<h1>Mathematical model of the combustion process for turbojet engine based on fuel properties</h1>
			<ul class="item-list">
	        	        <li>
	            Tomasz Białecki	            	            <abbr title="This is the corresponding author for this article">*</abbr>
	            	            	                <a href="mailto:tomasz.bialecki@itwl.pl" class="tiny-icon email-link mx-1" title="Email Tomasz Białecki">
	                    Email
	                </a>
	            	            	            <sup aria-label="Affiliated with Fuels and Lubricant Division, Air Force Institute of Technology, Warsaw, 01-494, PL">
	                1	            </sup>
	            	        </li>
	        	    </ul>
	    	    <ul class="affiliations" aria-hidden="true">
	        <li>Fuels and Lubricant Division, Air Force Institute of Technology, Warsaw, 01-494, PL</li>	    </ul>
	    
<h2>Abstract</h2>
<p>This paper presents the impact of the alternative fuels properties on the parameters characterizing the combustion process in a turbojet engine, expressed in the form of a mathematical model. Laboratory tests, bench tests and a regression analysis of the obtained results were conducted. The developed and published combustion process models were briefly described. It has been demonstrated that these models were insufficient in taking into account the impact of fuel properties on the course of the combustion process. The experimental data enabled developing a mathematical model of the combustion process using statistical methods. The developed model, unlike other currently known models, takes into account the chemical composition of the fuel to a greater extent, which is characterized by its physicochemical properties. Mathematical model enables predicting engine operating parameters and the emissions characteristics, based on analysing laboratory test results, and can be used as a tool verifying the environmental impact of new fuels, through predicting the exhaust gas emissions.</p><hr/><section><h2>Introduction</h2>
<p>The primary fuel used to power gas turbine engines is fossil jet fuel. For decades, the chemical composition of these fuels was modifying together with technological progress and experience in exploitation [
<a href="#CR1"><sup>1</sup></a>
].</p>
<p>The fuels are mainly mixtures of hydrocarbons, obtained from processing of crude oil (conventional fuels), supplemented with enriching additives that improve their operational parameters [
<a href="#CR2"><sup>2</sup></a>
]. Jet fuel is composed primarily of paraffinic and cycloparaffinic hydrocarbons, aromas and olefins [
<a href="#CR3"><sup>3</sup></a>
]. The composition depends on the used crude oil and its refining technology. For this reason, this type of fuel is not defined by the content of individual hydrocarbons, but through regulatory requirements.</p>
<p>Jet fuel chemical composition determines their operational properties. The content of individual hydrocarbons determines fuel properties, such as calorific value, chemical stability, combustion quality and many other operational properties. This relationship can be expressed as follows [
<a href="#CR4"><sup>4</sup></a>
]:
<section id="Equ1"><mml:math display="block" id="Equ1_Math"><mml:mrow><mml:msub><mml:mi mathvariant="italic">F</mml:mi><mml:mi mathvariant="italic">p</mml:mi></mml:msub><mml:mo>=</mml:mo><mml:mspace width="0.166667em"/><mml:mi mathvariant="italic">f</mml:mi><mml:mfenced close=")" open="("><mml:msub><mml:mi mathvariant="italic">Ch</mml:mi><mml:mi mathvariant="italic">f</mml:mi></mml:msub></mml:mfenced></mml:mrow></mml:math><tex-math id="Equ1_TeX"><![CDATA[\documentclass[12pt]{minimal}
				\usepackage{amsmath}
				\usepackage{wasysym}
				\usepackage{amsfonts}
				\usepackage{amssymb}
				\usepackage{amsbsy}
				\usepackage{mathrsfs}
				\usepackage{upgreek}
				\setlength{\oddsidemargin}{-69pt}
				\begin{document}$$\it F_{p} = \, f\left( {{\textit{Ch}}_{f} } \right)$$\end{document}]]></tex-math><graphic specific-use="web" mime-subtype="GIF" xlink:href="40095_2022_489_Article_Equ1.gif"/></section>
where 
<em>F</em>
<sub><em>p</em></sub>
 is the fuel properties and 
<em>Ch</em>
<sub><em>f</em></sub>
 is the chemical composition of fuel.</p>
<p>Recently, the petroleum industry has been focused on developing technologies that utilize non-petroleum raw materials in the course of production [
<a href="#CR5"><sup>5</sup></a>
]. This is due to economic, security and environmental factors. Currently, there are seven approved technologies of synthetic components originating from unconventional sources, which can be blended with fossil fuel up to 50%. They are listed in standard ASTM D7655 [
<a href="#CR6"><sup>6</sup></a>
] and are approved for use in aircraft turbine engines.</p>
<p>The complex process of approving fuels containing synthetic hydrocarbons for use in aircraft turbine engines resulted in limiting the previously widespread diversity of hydrocarbon groups within their composition. Changing the hydrocarbon structure of the fuel, besides affecting its properties, also modifies the mechanism of reactions, making up the complex combustion process.</p>
<p>The papers [
<a href="#CR7"><sup>7</sup></a>
, 
<a href="#CR8"><sup>8</sup></a>
, 
<a href="#CR9"><sup>9</sup></a>
, 
<a href="#CR10"><sup>10</sup></a>
, 
<a href="#CR11"><sup>11</sup></a>
, 
<a href="#CR12"><sup>12</sup></a>
–
<a href="#CR13"><sup>13</sup></a>
] were used as a basis to present the relationships between the parameters characterizing the combustion process in a turbojet engine and the physicochemical properties of the fuel (Fig. 
<a href="#Fig1"><sup>1</sup></a>
). The physicochemical properties of fuel are quantitative variables, since they can adopt specific numerical values. However, a review of the source literature enabled only defining them as qualitative variables. The reason for this is that these relationships were collected based on experiments and observations, without a determined quantitative impact on the combustion process.
