Boron Combustion Research Articles

The effect of surfactants on boron nanofuel combustion

In this study, the effect of surfactants on the combustion of boron nanofuel was experimentally observed. 1-butanol was chosen as the base fuel, and 70 nm boron nanoparticles were combined with two surfactants, Span 80 and oleic acid, to create the nanofuel. Experiments including single droplet combustion and heating value measurements were conducted, and optical and spectroscopical data were obtained to quantitatively evaluate the effects of the surfactants on boron combustion. The results showed that the addition of surfactants was essential for boron combustion by inducing puffing and atomization. The puffing intensity was stronger with Span 80 than with oleic acid, leading to more active boron combustion and a shorter droplet lifetime overall. An increase in boron concentration enhanced both puffing and boron combustion when surfactants were present. The addition of boron nanoparticles increased the heating value of the nanofuel compared to the base fuel. However, while the inclusion of oleic acid slightly rose the heating value of nanofuel, the addition of Span 80 decreased the heating value of nanofuel.

Impact of Aluminium and Titanium Additives on Ignition and Combustion in Boron-Loaded Gelled Jet A-1 Fuel

ABSTRACT A high-energy metal has been identified as a possible supplementary energy source for liquid fuel, which can be used to fuel volume-limited propulsive devices. However, the stability of metal particles in liquid fuel is a significant disadvantage, which can be overcome by suspending the particles in the gel fuel network. Boron’s (B) high energy density makes it a potential choice as fuel or energetic fuel additive for propulsion systems. However, the combustion of boron particles is challenging due to a native oxide layer on the boron particle surface that acts as an inhibitor. The influences of aluminum and titanium addition into the gel fuel containing boron particles have been investigated in the present study to understand whether Al or Ti positively enhances the ignition and combustion of boron particles. A droplet combustion study was conducted for gel fuel samples containing boron, boron-aluminum, and boron-titanium combinations. The key analyses include the feature of droplet diameter regression, the effect of Al/Ti additive on the ignition delay of boron particles through spectroscopic analysis, combustion of boron particles through chemiluminescence measurement of intermediate species of boron combustion (BO2) and flame imaging, and analysis of combustion residues. The obtained results and corresponding analyses suggest that the addition of Al particles improves the ignition of boron. In contrast, Ti particles significantly enhance the combustion of boron particles loaded in gel fuel.

Nanosizing and Al-Mg alloying effects of boron particles on combustion characteristics and energy release of B/JP-10 suspension fuel

Adding boron particles into JP-10 to prepare B/JP-10 suspension fuel can effectively improve the energy density and combustion heat of JP-10-based aviation fuel. However, the energy release of boron in B/JP-10 fuel has many challenges to overcome. In this study, micron-sized boron (Micro-B), nano-sized boron (Nano-B) and aluminum-magnesium-boron (AlMgB) alloy particles were added into JP-10 fuel to prepare suspension fuels. The effects of boron particle nanosizing and alloying on the combustion characteristics and energy release of B/JP-10 fuel are experimentally evaluated. These characteristics were achieved by investigating the combustion stage, flame structure, emission spectra, droplet evolution, micro-explosion, flame temperature, and morphology of residues. The results show that compared with Micro-B/JP-10, Nano-B/JP-10 droplets show better micro-explosion characteristics, shorter burning time, and better boron-oxygen reaction rate during the combustion process. The results of combustion flame temperature and emission spectrum show that Nano-B/JP-10 droplets burn better, which shows that nano-boron particles have better energy release characteristics. AlMgB/JP-10 droplets reduce the reaction temperature of boron and enhance the combustion of boron through the interphase interaction of Al and Mg into B. Compared with Micro-B/JP-10, it shows a higher combustion flame temperature and emission spectrum intensity, the boron-oxygen reaction rate is greatly improved, and react to form flaky crystals on the agglomerate surface, making it difficult for the shell to close, resulting in weak micro-explosion but effective energy release.

