Physical model of noise in the combustion chamber of a liquid-propellant engine

2021 ◽  
pp. 42-50
Author(s):  
О.П. Мосалов ◽  
Ю.В. Завьялова
Keyword(s):  
Spectral Density ◽  
Combustion Chamber ◽  
Rocket Engine ◽  
Single Mode ◽  
Liquid Rocket Engine ◽  
Liquid Propellant ◽  
Combustion Chambers ◽  
Power Spectral ◽  
Liquid Rocket ◽  
Working Procedure

В статье рассмотрена задача определения резонансных характеристик камер сгорания жидкостного ракетного двигателя. Приведён и математически обоснован подход к созданию алгоритмов решения такой задачи с помощью анализа спектральной плотности мощности шумовых сигналов параметров рабочих процессов. Рассмотрены вычислительные эксперименты и продемонстрированы их результаты для модельного сигнала с единственной модой. In this article a task of determining of resonance characteristics for combustion chambers of a liquid rocket engine. The approach for development of algorithms to solve this task using analysis of power spectral density of noise signals of working procedure parameters is considered and mathematically justified. Computational experiments are considered and their results for a model signal with a single mode is demonstrated.

scholarly journals Failure mechanism and life evaluation of liquid rocket engine combustion chamber under severe multi-physics conditions

2015 ◽  
Vol 81 (826) ◽  
pp. 14-00674-14-00674
Author(s):  
Miki NISHIMOTO ◽  
Hideyo NEGISHI ◽  
Shinobu YOSHIMURA ◽  
Naoto KASAHARA ◽  
Hiroshi AKIBA ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Failure Mechanism ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Life Evaluation ◽  
Engine Combustion ◽  
Liquid Rocket

Numerical Simulation of the Spray Characteristics in Small Scale Liquid Rocket Engine Combustion Chamber

2011 ◽  
Vol 383-390 ◽  
pp. 7729-7733
Author(s):  
Na Zhao ◽  
Yong Gang Yu ◽  
Yu Qiang Wang
Keyword(s):  
Numerical Simulation ◽  
Surface Tension ◽  
Rocket Engine ◽  
Nozzle Diameter ◽  
Small Scale ◽  
Liquid Rocket Engine ◽  
Liquid Droplets ◽  
Liquid Propellant ◽  
Fluent Software ◽  
Liquid Rocket

The mathematical and physical model of the liquid propellant spray in straight nozzle was proposed for studying the performance characteristics of the small-scale liquid rocket engine. With the Fluent software, the numerical simulation was carried out. Sauter mean diameter (SMD) of the HAN-based liquid propellant (LP1846) in the engine combustor changing with spray pressure, nozzle diameter and the liquid surface tension were analyzed. The results indicate that: in the spray pressure region of 1.8MPa~3.0MPa, at a fixed spray pressure, the smaller is the nozzle diameter, the smaller is the droplets’ SMD and the relationship between the SMD and the nozzle diameter is approximately linearity; for the same nozzle diameter and spray pressure, the larger is the surface tension, the larger is the liquid droplets’ SMD.

Performances Study of Liquid Rocket Engine

2014 ◽  
Vol 555 ◽  
pp. 84-90
Author(s):  
Grigore Cican ◽  
Daniel Eugeniu Crunteanu ◽  
Mohamed Yassir El Azzioui
Keyword(s):  
Combustion Chamber ◽  
Firing Temperature ◽  
Rocket Engine ◽  
Thermal Dissociation ◽  
Liquid Hydrogen ◽  
Combustion Reaction ◽  
Liquid Rocket Engine ◽  
Liquid Rocket

The article presents the performance of the liquid rocket engine. It will study the combustion reaction of the liquid hydrogen and oxygen without thermal dissociation. The main elements studied are the influence of the exces of the oxidant on firing temperature, on exhaust velocity, on the evacutation temperature from the engine and on the ishotermal coefficient. The pressure influence from the combustion chamber on the evacuation velocity, on the temperature from the evacuation from the exhaustion section and on the isentropic index.

Mathematical simulation of coolant flow in the cooling channel of a liquid rocket engine combustion chamber featuring an extremely high degree of ribbing

2019 ◽  
Author(s):  
V.P. Aleksandrenkov ◽  
K.E. Kovalev ◽  
D.A. Yagodnikov
Keyword(s):  
Combustion Chamber ◽  
Mass Flow Rate ◽  
Flow Rate ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Cooling Channel ◽  
Additive Technology ◽  
Engine Combustion ◽  
Liquid Rocket ◽  
High Degree

The paper presents a computational analysis of coolant distribution in the cooling channel of a liquid rocket engine combustion chamber, performed in order to develop a set of practical guidelines towards increasing efficiency of a cooling system featuring an extremely high degree of ribbing. We created a three-dimensional mathematical model comprising a closed system of hydrodynamic equations as well as initial and boundary conditions for an element of the liquid rocket engine chamber we modelled, the chamber featuring longitudinal cooling channel arrangement manufactured via additive technology. We computed velocity and pressure fields in characteristic cooling channel regions for various levels of coolant mass flow rate, which confirmed the feasibility of the layout proposed in terms of uniform coolant distribution in the cooling channel of the liquid rocket engine modelled. We obtained the friction loss ξ as a function of coolant mass flow rate and particle size of the powder used in the additive technology to manufacture the combustion chamber wall and cooling channel.

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