<figure id="Fig1"><h3>Fig. 1</h3>
<figcaption><p>Dependence of parameters characterizing the combustion process on fuel properties (H
<sub>c</sub>
—neat heat of combustion, D—density, V—viscosity, T
<sub>90</sub>
—90% distillation temperature, AP—aromatic content, C
<sub>f</sub>
—fuel consumption, T
<sub>3</sub>
—combustion chamber temperature, E
<sub>GT</sub>
—exhaust gas temperature, CO—CO emission, CO
<sub>2</sub>
—CO
<sub>2</sub>
 emission, NO
<sub>x</sub>
—NO
<sub>x</sub>
 emission)</p></figcaption>
<img src="40095_2022_489_Fig1_HTML.png" /></figure></p></section>
<section><h2>Combustion process models</h2>
<p>In the case of jet engines, combustion process consists of three stages. The first one involves fuel atomization, which means using the injectors to supply the combustion chamber with a fuel mist, and consists of very finely dispersed fuel droplets [
<a href="#CR14"><sup>14</sup></a>
]. During the second stage, the air stream mixes with the fuel mist (fine fuel droplets increase the evaporation volume of the injected liquid), creating a fuel-air mixture. In the case of older engine designs, fuel is supplied to the combustion chamber via evaporators, where it evaporates in contact with a hot tube (evaporator), and the vapours are lifted with air to the combustion zone. The last stage is the ignition of the fuel-air mixture, resulting from a flame (in the combustion zone), and combustion, which spreads quickly in all areas where air and fuel are mixed within flammability limits [
<a href="#CR15"><sup>15</sup></a>
].</p>
<p>Combustion process chemistry and rate depend on the engine design [
<a href="#CR16"><sup>16</sup></a>
], as well as the properties of used fuel [
<a href="#CR17"><sup>17</sup></a>
]. Fuel must be injected, vaporized and mixed with air in the combustion chamber, before combustion occurs. The extent to which these processes affect combustion greatly depends on the physicochemical properties of fuel. This relationship can be expressed as follows:
<section id="Equ2"><mml:math display="block" id="Equ2_Math"><mml:mrow><mml:msub><mml:mi>E</mml:mi><mml:mi>p</mml:mi></mml:msub><mml:mo>=</mml:mo><mml:mspace width="0.166667em"/><mml:mi>f</mml:mi><mml:mfenced close=")" open="("><mml:msub><mml:mi>F</mml:mi><mml:mi>p</mml:mi></mml:msub></mml:mfenced></mml:mrow></mml:math><tex-math id="Equ2_TeX"><![CDATA[\documentclass[12pt]{minimal}
				\usepackage{amsmath}
				\usepackage{wasysym}
				\usepackage{amsfonts}
				\usepackage{amssymb}
				\usepackage{amsbsy}
				\usepackage{mathrsfs}
				\usepackage{upgreek}
				\setlength{\oddsidemargin}{-69pt}
				\begin{document}$$E_{p} = \, f\left( {F_{p} } \right)$$\end{document}]]></tex-math><graphic specific-use="web" mime-subtype="GIF" xlink:href="40095_2022_489_Article_Equ2.gif"/></section>
<section id="Equ3"><mml:math display="block" id="Equ3_Math"><mml:mrow><mml:msub><mml:mi>E</mml:mi><mml:mi>g</mml:mi></mml:msub><mml:mo>=</mml:mo><mml:mspace width="0.166667em"/><mml:mi>f</mml:mi><mml:mfenced close=")" open="("><mml:msub><mml:mi>F</mml:mi><mml:mi>p</mml:mi></mml:msub></mml:mfenced></mml:mrow></mml:math><tex-math id="Equ3_TeX"><![CDATA[\documentclass[12pt]{minimal}
				\usepackage{amsmath}
				\usepackage{wasysym}
				\usepackage{amsfonts}
				\usepackage{amssymb}
				\usepackage{amsbsy}
				\usepackage{mathrsfs}
				\usepackage{upgreek}
				\setlength{\oddsidemargin}{-69pt}
				\begin{document}$$E_{g} = \, f\left( {F_{p} } \right)$$\end{document}]]></tex-math><graphic specific-use="web" mime-subtype="GIF" xlink:href="40095_2022_489_Article_Equ3.gif"/></section>
where 
<em>E</em>
<sub><em>p</em></sub>
 is the engine operating parameters and 
<em>E</em>
<sub><em>g</em></sub>
 is the exhaust gas emission.</p>
<p>Mathematical modelling can be applied for solving problems involving phenomenon repeatability or similarity. However, due to the successive stages of the combustion process (atomization, evaporation and ignition), and the large number of elementary hydrocarbon oxidation reactions, an attempt to describe it using a model is not a simple task.</p>
<p>The following sections present the previously developed combustion process models, together with their limitations.</p>
<section><h2>ARP 1533C model</h2>
<p>Hydrocarbon fuel combustion model was presented in ARP 1533C [
<a href="#CR18"><sup>18</sup></a>
]. It includes a methodology for calculating the emission indices of exhaust gas components, fuel-to-air ratio and the combustion efficiency based on carbon monoxide (CO), carbon dioxide (CO
<sub>2</sub>
), hydrocarbon and nitrogen oxides (NO
<sub>x</sub>
) measurements. The combustion process model within the procedure presents an equation for the combustion of a single mole of hydrocarbon fuel and atmospheric air.</p>
<p>This model reduces multi-component hydrocarbon fuels to the form of an averaged chemical formula, e.g. C
<sub>11,6</sub>
H
<sub>22</sub>
 for Jet A fuel. However, hydrocarbons with the same number of carbon atoms exhibit various physicochemical properties. Hence, the conclusion that the averaged chemical formula adopted for various fuels (even petroleum-derived) is a huge simplification. Furthermore, the authors of [
<a href="#CR19"><sup>19</sup></a>
] confirmed that one chemical compound with several isomers, thus the same chemical formula, is characterized by different physicochemical properties, assigned to individual isomers.</p></section>
<section><h2>CFD model</h2>
<p>Computational fluid dynamics (CFD) modelling analyses chemical transformation of hundreds of compounds expressed by thousands of chemical reactions, taking into account the fact that the number of elementary reactions of hydrocarbon oxidation depends on their structure and falls within a range from several hundred to several thousand [
<a href="#CR20"><sup>20</sup></a>
]. However, a detailed numerical simulation of actual fuel combustion is still beyond reach, when it is applied to any fuel that is not a pure component or a mix of more than several components [
<a href="#CR21"><sup>21</sup></a>
].</p>
<p>One of the applied simplifications is the process being represented by a minor number of elementary reactions, making up a subsequent reaction chain. These so-called global mechanisms are stoichiometric relationships, for which approximated kinetic equations can be determined [
<a href="#CR22"><sup>22</sup></a>
].</p>
<p>Another method is modelling the combustion process using surrogate fuels. They are a simplified equivalent of fuel, composed of one or more selected hydrocarbons that represent the main fuel ingredients. The idea behind minimizing the number of ingredients is obtaining a model fuel that exhibits physicochemical properties and combustion characteristics similar to the conventional jet fuel [
<a href="#CR7"><sup>7</sup></a>
]. Although there are numerous models, such simplification of the mix composition that best mimics real-life fuel being tested remains a significant challenge.</p>
<p>Furthermore, it should be noted that CFD modelling often omits the properties of the tested fuel or takes their values from a library (averaged parameters). The authors of [
<a href="#CR23"><sup>23</sup></a>
] studied the combustion of fuel and its blends with added components, as well as the emission characteristics, describing fuel properties with only two values, i.e., density and viscosity, whereas [
<a href="#CR24"><sup>24</sup></a>
] describes conventional and synthetic fuels only with an average formula C
<sub>m</sub>
H
<sub>n</sub>
, the hydrogen-to-carbon ratio (information derived from the average formula C
