scholarly journals Factors Affecting Characteristic Length of the Combustion Chamber of Liquid Propellant Rocket Engines

2019 ◽  
Vol 38 (3) ◽  
pp. 729-744
Author(s):  
Tajwali Khan ◽  
Ihtzaz Qamar
Keyword(s):  
Combustion Chamber ◽  
Characteristic Length ◽  
Rocket Engine ◽  
Droplet Diameter ◽  
Computer Code ◽  
Rocket Engines ◽  
Fuel Droplet ◽  
Liquid Propellant ◽  
Proposed Model ◽  
Propellant Rocket

Optimum characteristic length of the combustion chamber of liquid rocket engine is very important to get higher energy from the liquid propellants. Characteristic length is defined by the time required for complete burning of fuel. Combustion reactions are very fast and combustion is evaporation dependent. This paper proposes fuel droplet evaporation model for liquid propellant rocket engine and discusses the factors which can affect the required size of characteristic length of the combustion chamber based on proposed model. The analysis is performed for low temperature combustion chamber. A computer code based on proposed model is generated, which solve analytical equations to calculate combustion chamber characteristic length under various input conditions. The analysis shows that characteristic length is affected by combustion chamber temperature, pressure, fuel droplet diameter, chamber diameter, mass flow rate of propellants and relative velocity of the droplet in the combustion chamber.

scholarly journals Evaluation of the high-frequency oscillation parameters of a liquid-propellant rocket engine with an annular combustion chamber

2021 ◽  
Vol 2021 (1) ◽  
pp. 16-28
Author(s):  
O.D. Nikolayev ◽  
◽  
I.D. Bashliy ◽  
N.V. Khoriak ◽  
S.I. Dolgopolov ◽  
...  
Keyword(s):  
Finite Element ◽  
Combustion Chamber ◽  
Rocket Engine ◽  
Element Model ◽  
Numerical Approach ◽  
Rocket Engines ◽  
Liquid Propellant ◽  
Liquid Propellant Rocket Engine ◽  
Firing Tests ◽  
Propellant Rocket

The high-frequency instability (HF instability) of a liquid-propellant rocket engine (LPRE) during static firing tests is often accompanied by a significant increase in dynamic loads on the combustion chamber structure, often leading to the chamber destruction. This dynamic phenomenon can also be extremely dangerous for the dynamic strength of a liquid-propellant rocket engine with an annular combustion chamber. Computation of the parameters of acoustic combustion product oscillations is important in the design and static firing tests of such rocket engines. The main aim of this paper is to develop a numerical approach to determining the parameters of acoustic oscillations of combustion products in annular combustion chambers of liquid-propellant rocket engines taking into account the features of the configuration of the combustion space and the variability of the physical properties of the gaseous medium depending on the axial length of the chamber. A numerical approach is proposed. The approach is based on mathematical modeling of natural oscillations of a “shell structure of an annular chamber – gas” coupled dynamic system by using the finite element method. Based on the developed finite-element model of coupled spatial vibrations of the structure of the annular combustion chamber and the combustion product oscillations, the oscillation parameters of the system under consideration (frequencies, modes, and effective masses) for its dominant acoustic modes, the vibration amplitudes of the combustion chamber casing, and the amplitudes of its vibration accelerations can be determined. The operating parameters of the liquid-propellant rocket engine potentially dangerous for the development of thermoacoustic instability of the working process in the annular combustion chamber can be identified. For the numerical computation of the dynamic gains (in pressure) of the combustion chamber, a source of harmonic pressure excitation is introduced to the finite element model of the dynamic system “shell structure of an annular configuration – gas” (to the elements at the start of the chamber fire space). The developed approach testing and further analysis of the results were carried out for an engine with an annular combustion chamber (with a ratio of the outer and inner diameters of 1.5) using liquid oxygen – methane as a propellant pair. The system shapes and frequencies of longitudinal, tangential and radial modes are determined. It is shown that the frequency of the first acoustic mode in the case of a relatively low stiffness of the combustion chamber casing walls can be reduced by 40 percent in comparison with the frequency determined for a casing with rigid walls.

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.

scholarly journals Influence of Polyisobutylene Kerosene Additive on Combustion Efficiency in a Liquid Propellant Rocket Engine

Aerospace ◽  
2019 ◽  
Vol 6 (12) ◽  
pp. 129 ◽  
Author(s):  
Igor Borovik ◽  
Evgeniy Strokach ◽  
Alexander Kozlov ◽  
Valeriy Gaponov ◽  
Vladimir Chvanov ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Film Cooling ◽  
Rocket Engine ◽  
Combustion Efficiency ◽  
Liquid Propellant ◽  
Gaseous Oxygen ◽  
Wall Film ◽  
Measurement Results ◽  
Liquid Propellant Rocket Engine ◽  
Propellant Rocket

The combustion of kerosene with the polymer additive polyisobutylene (PIB) was experimentally investigated. The aim of the study was to measure the effect of PIB kerosene on the efficiency of combustion chamber cooling and the combustion efficiency of the liquid propellant for a rocket engine operating on kerosene and gaseous oxygen (GOX). The study was conducted on an experimental rocket engine using kerosene wall film cooling in the combustion chamber. Fire tests showed that the addition of polyisobutylene to kerosene had no significant effect on the combustion efficiency. However, analysis of the wall temperature measurement results showed that the use of PIB kerosene is more effective for film cooling than pure kerosene, which can increase the efficiency of combustion chamber cooling and subsequently increase its reliability and reusability. Thus, the findings of this study are expected to be of use in further investigations of wall film cooling efficiency.

