Kerosene Combustion Research Articles

Organization of Effective Combustion of Kerosene in a Channel at High Flow Velocities

A new method of initiation and effective burning of kerosene at supersonic velocities of the flow in a constant-section channel is considered as applied to combustion chambers of variable geometry. The regime of intense combustion occurs due to an external action of a package of gas-dynamic pulses with the energy varying in time. It is experimentally observed that this regime is retained if the action is terminated after the combustion process is organized in the expanding part of the combustor. It is demonstrated that the proposed method can be applied at flow temperatures and high velocities at which kerosene combustion is impossible without special tools for flame stabilization.

Organization of Effective Combustion of Kerosene in a Channel at High Flow Velocities

Organization of Effective Combustion of Kerosene in a Channel at High Flow Velocities

Organization of Effective Combustion of Kerosene in a Channel at High Flow Velocities

The boundaries of stable combustion in a flow of an aluminum particle–air mixture in a wide range of changes in an air-to-fuel ratio (0.1–2.0) are experimentally determined. A characteristic feature of the relationship of a flame blowoff velocity with the air-to-fuel ratio is revealed: it has two maxima. Taking into account the principle of the flame stabilization mechanism, based on the equality of the flow velocity at which the flame is blown off to the flame front propagation velocity, it is concluded that there are two maxima in the relationship of the front velocity with the air-to-fuel ratio, which correspond to the maximum values of heat release and combustion temperature of the aluminum particle–air mixture with an air-to-fuel ratio of 0.2 and 1.0. Previously, these maxima were obtained by other researchers in thermodynamic calculations.

Application of Synthesis Gas to Intensify Kerosene Combustion in a Supersonic Flow

Application of Synthesis Gas to Intensify Kerosene Combustion in a Supersonic Flow

Modeling of Kerosene Combustion in a Supersonic Flow under the Action of a Throttling Jet

Modeling of Kerosene Combustion in a Supersonic Flow under the Action of a Throttling Jet

Evolution of mechanical properties of Ti6242S alloy after oxidation in air at 560°C: influence of solid salts deposits

Titanium alloys are widely used in aerospace applications due to their good ratio of weight versus mechanical properties. When exposed to air at 560°C, Ti6242S titanium alloy presents very good oxidation resistance: a very thin oxide layer forms at its surface and oxygen dissolution inside the metallic material is rather limited. However, in real functioning conditions of the plane, near seas or oceans, the atmosphere contains NaCl, that can crystallise at the surface of hot parts. An active corrosion mechanism is established in these conditions, with catastrophic effect on the material behaviour at high temperature: very thick and brittle oxide scales and very important damaging of the metal outer part. Another issue is the formation of Na2SO4 specie by reaction of NaCl with kerosene combustion gases (SO2/SO3), leading to mixed NaCl/Na2SO4 deposits. The effect of exposure conditions on the mechanical properties of titanium alloy Ti6242S was evaluated through tensile tests performed on the raw alloy and after oxidation in air at 560°C of the specimens: without any deposit, with NaCl solid deposit, with NaCl/Na2SO4 solid deposit. The evolution of mechanical properties was interpreted in connexion with the microstructural modifications that occur during the high temperature ageing.

Indoor Particle Concentrations, Size Distributions, and Exposures in Middle Eastern Microenvironments

There is limited research on indoor air quality in the Middle East. In this study, concentrations and size distributions of indoor particles were measured in eight Jordanian dwellings during the winter and summer. Supplemental measurements of selected gaseous pollutants were also conducted. Indoor cooking, heating via the combustion of natural gas and kerosene, and tobacco/shisha smoking were associated with significant increases in the concentrations of ultrafine, fine, and coarse particles. Particle number (PN) and particle mass (PM) size distributions varied with the different indoor emission sources and among the eight dwellings. Natural gas cooking and natural gas or kerosene heaters were associated with PN concentrations on the order of 100,000 to 400,000 cm−3 and PM2.5 concentrations often in the range of 10 to 150 µg/m3. Tobacco and shisha (waterpipe or hookah) smoking, the latter of which is common in Jordan, were found to be strong emitters of indoor ultrafine and fine particles in the dwellings. Non-combustion cooking activities emitted comparably less PN and PM2.5. Indoor cooking and combustion processes were also found to increase concentrations of carbon monoxide, nitrogen dioxide, and volatile organic compounds. In general, concentrations of indoor particles were lower during the summer compared to the winter. In the absence of indoor activities, indoor PN and PM2.5 concentrations were generally below 10,000 cm−3 and 30 µg/m3, respectively. Collectively, the results suggest that Jordanian indoor environments can be heavily polluted when compared to the surrounding outdoor atmosphere primarily due to the ubiquity of indoor combustion associated with cooking, heating, and smoking.

