pressure and temperature of throat increase; but the flux, pressure and temperature of outlet decrease. Under the different conditions of combustion chamber pressure, the outlet velocity, pressure, temperature and flux have a stable section; but the flux decreases.

Gas dynamics of combustion-chamber processes in solid-fuel rocket motors

1992 ◽  
Vol 35 (8) ◽  
pp. 769-776
Author(s):  
E. A. Kozlov ◽  
A. B. Vorozhtsov ◽  
S. S. Bondarchuk
Keyword(s):  
Combustion Chamber ◽  
Solid Fuel ◽  
Gas Dynamics ◽  
Rocket Motors

Analysis of Gas Dynamics and Combustion in a Small Reverse-Flow Combustion Chamber

2018 ◽  
Vol 61 (3) ◽  
pp. 460-466
Author(s):  
W. M. Yousef ◽  
V. A. Sychenkov ◽  
N. V. Davydov ◽  
Yu. B. Aleksandrov
Keyword(s):  
Combustion Chamber ◽  
Gas Dynamics ◽  
Reverse Flow

Supernovae and interstellar gas dynamics

1967 ◽  
Vol 31 ◽  
pp. 117-119
Author(s):  
F. D. Kahn ◽  
L. Woltjer
Keyword(s):  
Lower Limit ◽  
High Velocity ◽  
Gas Dynamics ◽  
Interstellar Cloud ◽  
Interstellar Gas ◽  
Random Motions ◽  
Relativistic Particles

The efficiency of the transfer of energy from supernovae into interstellar cloud motions is investigated. A lower limit of about 0·002 is obtained, but values near 0·01 are more likely. Taking all uncertainties in the theory and observations into account, the energy per supernova, in the form of relativistic particles or high-velocity matter, needed to maintain the random motions in the interstellar gas is estimated as 1051·4±1ergs.

DETERMINATION OF THE TYPE OF A SINGLE-USE GRENADE LAUNCHER BASED ON ITS COMPOSITE PARTS AND FRAGMENTS OF REACTIVE GRENADE FOUND AT THE PLACE OF ACCIDENT

2017 ◽  
Vol 17 ◽  
pp. 245-252
Author(s):  
V. V. Somov
Keyword(s):  
Combustion Chamber ◽  
Structural Features ◽  
Outlet Section ◽  
Technical Expertise ◽  
Jet Engine ◽  
Size Ofthe ◽  
Single Use ◽  
Nozzle Block ◽  
Considerable Damage

In carrying out an investigation into the explosion, among others, the investigative version of the use of a single-use reactive grenade launcher is being considered. The most common for criminal explosions are applied grenade launchers RPG-18, RPG-22, RPG-26. Their use is due to a number of such properties as small size and weight, which makes it possible to transfer them covertly, the range of the shot significantly exceeding the range of the hand grenade throw, the high detonating effect of the rocket grenade explosion. The single-use rocket launchers are generally of the same design. Their differences are in the features of the components construction and dimensional characteristics, which are given in the article. On the basis of expert practice, details ofgrenade launchers that remain at the site of the explosion and have the least damage are determined. These details are the objects of investigation of the explosion technical expertise. These objects include launchers of grenade launchers and rocket parts ofjet grenades. The design features of the launchers, their dimensional characteristics and marking symbols make it possible to determine their belonging to a specific type of jet grenade launchers. Missile parts of jet grenades differ in the form of the combustion chamber of the jet engine, nozzle, in the size ofthe outlet section of the nozzle, in the form and size of the stabilizerfeathers. To determine the belonging of the rocket part of the grenade to a specific type ofjet grenade launcher, it’s necessary to establish a set of structural features and dimensional characteristics. At considerable damage of the combustion chamber of the jet engine, as a rule, the nozzle block remains intact that allows to define diameter of critical section of a nozzle, and on it to establish type of the used single-use grenade launcher.

DEVELOPMENT OF THE COMBUSTION CHAMBER OF GAS ENGINE, CONVERTED ON THE BASIS OF DIESELS D-120 OR D-144 ENGINES TO WORK FOR ON LIQUEFIED PETROLEUM GAS

2019 ◽  
pp. 2-8
Author(s):  
Serhii Kovalov
Keyword(s):  
Combustion Chamber ◽  
Compression Ratio ◽  
Diesel Engines ◽  
Combustion Engine ◽  
Motor Fuel ◽  
Liquefied Petroleum Gas ◽  
Gas Engine ◽  
Chamber Volume ◽  
Motor Fuels ◽  
Dynamic Cycle

The expediency of using vehicles of liquefied petroleum gas as a motor fuel, as com-pared with traditional liquid motor fuels, in particular with diesel fuel, is shown. The advantages of converting diesel engines into gas ICEs with forced ignition with respect to conversion into gas diesel engines are substantiated. The analysis of methods for reducing the compression ratio in diesel engines when converting them into gas ICEs with forced ignition has been carried out. It is shown that for converting diesel engines into gas ICEs with forced ignition, it is advisable to use the Otto thermo-dynamic cycle with a decrease in the geometric degree of compression. The choice is grounded and an open combustion chamber in the form of an inverted axisymmetric “truncated cone” is developed. The proposed shape of the combustion chamber of a gas internal combustion engine for operation in the LPG reduces the geometric compression ratio of D-120 and D-144 diesel engines with an unseparated spherical combustion chamber, which reduces the geometric compression ratio from ε = 16,5 to ε = 9,4. The developed form of the combustion chamber allows the new diesel pistons or diesel pistons which are in operation to be in operation to be refined, instead of making special new gas pistons and to reduce the geometric compression ratio of diesel engines only by increasing the combustion chamber volume in the piston. This method of reducing the geometric degree of compression using conventional lathes is the most technologically advanced and cheap, as well as the least time consuming. Keywords: self-propelled chassis SSh-2540, wheeled tractors, diesel engines D-120 and D-144, gas engine with forced ignition, liquefied petroleum gas (LPG), compression ratio of the internal com-bustion engine, vehicles operating in the LPG.

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