<sub>m</sub>
H
<sub>n</sub>
) and net heat of combustion. As highlighted before, fuel composition impacts its physicochemical properties, therefore, adopting average data from libraries or taking into account the minimum number of parameters is a very simplified approach and prevents studying the impact of fuel properties on the combustion process.</p></section>
<section><h2>Statistical model</h2>
<p>During literature review, one publication [
<a href="#CR25"><sup>25</sup></a>
] was found which presents combustion process model for turbojet engine fuel, developed using statistical methods. However, its objective was to statistically analyse the ICAO Aircraft Engine Emissions Databank, in order to estimate the emissions in new turbofan engines. The development of the obtained statistical model did not take fuel properties into account and was based purely on a historical database. Furthermore, no statistical model of the combustion process based on the experimental studies was found.</p>
<p>The presented and characterized combustion process models focus on its various elements; however, in the majority of cases they assume that fuel is the element of the system, the change of which is insignificant or that is not changed at all. This is most probably due to the fact that so far, the modelling process was implemented by turbojet engine engineers. Their primary objective was to improve the engine operating parameters, which was not associated with changing the used fuel as the propulsion source. The process of introducing synthetic fuels to the aviation industry enforced the necessity to conduct work on modifying fuel physicochemical composition and stop perceiving it as a constant value in modelling the combustion process.</p>
<p>In the light of the above, it seems appropriate to analyse combustion process with greater emphasis on fuel, as a variable within this process, which has been defined as the objective of this paper.</p></section></section>
<section><h2>3. Materials and methods</h2>
<section><h2>Tested fuels</h2>
<p>Conventional jet fuel and its blends with synthetic components form two different technologies approved by ASTM D7566 and biobutanol, which were used in this study and marked as follows:
<ul><li><p>Conventional jet fuel (Jet A-1)—Jet;</p></li>
<li><p>Blend of Jet A-1 with synthetic component from hydroprocessed esters and fatty acids (HEFA), feedstock: used cooking oil (75:25)—25UCO;</p></li>
<li><p>Blend of Jet A-1 with synthetic component from HEFA, feedstock: used cooking oil (50:50)—50UCO;</p></li>
<li><p>Blend of Jet A-1 with synthetic component from HEFA, feedstock: used cooking oil (25:75)—75UCO;</p></li>
<li><p>Blend of Jet A-1 with synthetic component from HEFA, feedstock: camelina (50:50)—50CAM;</p></li>
<li><p>Blending synthetic component from technology approved by ASTM D7566 (other than HEFA)—S;</p></li>
<li><p>Blend of Jet A-1 with synthetic component from S (75:25)—25S;</p></li>
<li><p>Blend of Jet A-1 with synthetic component from S (50:50)—50S;</p></li>
<li><p>Blend of Jet A-1 with synthetic component from S (25:75)—75S;</p></li>
<li><p>Blend of Jet A-1 with biobutanol (75:25)—25but;</p></li>
<li><p>Blend of Jet A-1 with biobutanol (50:50)—50but;</p></li>
<li><p>Blend of Jet A-1 with biobutanol (25:75)—75but.</p></li></ul></p>
<p>HEFA and S components are specified in standard ASTM D7566 and, after blending with fossil fuel in a volume of up to 50%, can be supplied to aviation turbine engines, whereas biobutanol (n-butanol) is an alcohol that was produced through fermenting the 
<em>C</em>
<sub>5</sub>
 and 
<em>C</em>
<sub>6</sub>
 sugars. Choosing n-butanol, unlike other components, resulted from the need to increase the range of measured fuel properties, even going beyond the area set out by normative documents. Prepared fuel samples were subjected to selected laboratory tests (Table 
<a href="#Tab1"><sup>1</sup></a>
), determined by their impact on the combustion process.
<figure id="Tab1"><h3>Table 1</h3>
<figcaption><p>Selected fuel properties and their impact on the combustion process</p></figcaption>
<table frame="hsides" rules="groups"><thead><tr><th align="left"><p>Property</p></th><th align="left"><p> Impact on the combustion process</p></th></tr></thead><tbody><tr><td align="left"><p>Density at 15 °C, kg/m<sup>3</sup></p></td><td align="left"><p>Is taken into account during aircraft range calculations—the amount of fuel necessary to secure the combustion process</p></td></tr><tr><td align="left"><p>Viscosity at − 20 °C, mm<sup>2</sup>/s</p></td><td align="left"><p>Determines the resistance of fuel flow through filters and nozzles; it also affects the injection process and fuel atomization in the combustion chamber</p></td></tr><tr><td align="left"><p>Net heat of combustion, MJ/kg</p></td><td align="left"><p>Determines the engine efficiency and its characteristics and is taken into account during aircraft range calculations</p></td></tr><tr><td align="left"><p>Aromatic content, % (V/V)</p></td><td align="left"><p>Tendency to incomplete combustion (smoke)</p></td></tr><tr><td align="left"><p>Distillation:</p><p>90% v/v at °C, °C</p></td><td align="left"><p>Affects the rate of fuel evaporation, combustion chamber temperature and exhaust gas temperature</p></td></tr></tbody></table></figure></p></section>
<section><h2>Engine</h2>
<p>Bench testing was conducted on a Miniature Jet Engine Test Rig (MiniJETRig) with miniature turbojet engine GTM 140 for jet fules combustion process research. The test rig is used in research and development work, mainly for testing alternative fuels for aviation [
<a href="#CR26"><sup>26</sup></a>
, 
<a href="#CR27"><sup>27</sup></a>
–
<a href="#CR28"><sup>28</sup></a>
]. Its detailed description can be found in [
<a href="#CR29"><sup>29</sup></a>
].</p>
<p>Previous research with the use of the test rig enabled developing a procedure for testing [
<a href="#CR30"><sup>30</sup></a>
]. Nonetheless, given the fact that turbojet engine operating parameters change at various rotational speeds, only one speed, namely 70000 rpm, was selected for the purpose of the paper (Fig. 
<a href="#Fig2"><sup>2</sup></a>
). This speed corresponds to 30% of the maximum thrust achieved by the engine and characterizes its lowest thermal load.
<figure id="Fig2"><h3>Fig. 2</h3>
<figcaption><p>Profile of engine test</p></figcaption>
<img src="40095_2022_489_Fig2_HTML.png" /></figure></p></section>
<section><h2>Measurement equipment</h2>
<p>Each tested fuel was bench-tested at least twice in the course of the research. The parameter results from the last 30 s (stabilization) were taken in the case of each engine test as measurement data sets that were averaged and considered as the measurement result (for 
<em>T</em>
<sub>3</sub>
, 
<em>E</em>
<sub>GT</sub>
 and 
<em>C</em>
<sub><em>f</em></sub>
) or as a value to calculate 
<em>EI</em>
 (for CO, CO
<sub>2</sub>
 and NO
<sub>x</sub>
).</p>
<p>The engine tests involved recording parameters characterizing the combustion process in a turbojet engine:
<ul><li><p>Thermodynamic state, namely fuel consumption, mean temperature in the combustion chamber (measured by six thermocouples located circumferentially) and the exhaust gas temperature (measured downstream of the exhaust nozzle),</p></li>
<li><p>Exhaust gas emissions, namely carbon monoxide, carbon dioxide and nitrogen oxides.</p></li></ul></p>
<p>The details of the equipment used to measure the exhaust concentration of CO, CO
<sub>2</sub>
 and NO
<sub>x</sub>
 are shown in Table 
<a href="#Tab2"><sup>2</sup></a>
.