Evaluation of Boron Combustion for Ducted Rocket Applications Using Condensed Product Analysis

Boron, a metalloid, produces high energy upon combustion. It is recommended as an ingredient for fuel or propellant in rocket propulsion, despite the challenge of extracting its full thermal energy. So far no one has claimed the complete energy conversion of boron upon combustion. On the other hand, the current propulsion system of the Meteor missile uses boron-loaded propellant. The boron-loaded propellant provides an approximately three-fold increase in specific impulse compared to conventional propellants. The present study focuses on boron-HTPB-based solid fuels impregnated with early ignited particles as additives, aiming to assess the combustion performance of boron particles. These additives are magnesium (Mg), titanium (Ti), and activated charcoal (C), and their effects are evaluated based on the residual active boron content in the condensed combustion products (burned residues). An economical tool commonly called stagnation flow or opposed flow burner (OFB) is used to deflagrate the fuel sample by means of pressurized oxygen gas. The condensed combustion products are examined using a field emission scanning electron microscope (FESEM), X-ray diffraction (XRD), thermogravimetric analysis (TGA), and differential thermal analysis (DTA). Among the fuel combinations investigated here, magnesium has been found to be a good burning enhancer of boron, leaving the lowest active boron content (30%) in the burned-out residue. The current research aims to develop an efficient boron-containing solid fuel for hybrid propellant ducted rocket engine applications.

Combustion enhancement of boron-containing fuel-rich mixture by steam reforming in a supersonic flow

In this paper, a novel experimental investigation was conducted to enhance the combustion of boron-containing fuel-rich mixture by steam reforming in a supersonic flow. The ground direct-connected experiments were designed to simulate a flight condition at Mach number 5.9 and an altitude of 25 km. The operating characteristics and performance evaluation of the scramjet combustor were analyzed and discussed. The experimental results demonstrate that steam reforming can enhance the combustion of boron-containing fuel-rich mixtures in the supersonic flow. The performance of the combustor is firstly enhanced and then weakened with the increase of the steam-fuel ratio. The optimal steam-fuel ratio is approximately 0.189, which maximizes performance. At this steam-fuel ratio, combustion efficiency reaches 0.451, which is 9.9 % and 7.4 % higher than steam-fuel ratios of 0 and 0.395, respectively. The possible mechanism of steam reforming promoting boron combustion in the supersonic mainstream is explained. Steam accelerates the removal of the liquid oxide layer surrounding the boron particle, then combines with oxygen to produce hydrogen with good ignition-combustion characteristics and a new oxide layer. The cycle continues until the boron burns out. These conclusions can promote an understanding of enhancing the combustion of boron-containing fuel-rich mixture by steam reforming in the supersonic flow.

EFFECTS OF FLUORINATED AND NON-FLUORINATED ADDITIVES ON BURNING RATES OF BORON-TEFLON BLENDS FOR SOLID ROCKET PROPULSION

Boron is considered a promising metal fuel for energetic propellants due to its high energy density, but in practice, boron experiences slow combustion kinetics. Fluorinated additives can improve boron combustion. The objective of this study was to determine how different fluorinated additives would affect the burn rate of a boron-based fuel in a high-pressure inert environment. Boron powder was sintered with polytetrafluoroethylene (PTFE) powder to create test pellets with variable fluorine:boron mass ratios. Three different purities of boron powders were tested, along with three different fluoropolymer additives and 14 other additives, which varied in molecular morphology and fluorination. The base boron-PTFE test pellets with no additives have a maximum burning rate at fluorine:boron mass ratio of ~ 3.5, which remains the same even with additives at 20 wt%. A commercial fluoropolymer, Aquivion, showed significant burn rate enhancement at 20 wt% but not at 5 wt%. At this lower loading level, materials that tend to enhance thermal conductivity (graphene, nanotubes) show some burn rate enhancement, even without fluorination. However, very significant burn rate enhancement is shown by a fluorinated carbon nanotube, likely due to the reduced bond dissociation energy of fluorine when attached to a nanotube. The data suggest this method of fluorination can have an important effect on enhancing boron combustion, and even small additives with readily available fluorine could significantly improve boron combustion rates for solid propellant applications.

A short review of challenges and prospects of boron-laden solid fuels for ramjet applications

This short review article explores the advancement, challenges, and prospects of boron-laden solid fuel for ramjet. The energetic aspect of boron combustion is well known, but the complications associated with its efficient combustion persist and must be overcome to harness its potential completely. The strategies like coating, adding additives, and utilizing boron nanoparticles, which may improve its combustion performance, are widely studied. The latest development in advanced rocket propulsion systems, i.e., using a hybrid fuel-based gas generator for ducted rockets or air augmentation of hybrid rockets, seems a feasible idea; as it can provide two-stage combustion, which may significantly promote and improve the combustion performance of boron hence the specific impulse. Since it utilizes hybrid fuel, it retains its advantages of it as well as its drawbacks. To mitigate these drawbacks, various strategies/suggestions are briefly discussed here. A fundamental aspect of boron combustion must be fully understood and addressed for its applications in advanced propulsion systems.