Initiation of kerosene combustion in supersonic air flow by a package of gas-dynamic pulses

A technique has been proposed and the possibility of its realization for the initiation of kerosene combustion in supersonic air flow in part of the combustion chamber (CC) of a constant cross section has been confirmed. The intense combustion regime is realized with the use of a package of pulses of variable energy and is preserved at a switch-off of the action after the combustion arrangement in the CC diverging part.

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

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.

Kerosene combustion in a supersonic flow

A new approach is proposed to the initiation of kerosene combustion in a supersonic airflow with the stagnation temperature below 2000 K, which consists of a pulsed-periodic gas-dynamic action on the flow. The experiments have shown that it is possible to implement a quasi-steady pulsed combustion mode by choosing the parameters of pulses: energy, duration, and frequency.

Initiation of Kerosene Combustion in a Supersonic Air Flow by a Bunch of Gas-Dynamic Pulses

In this paper, we propose a method to initiate combustion of kerosene in a supersonic air flow in part of a combustion chamber with a constant cross section and experimentally confirm the possibility of its implementation. An intensive combustion mode is implemented using a bunch of pulses with variable energy and is maintained when the exposure is turned off after the combustion is arranged in the diverging part of the combustion chamber.

Droplet combustion of kerosene augmented by stabilized nanoaluminum/oxidizer composite mesoparticles

Inclusion of energetic and chemically active nanoparticles into liquid fuels and propellants is known to affect resultant combustion dynamics. Recently, the activity of such nanoparticle additives has been promoted using electrospray to preassemble said particles into nitrocellulose-bound mesoparticle (MP) clusters of either nanoaluminum (nAl) or oxygen-carrying nanoparticle primaries. In either case, stability in kerosene with TOPO surfactant and isolated droplet burning rates estimated in a free-droplet combustion experiment increase substantially with the MP additive architecture. Burning rates benefit from violent physical mixing of droplet systems which occurs when the carried nanoparticles are energetic and/or chemically active, causing gas generation, additive transport to the flame, energy or oxygen release, and further gas liberation accelerating the process. In this study, this same physical underlying mechanism is seen superimposed with the effects of another advantage of electrospray particle assembly: MP composition flexibility. By mixing nAl with oxide nanoparticles to form composite MPs, these novel additives for hydrocarbons are employed to modify kerosene and their effects are found to be dependent on the oxidizer chosen. Most notably, nAl/CuO MPs show evidence of interparticle thermite reaction in the droplet system yielding a cooperative benefit of the two constituents relative to either alone in MPs. Use of oxidizer co-additives and the MP architecture with nAl represents a flexible and promising method of overcoming low burning rates of hydrocarbons with high as-received nAl loadings and provides expansive means of tunability to tailor nanofuel properties.

Design, Construction and Testing of a Kerosene Powered Multi Bird-Egg Incubator

The demand for poultry products such as eggs, meat and birds is on the increase daily that the world can no longer depend solely on the natural mode of incubation hence, the need for artificial incubators. But not all countries have stable electricity supply; therefore, there is a need to fabricate other types of incubators that will not be powered by electricity. Hence the choice of kerosene powered incubator. Heat generated by the combustion of kerosene was transferred into the incubator chamber by conduction and circulated by means of a 12 V D.C fan powered by a 12volt battery device. LM35 temperature sensor was used as the temperature sensing device. Both the turning of eggs and heat generated from heat source were controlled by mechanically incorporated driver motors. The LM35 temperature sensor and the two stepper motors were controlled by a PIC16F877 microcontroller. Insulation of the incubator chamber was achieved by lining the inner portion of the incubator with fiber materials. The incubator was designed and constructed using locally available material to reduce cost with little or no dependence on electricity and more user friendly. The incubator was tested with 90 eggs each for the three birds (i.e Chicken, Quail and Turkey). The result obtained shows that quail has the highest hatchability of 93% followed by Chicken with 84.4% and lastly turkey with 70%. The unit cost for the incubator is ₦95,000.00. The above average efficiencies implied that the Incubator performed efficiently and effectively. The birds also look healthy and strong several days after they were hatched.