<figure id="Tab2"><h3>Table 2</h3>
<figcaption><p>Details of measurement equipment for gas emissions</p></figcaption>
<table frame="hsides" rules="groups"><thead><tr><th align="left"><p>Parameter</p></th><th align="left"><p>Sensor type</p></th><th align="left"><p>Range</p></th><th align="left"><p>Least count</p></th><th align="left"><p>Accuracy</p></th></tr></thead><tbody><tr><td align="left"><p>CO</p></td><td align="left"><p>Electrochemical</p></td><td char="–" align="char"><p>0–2 000</p></td><td char="." align="char"><p>0.1 ppm</p></td><td align="left"><p> ± 5% of the measured value</p></td></tr><tr><td align="left"><p>CO<sub>2</sub></p></td><td align="left"><p>Infrared</p></td><td char="–" align="char"><p>0–25</p></td><td char="." align="char"><p>0.01%</p></td><td align="left"><p> ± 5% of the measured value</p></td></tr><tr><td align="left"><p>NO</p></td><td align="left"><p>Electrochemical</p></td><td char="–" align="char"><p>0–500</p></td><td char="." align="char"><p>0.1 ppm</p></td><td align="left"><p> ± 5% of the measured value</p></td></tr><tr><td align="left"><p>NO<sub>2</sub></p></td><td align="left"><p>Electrochemical</p></td><td char="–" align="char"><p>0–100</p></td><td char="." align="char"><p>0.1 ppm</p></td><td align="left"><p> ± 5 ppm</p></td></tr></tbody></table></figure></p>
<p>Emissions of gaseous exhaust gas components: CO, CO
<sub>2</sub>
 and NO
<sub>x</sub>
 converted and presented in the form of emission indices, according to [
<a href="#CR31"><sup>31</sup></a>
]:
<section id="Equ4"><mml:math display="block" id="Equ4_Math"><mml:mrow><mml:msub><mml:mtext>EI</mml:mtext><mml:mi>i</mml:mi></mml:msub><mml:mo>=</mml:mo><mml:mfrac><mml:msub><mml:mtext>X</mml:mtext><mml:mtext>i</mml:mtext></mml:msub><mml:mrow><mml:msub><mml:mtext>X</mml:mtext><mml:mtext>CO</mml:mtext></mml:msub><mml:mo>+</mml:mo><mml:msub><mml:mtext>X</mml:mtext><mml:msub><mml:mtext>CO</mml:mtext><mml:mn>2</mml:mn></mml:msub></mml:msub></mml:mrow></mml:mfrac><mml:mfrac><mml:msub><mml:mtext>xMW</mml:mtext><mml:mtext>i</mml:mtext></mml:msub><mml:msub><mml:mtext>MW</mml:mtext><mml:mtext>f</mml:mtext></mml:msub></mml:mfrac></mml:mrow></mml:math><tex-math id="Equ4_TeX"><![CDATA[\documentclass[12pt]{minimal}
				\usepackage{amsmath}
				\usepackage{wasysym}
				\usepackage{amsfonts}
				\usepackage{amssymb}
				\usepackage{amsbsy}
				\usepackage{mathrsfs}
				\usepackage{upgreek}
				\setlength{\oddsidemargin}{-69pt}
				\begin{document}$${\text{EI}}_{i} = \frac{{\text{X}_{\text{i}} }}{{\text{X}_{{{\text{CO}}}} + \text{X}_{{ {\text{CO}}_{2} }} }}\frac{{\text{x}{\text{MW}}_{\text{i}} }}{{{\text{MW}}_{\text{f}} }}$$\end{document}]]></tex-math><graphic specific-use="web" mime-subtype="GIF" xlink:href="40095_2022_489_Article_Equ4.gif"/></section>
where 
<em>EI</em>
<sub><em>i</em></sub>
 is the emission index of species 
<em>i</em>
, 
<em>X</em>
<sub><em>i</em>
/
<em>CO/CO</em></sub>
<sub><em>2</em></sub>
 is the mole fractions of species 
<em>i</em>
/
<em>CO</em>
/
<em>CO</em>
<sub><em>2</em></sub>
, x is the number of moles of carbon in a mole of fuel, and 
<em>MW</em>
<sub><em>i</em></sub>
/
<em>MW</em>
<sub><em>f</em></sub>
 is the molecular weights of species 
<em>i</em>
/fuel.</p></section></section>
<section><h2>Results</h2>
<p>Selected properties of the fuel samples are presented in Table 
<a href="#Tab3"><sup>3</sup></a>
, while Table 
<a href="#Tab4"><sup>4</sup></a>
 presents the results of the bench tests.
<figure id="Tab3"><h3>Table 3</h3>
<figcaption><p>Selected properties of the fuel samples</p></figcaption>
<table frame="hsides" rules="groups"><thead><tr><th align="left" rowspan="2"><p>Property</p></th><th align="left" rowspan="2"><p>Test method</p></th><th align="left" rowspan="2"><p>Requirements ASTM D1655/ASTM D7566</p></th><th align="left" colspan="12"><p>Test result</p></th></tr><tr><th align="left"><p>Jet</p></th><th align="left"><p>25but</p></th><th align="left"><p>50but</p></th><th align="left"><p>75but</p></th><th align="left"><p>25UCO</p></th><th align="left"><p>50UCO</p></th><th align="left"><p>75UCO</p></th><th align="left"><p>50CAM</p></th><th align="left"><p>25S</p></th><th align="left"><p>50S</p></th><th align="left"><p>75S</p></th><th align="left"><p>S</p></th></tr></thead><tbody><tr><td align="left"><p>Density at 15 °C, kg/m<sup>3</sup></p></td><td align="left"><p>ASTM D 4052</p></td><td align="left"><p>775–840</p></td><td char="." align="char"><p>790.1</p></td><td char="." align="char"><p>794.0</p></td><td char="." align="char"><p>800.1</p></td><td char="." align="char"><p>806.5</p></td><td char="." align="char"><p>779.8</p></td><td char="." align="char"><p>770.7</p></td><td char="." align="char"><p>761.4</p></td><td char="." align="char"><p>779.9</p></td><td char="." align="char"><p>782.9</p></td><td char="." align="char"><p>773.8</p></td><td char="." align="char"><p>766.0</p></td><td char="." align="char"><p>758.6</p></td></tr><tr><td align="left"><p>Viscosity at -20 °C, mm<sup>2</sup>/s</p></td><td align="left"><p>ASTM D 445</p></td><td align="left"><p>Max 8.0</p></td><td char="." align="char"><p>3.069</p></td><td char="." align="char"><p>4.070</p></td><td char="." align="char"><p>6.320</p></td><td char="." align="char"><p>8.092</p></td><td char="." align="char"><p>3.227</p></td><td char="." align="char"><p>3.481</p></td><td char="." align="char"><p>3.754</p></td><td char="." align="char"><p>4.968</p></td><td char="." align="char"><p>3.312</p></td><td char="." align="char"><p>3.699</p></td><td char="." align="char"><p>4.155</p></td><td char="." align="char"><p>4.766</p></td></tr><tr><td align="left"><p>Net heat of combustion, MJ/kg</p></td><td align="left"><p>ASTM D 3338</p></td><td align="left"><p>Min 42.8</p></td><td char="." align="char"><p>43.31</p></td><td char="." align="char"><p>40.73</p></td><td char="." align="char"><p>38.18</p></td><td char="." align="char"><p>35.63</p></td><td char="." align="char"><p>43.54</p></td><td char="." align="char"><p>43.74</p></td><td char="." align="char"><p>43.95</p></td><td char="." align="char"><p>43.69</p></td><td char="." align="char"><p>43.49</p></td><td char="." align="char"><p>43.67</p></td><td char="." align="char"><p>43.84</p></td><td char="." align="char"><p>44.02</p></td></tr><tr><td align="left"><p>Aromatic content, % (V/V)</p></td><td align="left"><p>ASTM D1319 /calculative</p></td><td align="left"><p>Max 25.0</p></td><td