Combustion features of boron-based composite solid propellants

This paper describes a technique for the sampling of condensed combustion products (CCPs) of metalized propellants. Experiments were carried out with model propellants containing 15.7% of a metallic fuels, ammonium perchlorate, and an inert binder under pressure levels of about 2, 4, and 8 MPa. We used microsized powders of aluminum, boron, aluminum diboride and aluminum dodecaboride as metallic fuels. For the initial fuels, we defined the granulometric composition and determined the content of the active (non-oxidized) metal by the cerimetric method. The quenching of the dispersed phase particles was performed near the burning surface by a co-current argon flow. The paper provides the burning rate of the propellants and CCPs characteristics – the particle size and morphological composition, and the combustion incompleteness of the metal fuels. We have identified the morphology features of the agglomerated particles of aluminum and boron. The paper also contains calculated data on the heat release efficiency of the tested propellants. The obtained experimental data provide a basis for the development and verification of theoretical models on the combustion of metalized propellants. For the studied propellant formulations, we have not identified the increase in the boron combustion completeness due to the adding of aluminum into the propellant composition.

Ignition study of facile spray drying prepared microspheres of nickel coated boron nanoparticles using a shock tube

Boron is being widely explored as a potential additive for high energy fuels because of its extraordinary gravimetric and volumetric energy content. However, its application is obstructed by the surface oxide layer which forms on the core boron particles, degrading its combustion and ignition performance. This oxide layer has a high vaporization temperature. To improve the combustion and ignition performance of boron, nickel nanoparticles were coated on the boron particle surface using a simple and unique spray drying technique. Numerous samples were prepared while varying the boron and nickel particles weight percent ratios. Surface morphological analyses showed that the nickel coated boron particles formed microspheres. These microspheres had a size distribution in the range of 2–15 µm and a mean diameter of 4.64 µm. The coating density of the crystalline nickel nanoparticles on the boron surface increased as the nickel percent used for the sample preparation was increased. X-ray diffraction (XRD) identifies the coating of nickel particles over the boron surface without any phase formation. Field emission scanning electron microscopy (FE-SEM), line scanning, elemental mapping and energy dispersive spectroscopy (EDS) studies provided an elemental analysis of the nickel coated boron particles that confirmed the surfaces of the boron particles were coated with nickel particles, and formed intimate contact between them. The oxidation performance of nickel, boron, and boron coated with nickel particles was studied by thermogravimetric analysis (TGA). The beginning of oxidation and the exothermic peaks of pure boron appeared earlier after the coating with nickel. Also, a decrease in weight gain was observed at 1000 °C in the boron coated with nickel. A shock tube experiment showed the nickel coated boron has a lower ignition delay time than the pure boron. The ignition delay times of the nickel coated boron samples, such as B:Ni= 40:1 and B:Ni= 10:1 samples decreased by 12% and 16%, respectively, compared to pure boron. Thus, spray drying prepared nickel coated boron particles demonstrated a substantial improvement in ignition performance versus uncoated boron.

Ignition and combustion of boron particles coated by modified materials with various action mechanisms

