Experimental Analysis of Swirl Fuel Injector in Liquid Propellant Rocket Engine

Fuel injector for a liquid rocket is a very important component since a small difference in its design can drastically affect the combustion efficiency. The primary function of the injector is to break the fuel up into very small droplets. The concept of this project is to perform the fuel atomization with the desired cone angle. This atomization is achieved by passing the fuel through a swirl fuel injector which is connected to the fuel tank and air compressor. Three different orifices of various diameters are designed with different cone angles. The experimental setup consists of a fuel injector with the swirler inside, which is made up of brass with two different vane angles. The air compressor is used for pressurizing the fuel through the injectors. The cold flow experiment is conducted by passing the mixture of air and fuel to get the atomization. The injector is tested with various pressures ranging from 3 to 7 bar for the two cone angles with varying orifice diameters and the different spray patterns are captured. The results are compared, tabulated and correlated with existing values.

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Analysis of properties of inertia regulator of thrust control system of liquid rocket engine

Omsk Scientific Bulletin Series Aviation-Rocket and Power Engineering ◽

10.25206/2588-0373-2021-5-2-98-105 ◽

2021 ◽

Vol 5 (2) ◽

pp. 98-105

Author(s):

M. M. Dron ◽

◽

A. B. Yakovlev ◽

Keyword(s):

Control System ◽

Rocket Engine ◽

Space Rocket ◽

Liquid Propellant Rocket Engine ◽

Thrust Control ◽

Liquid Rocket ◽

The Cost ◽

Rocket System ◽

Propellant Rocket

The quality of the flight task of a space rocket system is determined among other things by the accuracy of maintaining and regulating the thrust of the rocket engine. Improving the accuracy and reducing errors in the engine mode control system will reduce the cost of space launches or allow you to put a large payload into orbit. The article presents a mathematical model of a controller with an inertial booster of a liquid-propellant rocket engine, identifies parameters and values that affect its accuracy, and considers measures to reduce static error

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

Aerospace ◽

10.3390/aerospace6120129 ◽

2019 ◽

Vol 6 (12) ◽

pp. 129 ◽

Cited By ~ 1

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.

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Spray cone angle and air core diameter of hollow cone swirl rocket injector

IIUM Engineering Journal ◽

10.31436/iiumej.v12i3.66 ◽

2011 ◽

Vol 12 (3) ◽

Cited By ~ 2

Author(s):

Ahmad Hussein Abdul Hamid

Keyword(s):

Cone Angle ◽

Injection Pressure ◽

Combustion Efficiency ◽

Fuel Injector ◽

Hollow Cone ◽

Spray Cone Angle ◽

Core Diameter ◽

Spray Cone ◽

Air Core ◽

Liquid Rocket

ABSTRACT : Fuel injector for liquid rocket is a very critical component since that small difference in its design can dramatically affect the combustion efficiency. The primary function of the injector is to break the fuel up into very small droplets. The smaller droplets are necessary for fast quiet ignition and to establish a flame front close to the injector head, thus shorter combustion chamber is possible to be utilized. This paper presents an experimetal investigation of a mono-propellant hollow cone swirl injector. Several injectors with different configuration were investigated under cold ï¬‚ow test, where water is used as simulation fluid. This investigation reveals that higher injection pressure leads to higher spray cone angle. The effect of injection pressure on spray cone angle is more prominent for injector with least number of tangential ports. Furthermore, it was found that injector with the most number of tangential ports and with the smallest tangential port diameter produces the widest resulting spray. Experimental data also tells that the diameter of an air core that forms inside the swirl chamber is largest for the injector with smallest tangential port diameter and least number of tangential ports.ABSTRAK : Injektor bahan api bagi roket cecair merupakan satu komponen yang amat kritikal memandangkan perbezaan kecil dalam reka bentuknya akan secara langsung mempengaruhi kecekapan pembakaran. Fungsi utama injektor adalah untuk memecahkan bahan api kepada titisan yang amat kecil. Titisan kecil penting untuk pembakaran pantas secara senyap dan untuk mewujudkan satu nyalaan di hadapan, berhampiran dengan kepala injektor, maka kebuk pembakaran yang lebih pendek berkemungkinan dapat digunakan. Kertas kerja ini mebentangkan satu penyelidikan eksperimental sebuah injektor ekabahan dorong geronggang kon pusar. Beberapa injektor dengan konfigurasi berbeza telah dikaji di bawah ujian aliran sejuk, di mana air digunakan sebagai bendalir simulasi. Kajian ini mendedahkan bahawa suntikan bertekanan tinggi menghasilkan sudut semburan kon yang besar. Kesan tekanan suntikan ke atas sudut semburan kon lebih ketara pada injektor yang mempunyai lubang tangen yang kurang Tambahan pula, injektor yang mempunyai jumlah lubang tangen yang paling banyak dan lubang tangen berdiameter paling kecil menghasilkan semburan yang paling lebar. Data eksperimental juga menunjukkan bahawa diameter teras udara terbesar terhasil di dalam kebuk pusar injektor yang mempunyai diameter lubang tangen terkecil dan jumlah lubang tangen yang paling kurang.

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DESIGN OF TYPICAL COOLING JACKET FOR LIQUID PROPELLANT ROCKET ENGINE BY COMPUTATIONAL FLUID DYNAMICS

10.26678/abcm.encit2018.cit18-0121 ◽

2018 ◽

Author(s):

Daniel Roberto Ferreira ◽

Wladimyr Dourado

Keyword(s):

Fluid Dynamics ◽

Computational Fluid Dynamics ◽

Rocket Engine ◽

Liquid Propellant ◽

Liquid Propellant Rocket Engine ◽

Cooling Jacket ◽

Propellant Rocket

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Influence of Ignition Channel on the Ignition Performance of Ignition Device

Mathematical Problems in Engineering ◽

10.1155/2018/4270790 ◽

2018 ◽

Vol 2018 ◽

pp. 1-14

Author(s):

Jiang Chang ◽

Gongping Wu ◽

Hanwei Tang

Keyword(s):

Working Conditions ◽

Inflection Point ◽

Rocket Engine ◽

Gas Pressure ◽

Gas Velocity ◽

Liquid Propellant ◽

Liquid Propellant Rocket Engine ◽

Ignition Device ◽

Propellant Rocket ◽

Solid Type

Based on relative theories of gas dynamics and computational fluid dynamics, the flow field computation software ANSYS Fluent was used to simulate the steady flow field of the solid type ignition device of liquid-propellant rocket engine in two working conditions (condition I: without ignition channel, condition II: with ignition channel). On this basis, the influence of ignition channel on the working characteristics of the solid type ignition device of the liquid-propellant rocket engine was analyzed and experimentally tested. The results showed that when the pressure in the combustion chamber was atmospheric pressure, under condition II, the gas velocity at the throat of the ignition device did not reach the sonic velocity, and the position of sonic velocity moved to the downstream section of the ignition channel. Compared to condition I, the gas velocity and energy at the ignition outlet increased, which would be beneficial for initial ignition, and the gas pressure and temperature at the throat increased as well, indicating that the structural strength at the throat should be evaluated. The gas flow, gas pressure, and gas temperature at the ignition outlet decreased compared to working condition I, yet the changes were small and would have minimal effect on the ignition performance. During the pressure increase process in the combustion chamber, the gas pressure, velocity, temperature, flow, and energy at the ignition outlet experienced a steady stage in both working conditions before coming to an inflection point. The inflection point under condition II is smaller than that under condition I. To improve the ignition reliability, the working pressure of the ignition device should be further increased.

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