char="." align="char"><p>15.1</p></td><td char="." align="char"><p>11.3</p></td><td char="." align="char"><p>7.6</p></td><td char="." align="char"><p>3.8</p></td><td char="." align="char"><p>11.3</p></td><td char="." align="char"><p>7.6</p></td><td char="." align="char"><p>3.8</p></td><td char="." align="char"><p>9.1</p></td><td char="." align="char"><p>11.3</p></td><td char="." align="char"><p>7.6</p></td><td char="." align="char"><p>3.8</p></td><td char="." align="char"><p>0</p></td></tr><tr><td align="left"><p>Distillation: 90% v/v at ºC, °C</p></td><td align="left"><p>ASTM D 86</p></td><td align="left"><p>Report</p></td><td char="." align="char"><p>213.5</p></td><td char="." align="char"><p>205.2</p></td><td char="." align="char"><p>200.5</p></td><td char="." align="char"><p>184.2</p></td><td char="." align="char"><p>224.7</p></td><td char="." align="char"><p>235.1</p></td><td char="." align="char"><p>241.7</p></td><td char="." align="char"><p>230.0</p></td><td char="." align="char"><p>213.0</p></td><td char="." align="char"><p>211.9</p></td><td char="." align="char"><p>209.7</p></td><td char="." align="char"><p>206.6</p></td></tr></tbody></table></figure>
<figure id="Tab4"><h3>Table 4</h3>
<figcaption><p>Bench test results</p></figcaption>
<table frame="hsides" rules="groups"><thead><tr><th align="left"><p>Fuel sample</p></th><th align="left"><p>Number of measurements</p></th><th align="left"><p><italic>T</italic><sub>3</sub></p></th><th align="left"><p><italic>E</italic><sub>GT</sub></p></th><th align="left"><p><italic>C</italic><sub><italic>f</italic></sub></p></th><th align="left"><p><italic>EI CO</italic></p></th><th align="left"><p><italic>EI CO</italic><sub>2</sub></p></th><th align="left"><p><italic>EI NO</italic><sub><italic>x</italic></sub></p></th></tr></thead><tbody><tr><td align="left"><p>Jet</p></td><td char="." align="char"><p>300</p></td><td char="." align="char"><p>531.8</p></td><td char="." align="char"><p>503.4</p></td><td char="." align="char"><p>2.154</p></td><td char="." align="char"><p>113.3</p></td><td char="." align="char"><p>2990</p></td><td char="." align="char"><p>1.63</p></td></tr><tr><td align="left"><p>25but</p></td><td char="." align="char"><p>450</p></td><td char="." align="char"><p>518.6</p></td><td char="." align="char"><p>495.5</p></td><td char="." align="char"><p>2.204</p></td><td char="." align="char"><p>113.0</p></td><td char="." align="char"><p>2793</p></td><td char="." align="char"><p>1.026</p></td></tr><tr><td align="left"><p>50but</p></td><td char="." align="char"><p>450</p></td><td char="." align="char"><p>518.9</p></td><td char="." align="char"><p>490.2</p></td><td char="." align="char"><p>2.214</p></td><td char="." align="char"><p>102.5</p></td><td char="." align="char"><p>2614</p></td><td char="." align="char"><p>0.866</p></td></tr><tr><td align="left"><p>75but</p></td><td char="." align="char"><p>450</p></td><td char="." align="char"><p>516.7</p></td><td char="." align="char"><p>489.5</p></td><td char="." align="char"><p>2.278</p></td><td char="." align="char"><p>96.6</p></td><td char="." align="char"><p>2422</p></td><td char="." align="char"><p>0.750</p></td></tr><tr><td align="left"><p>25UCO</p></td><td char="." align="char"><p>300</p></td><td char="." align="char"><p>537.2</p></td><td char="." align="char"><p>509.0</p></td><td char="." align="char"><p>2.133</p></td><td char="." align="char"><p>97.9</p></td><td char="." align="char"><p>2998</p></td><td char="." align="char"><p>1.46</p></td></tr><tr><td align="left"><p>50UCO</p></td><td char="." align="char"><p>300</p></td><td char="." align="char"><p>540.2</p></td><td char="." align="char"><p>513.5</p></td><td char="." align="char"><p>2.133</p></td><td char="." align="char"><p>94.2</p></td><td char="." align="char"><p>2987</p></td><td char="." align="char"><p>1.54</p></td></tr><tr><td align="left"><p>75UCO</p></td><td char="." align="char"><p>300</p></td><td char="." align="char"><p>542.0</p></td><td char="." align="char"><p>514.2</p></td><td char="." align="char"><p>2.132</p></td><td char="." align="char"><p>93.3</p></td><td char="." align="char"><p>2971</p></td><td char="." align="char"><p>1.62</p></td></tr><tr><td align="left"><p>50CAM</p></td><td char="." align="char"><p>300</p></td><td char="." align="char"><p>537.4</p></td><td char="." align="char"><p>510.5</p></td><td char="." align="char"><p>2.096</p></td><td char="." align="char"><p>103.5</p></td><td char="." align="char"><p>2973</p></td><td char="." align="char"><p>1.84</p></td></tr><tr><td align="left"><p>25S</p></td><td char="." align="char"><p>300</p></td><td char="." align="char"><p>530.9</p></td><td char="." align="char"><p>503.8</p></td><td char="." align="char"><p>2.155</p></td><td char="." align="char"><p>121.6</p></td><td char="." align="char"><p>2964</p></td><td char="." align="char"><p>1.64</p></td></tr><tr><td align="left"><p>50S</p></td><td char="." align="char"><p>300</p></td><td char="." align="char"><p>529.4</p></td><td char="." align="char"><p>501.0</p></td><td char="." align="char"><p>2.139</p></td><td char="." align="char"><p>130.8</p></td><td char="." align="char"><p>2936</p></td><td char="." align="char"><p>1.63</p></td></tr><tr><td align="left"><p>75S</p></td><td char="." align="char"><p>300</p></td><td char="." align="char"><p>530.4</p></td><td char="." align="char"><p>500.9</p></td><td char="." align="char"><p>2.167</p></td><td char="." align="char"><p>141.4</p></td><td char="." align="char"><p>2906</p></td><td char="." align="char"><p>1.63</p></td></tr><tr><td align="left"><p>S</p></td><td char="." align="char"><p>300</p></td><td char="." align="char"><p>530.0</p></td><td char="." align="char"><p>501.4</p></td><td char="." align="char"><p>2.187</p></td><td char="." align="char"><p>154.0</p></td><td char="." align="char"><p>2896</p></td><td char="." align="char"><p>1.66</p></td></tr></tbody></table></figure></p>
<p>The impact of synthetic components on the fuel properties, engine operating parameters and exhaust characteristics has been presented in previous works [
<a href="#CR27"><sup>27</sup></a>
, 
<a href="#CR32"><sup>32</sup></a>
, 
<a href="#CR33"><sup>33</sup></a>
]. The obtained results were used as a database for regression analysis.</p></section>
<section><h2>Development of mathematical model</h2>
<p>The main purpose of developing the model was an attempt to describe the relationships presented in Fig. 