Study on initial combustion characteristics of kerosene based on inductive charging ignition system

Spark ignition is an important method to achieve combustion of in-cylinder mixture. The inductive charging ignition is considered to be a simple and effective ignition method. This study presents a circuit simulation model of this ignition system in MATLAB/Simulink and the effects of charging voltage, charging time and multi-pulse charging interval on ignition energy were calculated and the ignition energy value was obtained. The experimental study of the ignition system in a constant volume vessel was carried out to explore the influence of ignition energy on the initial combustion of kerosene. The results show that the simulation results match well with the experimental results. With the increase of ignition energy, the initial flame propagation of kerosene shows speed fluctuations and the higher ignition energy makes the propagation speed of flame fluctuate more obviously.

Development of blend composition of aviation kerosene surrogate for the simulation of workflow of gas turbine engine combustion chamber

In this paper, the criteria for determining the composition and physicochemical properties of aviation kerosene were formulated. The data on the physicochemical properties of known kerosene surrogates were systematized and classified. The main classes of individual chemical components of aviation kerosene were determined, and the main representatives of these classes which were used in the preparation of surrogates, were investigated. Four- and six-component kerosene substitutes are proposed. The physical properties of the developed surrogates were validated according to the flow characteristics and the spray angle of the flame of a centrifugal fuel nozzle. The dependence of the flame speed on the composition of the mixture of developed kerosene surrogates was determined. The results of determining the composition of combustion products during the combustion of TS-1 brand aviation kerosene and its surrogates in a model combustion chamber were compared.

From fundamental study to practical application of kerosene in compression ignition engines: An experimental and modeling review

The use of kerosene in direct injection compression ignition engines is fundamentally due to the introduction of the Single Fuel Concept. As conventional direct injection compression ignition diesel engines are made specifically to use diesel fuel, the usage of kerosene will affect engine emissions and performance due to differences between the fuel properties of kerosene and diesel. As a result, in order for kerosene to be properly and efficiently used in diesel engines, it is needful for the scientific community to know the properties of kerosene, its autoignition and combustion characteristics, as well as its emissions formation behavior under diesel engine operating conditions. Moreover, it is desirable to know the progress made in the development of suitable kerosene surrogates for engine applications as it is a crucial step toward the development of reliable chemical reaction mechanisms for numerical simulations. Therefore, in this work, a comprehensive review is carried out systematically to better understand the characteristics and behavior of kerosene under direct injection compression ignition engine relevant conditions. In this review work, the fuel properties of kerosene are summarized and discussed. In addition, fundamental autoignition studies of kerosene in shock tube, rapid compression machine, fuel ignition tester, ignition quality tester, constant volume combustion chamber, and engine are compiled and evaluated. Furthermore, experimental studies of kerosene spray and combustion in constant volume combustion chambers are examined. Also, the experimental investigations of kerosene combustion and emissions in direct injection compression ignition engines are discussed. Moreover, the development of kerosene surrogates, their chemical reaction mechanisms, and the modeling of kerosene combustion in direct injection compression ignition engines are summarized and talked about. Finally, recommendations are also given to help researchers focus on the areas which are still severely lacking.

An improved WSGG model for exhaust gases of aero engines within broader ranges of temperature and pressure variations

Advanced aero engines operate at high temperatures and pressures to improve thermal efficiency and power output, thus thermal radiation becomes a significant mode of heat transfer for exhaust gases. The existing gaseous radiative models for atmosphere are not suitable for the application in aero engines due to the huge pressure variation of exhaust gases. In this work, an improved weighted sum of gray gases (WSGG) model for mixtures of H2O and CO2 within broader ranges of temperature and pressure variations is proposed. The mole ratio of H2O and CO2 is fixed at 1/1, which represents typical products of stoichiometric combustion of kerosene. The weighting factors, which only relate to the temperature in previous WSGG models, are modified by taking into account the effects of both temperatures and pressures. The coefficients of the improved WSGG model are obtained based on the up-to-date HITEMP-2010 database, and they are valid for the temperatures varying from 500 K to 2500 K, pressures ranging from 1 atm to 30 atm, and pressure path-lengths ranging from 0.0001 atm·m to10 atm·m. To access the accuracy of the coefficients, the improved WSGG model and other two traditional WSGG models are applied to the solution of the radiative heat transfer with the discrete ordinate method, and the comparison is conducted with the benchmark line-by-line calculations. The results indicate that the improved WSGG model has much higher accuracy in the simulation of gaseous radiative heat transfer for exhaust gases of aero engines.