Coating boron particles with materials having multiple mechanisms of action is a promising way to promote the ignition and combustion properties of boron. The differences in thermal oxidation properties and ignition combustion characteristics of micron-sized boron composite particles (namely, AP@B, FR@B, and GAP@B) coated with 20 wt% ammonium perchlorate (AP), fluoropolymer (FR), or glycidyl azide polymer (GAP) were comparatively investigated using TG–DSC and CO2 laser ignition test systems. The results showed that the starting reaction temperature and activation energy of the composite particles were significantly reduced by the lower pyrolysis temperatures of the three modified materials. However, their oxidation phase lagged behind that of the original boron particles, most likely because the coating agglomerated 27% of the fine boron particles (<0.1 μm) into micron-sized particles. In addition, the slow heating approach did not allow the particles to reach the ignition temperature immediately and may indirectly aggravate the oxide layer thickness. Nevertheless, the coating modifier effectively promoted energy release (the heat release was increased by 93.76%, 28.65%, and 24.20% for FR@B, GAP@B, and AP@B, respectively). Generally, the ignition delay time (ti) decreases, whereas the combustion time (tc), self-sustaining combustion time (tf), maximum combustion temperature (Tmax) and burnout rate (α) increase after the coating of modified materials. First, AP decomposition produced O2 and other gases to provide an oxidant for boron combustion and disperse the particles into space, which promotes extremely rapid energy release. Thus, the Tmax and α of AP@B were significantly enhanced. Second, FR pyrolysis gas production can vaporize B2O3 and then promote the exposure of internal boron to react with oxygen. Thus, the tf and α of FR@B were significantly enhanced. However, the Tmax value was not the highest since the highest calorific value (up to 15,094 J•g−1) of FR@B is released at a slow rate. Finally, GAP can significantly shorten ti due to its lower activation energy, and this modification effect can be significantly improved by increasing the O2 content. Since boron is characterized by high oxygen consumption, increasing the oxygen partial pressure can significantly promote ignition and combustion. The Tmax values of four samples in a mixed O2–N2 environment under 1.0 MPa even exceeded the boiling point of B2O3, which is favorable for the reaction of internal boron with oxygen due to the gasification of the oxide layer at this time.

Investigation on spray combustion characteristics of Boron-Loaded slurry fuel in a Swirl-Stabilized combustor

For many decades, liquid hydrocarbon fuels are being used to propel air-breathing engines. However, the energy content of liquid hydrocarbon fuels has reached close to its limitation. Any further improvement in energy value is quite difficult through chemical methods. Slurry fuels, which are colloidal suspensions of solid energetic particles in liquid fuel, became a potential alternative fuel. Among several solid additives, boron is considered the best choice because of its higher heating values. However, our knowledge about boron-loaded slurry fuel is very limited. Therefore, here in this study, we experimentally investigated the combustion characteristics of boron/Jet A-1 slurry fuel spray in a swirl-stabilized combustor. A particle loading of 10% by weight is considered here for the experiment. The feed boron, as well as the burnt boron samples, were characterized using standard material characterization techniques in order to understand the surface morphology, oxidation behavior, and active boron content. The combustion characteristics of slurry fuel were analyzed through spectroscopy and BO2* chemiluminescence imaging. Positive thermal contribution from boron combustion was quantified via temperature measurements at three different radial locations of the combustor exit. The spectroscopy and chemiluminescence signatures indicate that combustion of boron particles occurs downstream of the dump plane. The exit temperature of boron-laden slurry fuel measured at all three different radial locations is higher compared to neat Jet A-1. An increment of 19% in exit temperature was observed in the case of boron slurry fuel relative to neat Jet A-1. The X-ray diffractograms (XRD) and thermogravimetric analysis (TGA) show the complete oxidation of boron particles.

Effect of Fluoroalkylsilane Surface Functionalization on Boron Combustion.

Boron has been regarded as a promising high-energy fuel due to its high volumetric and gravimetric heating values. However, it remains challenging for boron to attain its theoretical heat of combustion because of the existence of its native boron oxide layer and its high melting and boiling temperatures that delay ignition and inhibit complete combustion. Boron combustion is known to be enhanced by physically adding fluorine-containing chemicals, such as fluoropolymer or metal fluorides, to remove surface boron oxides. Herein, we chemically functionalize the surface of boron particles with three different fluoroalkylsilanes: FPTS-B (F3-B), FOTS-B (F13-B), and FDTS-B (F17-B). We evaluated the ignition and combustion properties of those three functionalized boron particles as well as pristine ones. The boron particles functionalized with the longest fluorocarbon chain (F17) exhibit the most powerful energetic performance, the highest heat of combustion, and the strongest BO2 emission among all samples. These results suggest that the surface functionalization with fluoroalkylsilanes is an efficient strategy to enhance boron ignition and combustion.

Ignition and Combustion Characteristic of B·Mg Alloy Powders.

Boron and its alloys have been explored a lot and it is expected that they can replace pure aluminum powder in the energetic formulation of active materials. MgB2 compounds were prepared and characterized by a combination of mechanical alloying and heat treatment. The ignition and combustion of boron–magnesium alloys were studied with the ignition wire method and laser ignition infrared temperature measurement. The results show that MgB2 has good ignition characteristics with maximum ignition temperatures obtained by the two various methods of 1292 K and 1293 K, respectively. Compared with boron, the ignition temperature of MgB2 is greatly reduced after alloying. The ignition reaction of MgB2 mainly occurs on the surface and the ignition process has two stages. In the initial stage of ignition, the large flame morphology and combustion state are close to the combustion with gaseous Mg, whereas the subsequent combustion process is close to the combustion process of B. Compared with boron, the ignition temperature of MgB2 is greatly reduced which suggests that MgB2 may be used in gunpowder, propellant, explosives, and pyrotechnics due to its improved ignition performance.