<a href="#Fig1"><sup>1</sup></a>
 using quantitative features. Multiple regression was used to determine the effect of many independent variables on each dependent variable. During the analysis, the fuel properties were treated as independent variables and the parameters characterizing the combustion process as dependent variables (Fig. 
<a href="#Fig3"><sup>3</sup></a>
). Stepwise regression in R software was used to determine their relationship. It involves developing a model, which initially does not contain any explanatory variable, while every successive step expands the model with only such variables that significantly predict the dependent variable.
<figure id="Fig3"><h3>Fig. 3</h3>
<figcaption><p>Data used for regression analysis</p></figcaption>
<img src="40095_2022_489_Fig3_HTML.png" /></figure></p>
<p>Data sets are analysed with a certain, predetermined likelihood level, specified by a confidence interval. A confidence interval level of 95% was adopted, which means a 95% probability that the confidence interval will cover an unknown value of the estimated parameter.</p>
<p>The development of a regression model for each explained variable (parameter characterizing the combustion process) took into account only explanatory variables (fuel properties) shown in Fig. 
<a href="#Fig1"><sup>1</sup></a>
. Nonetheless, this figure only shows their qualitative relationships, and applying the regression will enable their quantitative correlations.</p>
<p>Each constructed model was rated and verified through checking the significance of all explanatory variables (using Snedecor’s F distribution), significance of partial regression coefficient (using Student’s t distribution), matching of the theoretical and experimental curves (using the 
<em>R</em>
<sup>2</sup>
 determination coefficient), lack of collinearity between independent variables (using the variance inflation factor), and conformity of the residuum and normal distributions (using the Shapiro–Wilk test).</p>
<p>The developed and positively verified linear regression equations presented together show the model of combustion process in a turbojet engine:
<section id="Equ5"><mml:math display="block" id="Equ5_Math"><mml:mrow><mml:msub><mml:mi>T</mml:mi><mml:mn>3</mml:mn></mml:msub><mml:mo>=</mml:mo><mml:mspace width="0.166667em"/><mml:mn>424.2</mml:mn><mml:mspace width="0.166667em"/><mml:mo>+</mml:mo><mml:mspace width="0.166667em"/><mml:mn>0.49</mml:mn><mml:mspace width="0.166667em"/><mml:msub><mml:mi>T</mml:mi><mml:mn>90</mml:mn></mml:msub><mml:mo>±</mml:mo><mml:mspace width="0.166667em"/><mml:mn>3.2</mml:mn></mml:mrow></mml:math><tex-math id="Equ5_TeX"><![CDATA[\documentclass[12pt]{minimal}
				\usepackage{amsmath}
				\usepackage{wasysym}
				\usepackage{amsfonts}
				\usepackage{amssymb}
				\usepackage{amsbsy}
				\usepackage{mathrsfs}
				\usepackage{upgreek}
				\setlength{\oddsidemargin}{-69pt}
				\begin{document}$$T_{3} = \, 424.2 \, + \, 0.49 \, T_{90} \pm \, 3.2$$\end{document}]]></tex-math><graphic specific-use="web" mime-subtype="GIF" xlink:href="40095_2022_489_Article_Equ5.gif"/></section>
<section id="Equ6"><mml:math display="block" id="Equ6_Math"><mml:mrow><mml:msub><mml:mi>E</mml:mi><mml:mtext>gt</mml:mtext></mml:msub><mml:mo>=</mml:mo><mml:mspace width="0.166667em"/><mml:mn>396.8</mml:mn><mml:mspace width="0.166667em"/><mml:mo>+</mml:mo><mml:mspace width="0.166667em"/><mml:mn>0.49</mml:mn><mml:mspace width="0.166667em"/><mml:msub><mml:mi>T</mml:mi><mml:mn>90</mml:mn></mml:msub><mml:mo>±</mml:mo><mml:mspace width="0.166667em"/><mml:mn>2.4</mml:mn></mml:mrow></mml:math><tex-math id="Equ6_TeX"><![CDATA[\documentclass[12pt]{minimal}
				\usepackage{amsmath}
				\usepackage{wasysym}
				\usepackage{amsfonts}
				\usepackage{amssymb}
				\usepackage{amsbsy}
				\usepackage{mathrsfs}
				\usepackage{upgreek}
				\setlength{\oddsidemargin}{-69pt}
				\begin{document}$$E_{{{\text{gt}}}} = \, 396.8 \, + \, 0.49 \, T_{90} \pm \, 2.4$$\end{document}]]></tex-math><graphic specific-use="web" mime-subtype="GIF" xlink:href="40095_2022_489_Article_Equ6.gif"/></section>
<section id="Equ7"><mml:math display="block" id="Equ7_Math"><mml:mrow><mml:msub><mml:mi>C</mml:mi><mml:mi>f</mml:mi></mml:msub><mml:mo>=</mml:mo><mml:mspace width="0.166667em"/><mml:mn>2.822</mml:mn><mml:mspace width="0.166667em"/><mml:mo>-</mml:mo><mml:mspace width="0.166667em"/><mml:mn>0.0155</mml:mn><mml:mspace width="0.166667em"/><mml:msub><mml:mi>W</mml:mi><mml:mi>o</mml:mi></mml:msub><mml:mo>±</mml:mo><mml:mspace width="0.166667em"/><mml:mn>0.025</mml:mn></mml:mrow></mml:math><tex-math id="Equ7_TeX"><![CDATA[\documentclass[12pt]{minimal}
				\usepackage{amsmath}
				\usepackage{wasysym}
				\usepackage{amsfonts}
				\usepackage{amssymb}
				\usepackage{amsbsy}
				\usepackage{mathrsfs}
				\usepackage{upgreek}
				\setlength{\oddsidemargin}{-69pt}
				\begin{document}$$C_{f} = \, 2.822 \, {-} \, 0.0155 \, W_{o} \pm \, 0.025$$\end{document}]]></tex-math><graphic specific-use="web" mime-subtype="GIF" xlink:href="40095_2022_489_Article_Equ7.gif"/></section>
<section id="Equ8"><mml:math display="block" id="Equ8_Math"><mml:mrow><mml:mrow><mml:mtext>EI CO</mml:mtext><mml:mspace width="0.333333em"/></mml:mrow><mml:mo>=</mml:mo><mml:mspace width="0.166667em"/><mml:mn>2025.4</mml:mn><mml:mspace width="0.166667em"/><mml:mo>-</mml:mo><mml:mspace width="0.166667em"/><mml:mn>2.01</mml:mn><mml:mspace width="0.166667em"/><mml:msub><mml:mi>G</mml:mi><mml:mn>15</mml:mn></mml:msub><mml:mo>-</mml:mo><mml:mspace width="0.166667em"/><mml:mn>1.69</mml:mn><mml:mspace width="0.166667em"/><mml:msub><mml:mi>T</mml:mi><mml:mn>90</mml:mn></mml:msub><mml:mo>+</mml:mo><mml:mspace width="0.166667em"/><mml:mn>2.47</mml:mn><mml:mspace width="0.166667em"/><mml:mi>A</mml:mi><mml:mspace width="0.166667em"/><mml:mo>±</mml:mo><mml:mspace width="0.166667em"/><mml:mn>6.6</mml:mn></mml:mrow></mml:math><tex-math id="Equ8_TeX"><![CDATA[\documentclass[12pt]{minimal}
				\usepackage{amsmath}
				\usepackage{wasysym}
				\usepackage{amsfonts}
				\usepackage{amssymb}