Large Rocket Engines for Space Vehicles and Missiles

1961 ◽  
Vol 65 (605) ◽  
pp. 321-331
Author(s):  
S. K. Hoffman
Keyword(s):  
Rocket Engine ◽  
Space Vehicles ◽  
Rocket Engines ◽  
Liquid Propellant ◽  
New Developments ◽  
Engine Component ◽  
Space Projects ◽  
History Of ◽  
Liquid Propellant Rocket Engine ◽  
Propellant Rocket

SummaryThe history of Rocketdyne's activity in the field of large liquid-propellant rocket engines is outlined in a chronological review of applicable United States ballistic and space projects. Within security limitations, major rocket engine component improvements and general fabrication techniques are discussed. The trends and new developments in liquid-propellant rocket engine designs are presented and a forecast of future engines is made.

Research of Faulty Sensors Data Reconstructed for Liquid-Propellant Rocket Engines

2012 ◽  
Vol 229-231 ◽  
pp. 1449-1453 ◽  
Author(s):  
Yan Jun Li ◽  
Xiao Hui Peng ◽  
Yu Qiang Cheng ◽  
Jian Jun Wu
Keyword(s):  
Fuzzy Inference System ◽  
Fuzzy Inference ◽  
Rocket Engine ◽  
Fuzzy Model ◽  
Rocket Engines ◽  
Liquid Propellant ◽  
Inference System ◽  
Neuro Fuzzy ◽  
Faulty Sensors ◽  
Propellant Rocket

In this paper, the data of faulty sensors reconstruct algorithm of liquid-propellant rocket engine is developed based on adaptive neuro-fuzzy inference system. First, the input parameters selected for method is according to regularity criterion and the relationships between each parameter; second, adaptive neuro-fuzzy inference system is train by normal test, finally, the fuzzy mode is validated by normal data and the data of faulty sensor is reconstructed. The results indicate that this algorithm can reconstruct the data of faulty sensors accurately and show that the fuzzy model approach has good performance in faulty sensors data reconstruct for LRE.

On the feasibility of developing a single-stage acceleration/deceleration unit based on the oxygen-hydrocarbon engine 11D58M for a super-heavy launch vehicle

2021 ◽  
pp. 62-75
Author(s):  
Boris A. SOKOLOV ◽  
Nikolay N. TUPITSYN ◽  
Evgeniy N. TUMANIN ◽  
Igor A. KRYUKOV ◽  
Andrey V. KISELEV ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Launch Vehicle ◽  
Single Stage ◽  
Rocket Engines ◽  
Liquid Propellant ◽  
Gravity Assist ◽  
Upper Stage ◽  
Gravity Assist Maneuver ◽  
Lunar Gravity Assist ◽  
Propellant Rocket

The paper presents results of unsolicited exploratory design studies done by the authors into the feasibility of developing for a super-heavy launch vehicle a single-stage oxygen-hydrocarbon acceleration/deceleration unit (ADU) with two liquid-propellant rocket engines 11D58M developed by RSC Energia, intended for insertion of manned spacecraft into lunar orbit, as well as for insertion of super-heavy spacecraft into geostationary orbit (including the orbital module high-apogee transfer profile using lunar gravity assist maneuver). It demonstrates that the single-stage ADU will have a number of important advantages over both a single-stage oxygen-hydrogen ADU and a functionally similar two-stage acceleration/deceleration system of an orbital module in the form of a tandem stack of an oxygen-hydrogen acceleration stage and correction and braking stage. To assure the start-ups of the main liquid propulsion system of the ADU, it proposes a new method for inertial propellant component phase separation in the tanks in zero-gravity environment using a pre-startup pre-programmed ullage separation turn maneuver of the orbital unit about its transverse axis of inertia. Key words: Integrated launch vehicle, launch vehicle, orbital module, upper stage, orbital transfer vehicle, acceleration/deceleration unit, ullage maneuver, liquid-propellant rocket engine.

scholarly journals On the question of solid-propellant rocket engine design preventing unstable operation in the combustion chamber

2017 ◽  
pp. 63-72
Author(s):  
G. A. Glebov ◽  
S. A. Vysotskaya
Keyword(s):  
Combustion Chamber ◽  
Solid Propellant ◽  
Rocket Engine ◽  
Rocket Engines ◽  
Pressure Oscillations ◽  
Engine Design ◽  
Solid Propellant Rocket ◽  
Solid Propellant Rocket Engine ◽  
Flow Duct ◽  
Propellant Rocket

The paper presents results of a numerical investigation concerning the effect that the flow duct shape and combustion rate equation have on the gas dynamic vortex flow pattern and self-excited pressure oscillations in the combustion chamber of a solid-propellant rocket engine. We provide guidelines on upgrading solid-propellant rocket engines in order to decrease the magnitude of pressure pulses in the case of pulsating combustion.

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