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.

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.

Innovative methods for obtaining artificial roughness on the surfaces of heat-loaded parts of the liquid rocket engine combustion chambers

2020 ◽  
Author(s):  
A.Yu. Ryazantsev ◽  
S.S. Yukhnevich ◽  
A.A. Shirokozhukhova
Keyword(s):  
Combustion Chamber ◽  
Rocket Engine ◽  
Empirical Studies ◽  
Aerospace Industry ◽  
Rocket Engines ◽  
Artificial Roughness ◽  
Special Equipment ◽  
Liquid Rocket Engines ◽  
Engine Combustion ◽  
Liquid Rocket

The paper shows the applications of combined processing in the manufacture of parts and assembly units of liquid rocket engines in the aerospace industry. The most effective methods of obtaining artificial roughness on the surfaces of special equipment products are considered. Empirical studies of changes in the physical and mechanical properties of the material are performed using various methods of combined processing. Qualitative and quantitative relationships between the hydraulic characteristics of the rocket engine combustion chamber manufactured using the combined method, and the quality of the surface layer of the product are described and formalized. The analysis of modern processing methods is performed, and the latest methods for obtaining artificial roughness on the surfaces of rocket engine parts are presented. The relevance and need for the use of high-end technology in obtaining surface layers of products included in the structure of the combustion chamber of liquid rocket engines are proved. The results obtained allow significant expanding the technological capabilities of production, as well as appreciable improving the technical characteristics of special equipment products in the aerospace industry.

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.

Crack Evaluation of Mock-up Test Specimen of Rocket Engine Combustion Chamber by Eddy Current Testing

2017 ◽  
Vol 2017.52 (0) ◽  
pp. 173
Author(s):  
Kazuhiro NAKAJIMA ◽  
Tetsuya UCHIMOTO ◽  
Toshiyuki TAKAGI ◽  
Eiichi SATO ◽  
Mitsuharu SHIWA ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Eddy Current ◽  
Test Specimen ◽  
Rocket Engine ◽  
Eddy Current Testing ◽  
Current Testing ◽  
Engine Combustion

Conceptual Regenerative Nozzle Cooling Design for a Hydroxyl-Terminated Polybutadiene and Oxygen Hybrid Rocket Engine

2017 ◽  
Author(s):  
Luis R. Robles ◽  
Johnny Ho ◽  
Bao Nguyen ◽  
Geoffrey Wagner ◽  
Jeremy Surmi ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
High Temperatures ◽  
Cooling System ◽  
Rocket Engine ◽  
Combustion Efficiency ◽  
Rocket Engines ◽  
Hybrid Rocket ◽  
Gaseous Oxygen ◽  
Rocket Nozzle ◽  
Regenerative Cycle

Regenerative rocket nozzle cooling technology is well developed for liquid fueled rocket engines, but the technology has yet to be widely applied to hybrid rockets. Liquid engines use fuel as coolant, and while the oxidizers typically used in hybrids are not as efficient at conducting heat, the increased renewability of a rocket using regenerative cycle should still make the technology attractive. Due to the high temperatures that permeate throughout a rocket nozzle, most nozzles are predisposed to ablation, supporting the need to implement a nozzle cooling system. This paper presents a proof-of-concept regenerative cooling system for a hybrid engine which uses hydroxyl-terminated polybutadiene (HTPB) as its solid fuel and gaseous oxygen (O2) as its oxidizer, whereby a portion of gaseous oxygen is injected directly into the combustion chamber and another portion is routed up through grooves on the exterior of a copper-chromium nozzle and, afterwards, injected into the combustion chamber. Using O2 as a coolant will significantly lower the temperature of the nozzle which will prevent ablation due to the high temperatures produced by the exhaust. Additional advantages are an increase in combustion efficiency due to the heated O2 being used for combustion and an increased overall efficiency from the regenerative cycle. A computational model is presented, and several experiments are performed using computational fluid dynamics (CFD).

Sign in / Sign up

Export Citation Format

Share Document