				\usepackage{amsbsy}
				\usepackage{mathrsfs}
				\usepackage{upgreek}
				\setlength{\oddsidemargin}{-69pt}
				\begin{document}$${\text{EI CO }} = \, 2025.4 \, {-} \, 2.01 \, G_{15} {-} \, 1.69 \, T_{90} + \, 2.47 \, A \, \pm \, 6.6$$\end{document}]]></tex-math><graphic specific-use="web" mime-subtype="GIF" xlink:href="40095_2022_489_Article_Equ8.gif"/></section>
<section id="Equ9"><mml:math display="block" id="Equ9_Math"><mml:mrow><mml:msub><mml:mrow><mml:mtext>EI CO</mml:mtext></mml:mrow><mml:mn>2</mml:mn></mml:msub><mml:mo>=</mml:mo><mml:mspace width="0.166667em"/><mml:mn>82.4</mml:mn><mml:mspace width="0.166667em"/><mml:msub><mml:mi>W</mml:mi><mml:mi>o</mml:mi></mml:msub><mml:mo>+</mml:mo><mml:mspace width="0.166667em"/><mml:mn>4.0</mml:mn><mml:mspace width="0.166667em"/><mml:msub><mml:mi>G</mml:mi><mml:mn>15</mml:mn></mml:msub><mml:mo>-</mml:mo><mml:mspace width="0.166667em"/><mml:mn>3740</mml:mn><mml:mspace width="0.166667em"/><mml:mo>±</mml:mo><mml:mspace width="0.166667em"/><mml:mn>28</mml:mn></mml:mrow></mml:math><tex-math id="Equ9_TeX"><![CDATA[\documentclass[12pt]{minimal}
				\usepackage{amsmath}
				\usepackage{wasysym}
				\usepackage{amsfonts}
				\usepackage{amssymb}
				\usepackage{amsbsy}
				\usepackage{mathrsfs}
				\usepackage{upgreek}
				\setlength{\oddsidemargin}{-69pt}
				\begin{document}$${\text{EI CO}}_{2} = \, 82.4 \, W_{o} + \, 4.0 \, G_{15} {-} \, 3740 \, \pm \, 28$$\end{document}]]></tex-math><graphic specific-use="web" mime-subtype="GIF" xlink:href="40095_2022_489_Article_Equ9.gif"/></section></p>
<p>This analysis did not allow to build a regression equation for NO
<sub>x</sub>
. This may be due to the fact that fuel is not part of the NO
<sub>x</sub>
 formation process and the nitrogen oxide formation rate might indirectly depend on fuel properties. These oxides are formed primarily as a result of atmospheric nitrogen oxidation at very high temperatures, encountered in the combustion chamber.</p>
<p>The regression equations of the dependence of combustion process characterizing parameters on fuel properties are shown in Fig. 
<a href="#Fig4"><sup>4</sup></a>
. 
<figure id="Fig4"><h3>Fig. 4</h3>
<figcaption><p>Dependence of parameters characterizing the combustion process on fuel properties from regression equations from regression equations</p></figcaption>
<img src="40095_2022_489_Fig4_HTML.png" /></figure></p>
<p>The regression Eqs. (
<a href="#Equ5"><sup>5</sup></a>
)–(
<a href="#Equ6"><sup>9</sup></a>
) allow for the verification of qualitative relationships identified by the literature review. In addition, significant independent variables can be quantified using regression coefficients. Collected Eqs. (
<a href="#Equ5"><sup>5</sup></a>
)–(
<a href="#Equ6"><sup>9</sup></a>
) were treated as a combustion process mathematical model, taking into account the fuel properties to a greater extent than the previously known models.</p>
<p>However, this model has limitations, which include:
<ul><li><p>Input data falling within a range of fuel property intervals or in its close vicinity;</p></li>
<li><p>Output data falling within a range of the intervals of obtained test bench results or in its close vicinity;</p></li>
<li><p>The ability to apply the developed model for predicting results obtained only for the GTM 140 engine (used to conduct bench tests);</p></li>
<li><p>The ability to apply the model for predicting results obtained for specific engine operating conditions (predefined rotational speed).</p></li></ul></p></section>
<section><h2>Conclusions</h2>
<p>The objective of the research was to develop a mathematical model of combustion process using regression analysis. In order to implement the above laboratory and bench tests of conventional jet fuel and its blends with alternative components were carried out.</p>
<p>The obtained results were used as a database to conduct a regression analysis of data resulting in regression models covering the impact of fuel physicochemical properties on selected parameters characterizing the combustion process. Compiled regression equations were treated as a combustion process mathematical model, taking into account the fuel composition characterized by its properties to a greater extent than the previously known models. Furthermore, the created linear regression model is enabled to quantitatively describe qualitative relationships, identified by the source literature review.</p>
<p>The developed combustion process mathematical model enables predicting engine operating parameters and the emissions characteristics, based on analysing laboratory test results. This model can be used as a tool verifying the environmental impact of new fuels, through predicting the exhaust gas emissions. The developed model relates only the engine used in bench tests, while the use of the methodology implemented in this research allows to extend the model to other engines. However, statistical data analysis and the resulting model are aimed at facilitating and extending the scope of inference about the impact of fuel properties on the combustion process.</p>
<p>The author further plans to conduct laboratory and test bench tests of other alternative fuels, with their results supplementing input data, in order to constantly update the combustion process model for a GTM 140 engine. A perspective to continue the research is conducting test rig studies involving other engines, including full-sized ones, in order to verify the obtained relationships within the developed mathematical model and to attempt to develop a general model that enables assessing the impact of fuel chemical composition on the parameters characterizing the combustion process.</p></section><hr/><h2>Acknowledgements</h2>
<p>This research was funded by the Ministry of Science and Higher Education (Poland) for the project financed within the framework of the statutory activity. The author would like to thank Prof. Andrzej Kulczycki DSc, PhD Eng. and Wojciech Dzięgielewski for their support as thesis advisers.</p><hr/><h2>Publisher's Note</h2>
