scholarly journals Mathematical Model and Computational Research of Combustion Chamber Wall Thermal State for Gaseous-Propellant Oxygen-Methane Low-Thrust Rocket Engine on a Pulse Mode

2013 ◽  
Author(s):  
О.А. Ворожеева ◽  
◽  
Д.А. Ягодников ◽  
Keyword(s):  
Mathematical Model ◽  
Combustion Chamber ◽  
Thermal State ◽  
Rocket Engine ◽  
Pulse Mode ◽  
Chamber Wall ◽  
Low Thrust ◽  
Computational Research

Computational studies to optimize the geometry of the low-thrust rocket combustion chamber using gaseous propellants

2021 ◽  
Author(s):  
A.V. Novikov ◽  
E.A. Andreev ◽  
E.I. Bardakova
Keyword(s):  
Combustion Chamber ◽  
Thermal State ◽  
Rocket Engine ◽  
Environmental Safety ◽  
Rocket Engines ◽  
Space Technology ◽  
Low Thrust ◽  
Mathematical Experiment ◽  
Space Objects ◽  
Calculation Results

Due to the tough requirements for the environmental safety of the space objects operation, the use of methane-based fuel together with oxygen is a promising direction in developing a new generation of rocket and space technology, including low-thrust rocket engines. When developing low-thrust rocket engines running on oxygen-methane fuel, a mathematical experiment helps to identify the determining factors that affect the quality of the working process in the combustion chamber and to make a calculated optimization of the parameters for supplying fuel components to the combustion chamber. This contributes to a better understanding of the physics of the ongoing processes and leads to recommendations for the design of individual components of the combustion chamber. The numerical simulation enables us to optimize the geometry of the combustion chamber in order to obtain the maximum value of the chamber coefficient, which for an isobaric combustion chamber can be equal to the coefficient of the flow complex. This approach can significantly reduce the number of expensive bench tests. The paper introduces a physical and mathematical model of the workflow in the combustion chamber of a low-thrust rocket engine and gives a comparative analysis of the calculation results for various modifications of the original geometry of the low thrust rocket chamber. Recommendations are given for changing the initial geometry of the combustion chamber in order to increase the coefficient of the flow complex while maintaining a satisfactory thermal state of this chamber.

Numerical study of the influence of the physicochemical liquid fuel properties on the efficiency of the low-thrust rocket engine working process

2021 ◽  
Author(s):  
A.V. Novikov ◽  
E.A. Andreev ◽  
E.I. Bardakova
Keyword(s):  
Combustion Chamber ◽  
Numerical Study ◽  
Rocket Engine ◽  
Propulsion System ◽  
Rocket Engines ◽  
Space Technology ◽  
Low Thrust ◽  
Working Process ◽  
Engine Combustion ◽  
Parametric Studies

Low-thrust rocket engines are widely used in rocket and space technology for correcting the position of a spacecraft in orbit, for controlling motion along a trajectory, etc. Their number in the propulsion system can be from one to tens of units. Accordingly, the efficiency of their work significantly affects the perfection of the propulsion system as a whole. The object of the study was the low-thrust rocket engine combustion chamber operating according to the gas-liquid scheme. There were performed computational and parametric studies of various factor effects on the characteristics of the working process in the combustion chamber. The dependences of the coefficient of the consumable complex and parameters of the working process of the low-thrust rocket engine chamber on the influencing factors when using ethanol and kerosene as a fuel were calculated. A comparative analysis of the results of using these two components under similar conditions was carried out, which made it possible to reveal the influence of the physicochemical properties of the combustible component on the efficiency of the working process organization. The results obtained can be used in the design of low-thrust engines operating on the kerosene–oxygen and ethanol–oxygen propellants.