Effects of the Air Inlet Angle on the Combustion and Ablation Environment of a Hybrid Powder-Solid Ramjet

A hybrid powder-solid ramjet (HPSR) that combined the advantages of a solid rocket ramjet (SRJ) and a powder ramjet engine was investigated in this research. To improve the combustion efficiency and optimize the inner wall thermal protection of the afterburner, the effects of the air inlet angle on the combustion and wall ablation environment were studied. The standard k - ε model, the eddy-dissipation model (EDM), and the boron particle ignition and combustion model were adopted to simulate the two-phase flow in the afterburners with different air inlet angles (45°, 60°, 75°, and 90°). The results showed that the global flow field and the distribution of the vortexes in the afterburner that had a significant influence on the ablation environment of the inner wall and the combustion efficiency were determined by the impact effect and the squeezing effect of the ram air on the primary fuel gas, which was affected by the air inlet angle. As the air inlet angle increased, the total combustion efficiency of the four cases first increased and then decreased, reaching 80.38%, 81.64%, 84.34%, and 83.26% for angles of 45°, 60°, 75°, and 90°, respectively. At the same time, the inner wall ablation became more severe because both the erosion effect of the condensed phase particles and the gas-flow scouring effect were enhanced, and a large temperature gradient was generated on the inner wall. The study results can provide a reference for designing the air inlet angle of an HPSR.

Promotion mechanism analysis of metal hydride on the energy release characteristics of B/JP-10 suspension fuel

B/JP-10 suspension fuel is a novel high energy density fuel with great development potential. However, it faces the problem of incomplete energy release. In this study, metal hydride was first introduced as a solution. Thermogravimetric thermal analysis was conducted to analyze the effect of different metal hydrides and LiH presents the best performance with an optimal amount of 10 %, which can reduce the initial reaction temperature of boron from 789 °C to 638.4 °C. The effect of LiH on the combustion characteristics of B/JP-10 suspension fuel was studied with a CO2 laser ignition experimental system. It was found that with the addition of 10% LiH, the combustion of boron and JP-10 in the suspension fuel are both enhanced and the oxygen content in the residue is increased from 3.84% to 63.23%. Combined with thermodynamic calculations, the promotion mechanism of LiH on the energy release characteristics of B/JP-10 suspension fuel was obtained as: ① The oxidation of LiH occurs under lower temperature and releases heat to increase the local temperature; ② The decomposition products H2O and Li2O can react with B2O3 to destroy the oxide layer of boron particles; ③ The generation of radicals can initiate the chain reaction of JP-10 decomposition and oxidation.

Сравнительный анализ горения частиц бора, карбида бора, нитрида бора и углерода в воздухе

Combustion models of main components of condensed combustion products (CCP) of boron-containing solid propellants: boron, boron carbide, boron nitride, and carbon are analyzed. Using the known experimental data, the parameters of the combustion model of boron carbide and boron nitride particles are determined. Using the models of combustion of boron, B4C, BN and carbon particles, parametric calculations of the combustion of both individual abovementioned particles and their mixture, which simulates the composition of the CCP of boron-containing solid propellant, have been carried out. Calculations have shown that combustion of BN has the least effect on the completeness of CCP combustion. This is due to its low calorific value and low content in CCP. Ceteris paribus, carbon particles burn the fastest; however, their contribution to the completeness of CCP combustion is less than that of boron and boron carbide due to their lower calorific value.