<p>Springer Nature remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.</p>
<hr/><h2>References</h2>
<ol><li>Kulczycki (2017) <em>Theoretical approach to modeling the combustion process in turbine engines fuelled by alternative aviation fuels containing various components/biocomponents</em> 171(4) (pp. 245-249) <a href="https://doi.org/10.19206/CE-2017-441" target="_blank">10.19206/CE-2017-441</a></li><li>Tomasek et al. (2020) <em>Production of jet fuel from cracked fractions of waste polypropylene and polyethylene</em> <a href="https://doi.org/10.1016/j.fuproc.2019.106197" target="_blank">10.1016/j.fuproc.2019.106197</a></li><li>Gutiérrez-Antonio et al. (2017) <em>A review on the production processes of renewable jet fuel</em> (pp. 709-729) <a href="https://doi.org/10.1016/j.rser.2017.05.108" target="_blank">10.1016/j.rser.2017.05.108</a></li><li>Kulczycki (2018) <em></em> Wydawnictwo Naukowe Instytutu Technologii Eksploatacji - Państwowego Instytutu Badawczego</li><li>Fusaro et al. (2021) <em>Sustainable supersonic fuel flow method: an evolution of the Boeing fuel flow method for supersonic aircraft using sustainable aviation fuels</em> <a href="https://doi.org/10.3390/aerospace8110331" target="_blank">10.3390/aerospace8110331</a></li><li>Unknown () <em></em></li><li>Braun-Unkhoff et al. (2016) <em>About the interaction between composition and performance of alternative jet fuels</em> (pp. 83-94) <a href="https://doi.org/10.1007/s13272-015-0178-8" target="_blank">10.1007/s13272-015-0178-8</a></li><li>Mazlan et al. (2015) <em>Effects of biofuels properties on aircraft engine performance</em> (pp. 437-442) <a href="https://doi.org/10.1108/AEAT-09-2013-0166" target="_blank">10.1108/AEAT-09-2013-0166</a></li><li>Pires et al. (2018) <em>Chemical composition and fuel properties of alternative jet fuels</em> (pp. 2632-2657)</li><li>Unknown () <em></em></li><li>Mueller et al. (2014) <em>Fuels for engines and the impact of fuel composition on engine performance, chapter engines–fundamentals fuels</em> John Wiley & Sons Ltd</li><li>Murayama and Someya (1993) <em>Effects of fuel properties in combustion systems</em> Springer</li><li>Salvi et al. (2012) <em>Impact of physical and chemical properties of alternative fuels on combustion, gaseous emissions, and particulate matter during steady and transient engine operation</em> (pp. 4231-4241) <a href="https://doi.org/10.1021/ef300531r" target="_blank">10.1021/ef300531r</a></li><li>Vouros et al. (2017) <em>Spray characteristics of alternative aviation fuel blends</em> <a href="https://doi.org/10.3390/aerospace4020018" target="_blank">10.3390/aerospace4020018</a></li><li>Lefebvre and Ballal (2010) <em></em> CRC Press <a href="https://doi.org/10.1201/9781420086058" target="_blank">10.1201/9781420086058</a></li><li>Unknown () <em></em></li><li>McAllister et al. (2011) <em></em> Springer <a href="https://doi.org/10.1007/978-1-4419-7943-8" target="_blank">10.1007/978-1-4419-7943-8</a></li><li>Unknown () <em></em></li><li>Dzięgielewski et al. (2014) <em>Butanol/biobutanol as a component of an aviation and diesel fuel</em> (pp. 69-75)</li><li>Klippenstein (2017) <em>From theoretical reaction dynamics to chemical modeling of combustion</em> (pp. 77-111) <a href="https://doi.org/10.1016/j.proci.2016.07.100" target="_blank">10.1016/j.proci.2016.07.100</a></li><li>Dooley et al. (2010) <em>A jet fuel surrogate formulated by real fuel properties</em> (pp. 2333-2339) <a href="https://doi.org/10.1016/j.combustflame.2010.07.001" target="_blank">10.1016/j.combustflame.2010.07.001</a></li><li>Unknown () <em></em></li><li>Asadi (2019) <em>Combustion and emission characteristics of biomass derived biofuel, premixed in a diesel engine: a CFD study</em> (pp. 79-89) <a href="https://doi.org/10.1016/j.renene.2019.01.069" target="_blank">10.1016/j.renene.2019.01.069</a></li><li>Wang et al. (2010) <em>A physics-based approach to modeling real-fuel combustion chemistry–IV. HyChem modeling of combustion kinetics of a bio-derived jet fuel and its blends with a conventional Jet A</em> (pp. 477-489) <a href="https://doi.org/10.1016/j.combustflame.2018.07.012" target="_blank">10.1016/j.combustflame.2018.07.012</a></li><li>Filippone and Bojdo (2018) <em>Statistical model for gas turbine engines exhaust emissions</em> (pp. 451-463) <a href="https://doi.org/10.1016/j.trd.2018.01.019" target="_blank">10.1016/j.trd.2018.01.019</a></li><li>Gawron et al. (2020) <em>Exhaust toxicity evaluation in a gas turbine engine fueled by aviation fuel containing synthesized hydrocarbons</em> (pp. 60-66) <a href="https://doi.org/10.1108/AEAT-11-2018-0277" target="_blank">10.1108/AEAT-11-2018-0277</a></li><li>Gawron et al. (2020) <em>Combustion and emissions characteristics of the turbine engine fueled with HEFA blends from different feedstocks</em> <a href="https://doi.org/10.3390/en13051277" target="_blank">10.3390/en13051277</a></li><li>Janicka et al. (2018) <em>Emission of volatile organic compounds during combustion process in a miniature turbojet engine</em> (pp. 57-67)</li><li>Gawron and Białecki (2015) <em>The laboratory test rig with miniature jet engine to research aviation fuels combustion process</em> (pp. 79-90) <a href="https://doi.org/10.1515/jok-2015-0058" target="_blank">10.1515/jok-2015-0058</a></li><li>Gawron and Białecki (2015) <em>Measurement of exhaust gas emissions from miniature turbojet engine</em> (pp. 58-63) <a href="https://doi.org/10.19206/CE-2016-406" target="_blank">10.19206/CE-2016-406</a></li><li>Unknown () <em></em></li><li>Przysowa et al. (2021) <em>Performance and emissions of a microturbine and turbofan powered by alternative fuels</em> <a href="https://doi.org/10.3390/aerospace8020025" target="_blank">10.3390/aerospace8020025</a></li><li>Gawron and Białecki (2018) <em>Impact of a Jet A-1/HEFA blend on the performance and emission characteristics of a miniature turbojet engine</em> (pp. 1501-1508) <a href="https://doi.org/10.1007/s13762-017-1528-3" target="_blank">10.1007/s13762-017-1528-3</a></li></ol>