Parametric study of the effect of mode and geometric factors on the chamber coefficient of a liquid-propellant engine with a slotted nozzle head

2021 ◽  
Author(s):  
A.V. Novikov ◽  
E.A. Andreev
Keyword(s):  
Mathematical Model ◽  
Combustion Chamber ◽  
Rocket Engine ◽  
Rocket Engines ◽  
Liquid Propellant ◽  
Working Process ◽  
Bench Tests ◽  
Good Convergence ◽  
Nozzle Head ◽  
Propellant Rocket

The creation of advanced spacecraft requires developing new and improving existing now liquid-propellant rocket engines. In this case, one of the decisive factors determining their perfection is the design of the nozzle head of the combustion chamber, as well as the adopted scheme of mixing and burning rocket fuel. Thus, the optimization of the geometric and operating parameters of the combustion chamber is an urgent problem, which can be solved using both experimental and computational methods. The use of the latter can significantly reduce the volume of expensive bench tests. The article describes the study of a liquid-propellant engine chamber with a slotted nozzle head, in particular, the effect of the reduced length on the efficiency of the working process, assessed by the chamber coefficient. A mathematical model of the working process behaviour in the combustion chamber of a liquid-propellant rocket engine on oxygen-kerosene fuel components has been compiled. An algorithm for solving the equations of the mathematical model for the studied mixture formation scheme has been developed. Parametric calculations were performed and the main factors influencing the characteristics of the working process in the combustion chamber of a liquid-propellant engine with a slotted nozzle head were determined. Comparison of the calculation results according to the proposed method and the available results of bench tests showed their good convergence.

Preliminary Studies on Non-Reactive Flow Vortex Cooling

2019 ◽  
Vol 12 (3) ◽  
pp. 262-271
Author(s):  
T.N. Rajesh ◽  
T.J.S. Jothi ◽  
T. Jayachandran
Keyword(s):  
Combustion Chamber ◽  
Inner Core ◽  
Rocket Engine ◽  
Injection Pressure ◽  
Chamber Pressure ◽  
Reactive Flow ◽  
Stoichiometric Ratio ◽  
Gaseous Oxygen ◽  
Mixture Ratio ◽  
Vortex Combustion

Background: The impulse for the propulsion of a rocket engine is obtained from the combustion of propellant mixture inside the combustion chamber and as the plume exhausts through a convergent- divergent nozzle. At stoichiometric ratio, the temperature inside the combustion chamber can be as high as 3500K. Thus, effective cooling of the thrust chamber becomes an essential criterion while designing a rocket engine. Objective: A new cooling method of thrust chambers was introduced by Chiaverni, which is termed as Vortex Combustion Cold-Wall Chamber (VCCW). The patent works on cyclone separators and confined vortex flow mechanism for providing high propellant mixing with improved degree of turbulence inside the combustion chamber, providing the required notion for studies on VCCW. The flow inside a VCCW has a complex structure characterised by axial pressure losses, swirl velocities, centrifugal force, flow reversal and strong turbulence. In order to study the flow phenomenon, both the experimental and numerical investigations are carried out. Methods: In this study, non-reactive flow analysis was conducted with real propellants like gaseous oxygen and hydrogen. The test was conducted to analyse the influence of mixture ratio and injection pressure of the propellants on the chamber pressure in a vortex combustion chamber. A vortex combustor was designed in which the oxidiser injected tangentially at the aft end near the nozzle spiraled up to the top plate and formed an inner core inside the chamber. The fuel was injected radially from injectors provided near the top plate and the propellants were mixed in the inner core. This resulted in enhanced mixing and increased residence time for the fuel. More information on the flow behaviour has been obtained by numerical analysis in Fluent. The test also investigated the sensitivity of the tangential injection pressure on the chamber pressure development. Results: All the test cases showed an increase in chamber pressure with the mixture ratio and injection pressure of the propellants. The maximum chamber pressure was found to be 3.8 bar at PC1 and 2.7 bar at PC2 when oxidiser to fuel ratio was 6.87. There was a reduction in chamber pressure of 1.1 bar and 0.7 bar at PC1 and PC2, respectively, in both the cases when hydrogen was injected. A small variation in the pressure of the propellant injected tangentially made a pronounced effect on the chamber pressure and hence vortex combustion chamber was found to be very sensitive to the tangential injection pressure. Conclusion: VCCW mechanism has been to be found to be very effective for keeping the chamber surface within the permissible limit and also reducing the payload of the space vehicle.

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