Aerosol light absorption from optical measurements of PTFE membrane filter samples: sensitivity analysis of optical depth measures

Abstract. Mass absorption cross section (MAC) measurements of atmospherically relevant aerosols are required to quantify their effect on Earth's radiative budget. Estimating aerosol light absorption from transmittance and/or reflectance measurements through filter deposits is an attractive option because of their ease of deployment in field settings, low cost, and the ability to revisit previously analyzed samples. These measurements suffer from artifacts that depend on a given filter measurement system and aerosol optics. Empirical correction algorithms are available for commercial instruments equipped with optically thick fiber filters, but optically thin filter media have not been characterized in detail. Here, we present empirical relationships between particle light absorption optical depth – measured using multiwavelength integrated photoacoustic spectrometers – and filter optical depth measurements for polytetrafluoroethylene (PTFE) membrane filter samples of carbonaceous aerosols generated from combustion of diverse biomass fuels and kerosene (surrogate for fossil fuel combustion). Through radiative transfer modeling, we assessed the suitability of three measures of filter-based optical depth for robustly describing particulate-phase light absorption over a range of single scattering albedo (SSA) values: (1) ODs – a measure of transmission of the fraction of incident radiation that is not backscattered by the filter system – which utilizes transmittance and reflectance of the sample side of the filter; (2) the commonly used ODc, which uses transmittance and reflectance of the clean side of the filter; and (3) ATN or the Beer–Lambert attenuation. Modeling results were also validated experimentally, with ODs showing the least variability around the mean in this multidimensional parameter space. We establish a simple, wavelength-independent formulation for calculating aerosol MAC and absorption coefficients from measurements of ODs. We find the ratio between in situ particulate absorption optical depth and ODs to be inversely proportional to aerosol SSA. Our findings underscore that ODs is a better optical depth measure than ODc for applying appropriate correction factors when estimating particle-phase light absorption from filter-based techniques.

Control Oriented Model for Expander Cycle Scramjet

As a efficient and simple design, expander cycle is widely applied in LRE engineering, but it is seldomly used on scramjet research. In order to establish a complete mathematical model for expander cycle scramjet, a control-oriented model for expander cycle scramjet is proposed in this paper. This model consists of four major parts: combustor, cooling channel, turbo pump and nozzle and gives the result of pressure, temperature, mach number and velocity distribution of combustor and cooling channel and is capable of simulate both pure supersonic combustion mode and supersonic shock wave mode of the combustor. Each part is given by specific mathematical description, which contains the calculation of airflow, combustion, heat transfer and thermal cracking of kerosene. By putting all these parts together, a complete model is formed. This model is proposed to calculate the performance and condition of the engine precisely, comprehensively, swiftly and can be directly used in further study.

On Low-Emission Annular Combustor Based on Designing of Liner Air Admission Holes

Numerical experiments was carried out to predict the total temperature characteristics and formation of nitrogen oxide emissions and pattern factor in an annular combustor liner based on geometrical parameters and location and rows of different air admission holes, for 6 various cases, using computational fluid dynamics (CFD) .The simulation has been performed using ANSYS CFX including finite rate chemistry and eddy dissipation model, for simulation of liquid kerosene (Jet A) – air combustion after fuel droplet evaporation. The spray modeling was performed, including Rosin-Rammler droplet distribution. Thermal and prompt nitrogen oxide (NO x ) formation was performed to predicting NO x emission characteristics with a k -e model of turbulent. In this investigation the 3D CAD model of the realistic annular combustion chamber is presented for the simulation with double radial air swirler for the better mixing fuel with air. Beside this the characteristic and the flame structure is presented including the contour plots of total temperature and NO concentration at the outlet of the combustor liner and in cross section plane along the X axis from the injector center of the combustor including the chart of the velocity and NO, CO, CO 2 , O 2 and the total temperature along the liner from the injector center. For the combustion of kerosene with air 2 step kinetic schemes are presented in this study. The results show that the best result with the low concentration of NO is the case 5 but with a high percentage of pressure drop and the case 3 have the maximum concentration of NO with the low percentage of pressure drop.