Evolution of solid-liquid coupling combustion characteristics of boron suspension fuel in O2/Ar atmosphere

Boron suspension fuel is considered a good candidate to meet the energy requirements of hypersonic aircraft. As a solid-liquid mixed fuel, its combustion is a complex multi-stage process coupling of solid boron and liquid JP-10 combustion affected by various factors. In this study, A CO2 laser ignition test system was used to obtain the combustion characteristics of boron suspension fuel with solid loading of 10 wt.% in O2/Ar atmosphere. Focus is placed on the key factor of oxygen supply on the evolution of its solid-liquid coupling combustion characteristics. Theoretical analysis of the underlying mechanism of oxygen transportation and consumption caused by boron and JP-10 and their coupling characteristics was carried out for different stages. The results indicate that the combustion process could be divided into ignition, evaporation combustion, agglomerate combustion and extinguishment under full oxygen supply. In ignition stage, boron particles first ignite and promote the rapid ignition of JP-10. Oxygen supply can transfer boron combustion from heterogeneous reaction into homogeneous combustion. In evaporation combustion stage, a clear competition for oxygen between JP-10 and boron is observed. JP-10 is the main oxygen consumer whose flame forms an oxygen-lean zone around the droplet and suppresses boron combustion within the area. Micro-explosion could help carry boron particles into the outer oxygen-rich zone and achieve single-particle combustion. Increasing oxygen content to 60% can effectively compress the oxygen-lean zone area and realize simultaneous combustion of boron and JP-10. Agglomerate combustion stages could only occur when oxygen content is higher than 80%, which is the main energy releasing stage of boron. In extinguishment stage, black smoke is observed due to incomplete combustion of JP-10 when oxygen content is less than 60% while white smoke is observed due to boron oxide cooling deposition. This study provides a reference for the full energy exploitation of boron suspension fuel.

High energy release boron-based material with oxygen vacancies promoting combustion

Boron has a high calorific value and good application prospects in energetic materials. However, further applications of boron are hindered by its incomplete combustion. MoO3 has good catalytic properties, and its layered structure can provide good ion flow channels and embedding positions. In this study, mechanical mixtures of B/MoO3 and B/Mo were prepared. The promotion of B combustion by MoO3 and Mo was confirmed via combustion heat and burning rate tests. The mechanism by which Mo/MoO3 promote B combustion was studied by thermal analysis, high-temperature in situ X-ray diffraction, X-ray photoelectron spectroscopy, and Raman spectroscopy. The maximum heat release and burning rate of B/MoO3 and B/Mo were 2.49 and 2.62 and 2.67 and 2.55 times, respectively, those of raw boron. A pre-ignition reaction occurred when boron first came into contact with the surface of MoO3. The oxygen vacancies on the MoO3 surface served as reaction sites for boron. MoO3 promoted the combustion of B by opening up oxygen channels and improving the oxygen transport capability. Mo also effectively promoted boron combustion. B/Mo and B/MoO3 have promising future applications as high energy release materials.

Effects of aluminum addition on flash ignition and combustion of boron nanoparticles

Boron has been of considerable interest as fuel for propellants and explosives due to its high gravimetric and volumetric calorific values. In this study, the effects of different mixed modes, blending ratios, and packing densities on ignition and combustion characteristics of boron-aluminum mixture were explored using flash ignition facility and thermobalance. The results showed that the boron nanoparticles can be ignited upon exposure to the flash with a certain amount of aluminum nanoparticles addition and the flame luminous intensity increased with content of the added aluminum. The boron-aluminum mixture in loose contact performed better combustion characteristics than those in tight contact because of more access to the oxygen and less heat dissipation into the bulk sample. The main combustion products were detected and analyzed by the X-ray diffraction (XRD) and scanning electron microscopy (SEM). The temperatures of the ignited nanoparticles were measured and mostly distributed between 1273 K and 1473 K. The burning time decreased significantly with the increase of aluminum addition at the high packing density condition. The boron combustion efficiency increased with the addition of aluminum content in loose contact. The thermogravimetric experimental results showed that the aluminum addition could decrease the primary ignition temperature of boron. Moreover, the photothermal effect and plasmon resonance effect of aluminum were the potential flash ignition mechanism of the boron-aluminum mixture.

IGNITION AND COMBUSTION OF SINGLE SOLID PARTICLES AS NON-ISOTHERMAL METHODS OF CHEMICAL KINETICS

The ignition and combustion of single particles of crystalline boron continue to produce major scientific interest due to the particularities of the process and diversity of potential applications of boron compounds. The full valorization of boron energetic potential is a very current scientific challenge. The objective of the paper is to systematize the methodology for evaluating the kinetic parameters of boron ignition and combustion reactions in various oxidizing gaseous environments. Experimental dependencies between the ignition temperature and the particle size, as well as the combustion time as a function of oxidizing temperature are used for the calculation of the kinetic constants. As a main result, the kinetic parameters of the ignition and combustion reactions of boron in oxygen and water vapor are calculated.