The connection between rotating detonation waves and tangential high-frequency combustion instability (T-HFCI) suggests that radial HFCI (R-HFCI) may be induced by radial detonation. This implies the potential for utilizing radial detonation to achieve propulsion. This paper first explores a novel continuous detonation combustor based on radial detonation. First, the feasibility of stable operation in a radial detonation combustor is verified using a configuration with large injection intervals (LIIs). Second, a baffled configuration is employed to significantly expand the radial detonation zone, increasing the injection area ratio and propellant flow rate. The results indicate that stable operation of a two-subregion radial detonation is achieved with the LII configuration. As the inlet total pressure increases, the detonation mode transforms from rotating detonation to radial detonation, suggesting that higher inlet pressures may favor the formation of radial detonation. Owing to high-frequency reflections of radial detonation waves, the height of the fresh mixture layer in the radial detonation mode is kept at the millimeter level. In the baffled combustor, a self-stabilization process of radial detonation is observed, confirming it as a stable state in the evolution of the detonation flow field. A total pressure gain of 13.4% is obtained at the outlet in the baffled combustor. Furthermore, stable full-domain radial detonation under random single hot-spot ignition has been achieved. This work offers a new strategy for organizing combustion in detonation propulsion.

Reliable detonation onset is essential for rotating detonation engine (RDE) operation, yet initiation mechanisms under continuous non-premixed injection remain unexplored. Through synchronized high-speed imaging (single-pass schlieren, double-pass shadowgraph, and CH* chemiluminescence) in an optically accessible methane/oxygen obround RDE, the influence of reactant conditions, centerbody confinement, and channel curvature on flame acceleration, detonation re-initiation, and stability was investigated. After the predetonator wave diffracts into the combustor and decouples, RDE-specific re-initiation pathways rely on flame-driven compression waves, Mach stem development in stratified reactants, and hotspot autoignition within heated turbulent shear layers behind the Mach stem. Centerbody confinement yields tulip-shaped turbulent flames transitioning rapidly to overdriven detonation, accelerated by higher equivalence ratios, whereas hollow combustors exhibit spatially stochastic re-initiation via asymmetric flame-wall interactions; greater channel curvature delays re-initiation via enhancing rarefaction, yet raises incident angles and strengthens the Mach stem. Nevertheless, re-initiation cannot guarantee self-sustained detonation without sufficient energy release for re-establishing detonation after subsequent wave collisions. The hollow combustor extends lean detonability limits and promotes earlier detonation establishment compared to centerbody cases. The curvature transition induces velocity deficits and wave strength disparities, intensifying instabilities in multiwave collision regimes. These insights are vital for extending operational envelopes and enhancing deflagration-to-detonation-transition-based ignition reliability in non-premixed RDEs.

Rotating detonation afterburners have gained increasing attention for their potential to enhance propulsion performance. Traditional outer injection scheme tends to be employed to maintain the rotating detonation. In the study, the feasibility of the dual injection scheme for organizing stable detonation is numerically verified based on the hollow chamber. The differences between the two injection schemes are analyzed. Results show that additional inner injection creates an air column, resulting in a flow field similar to that in an annular chamber, excluding the mixed layer around the injection interface. Thereby, higher pressure gain is achieved. Based on this dual injection scheme, influences of nozzle structure and injection direction are discussed. It is found that detonation waves, different streams, and the nozzle affect the outer mass flux differently. Compared to axial injection of bypass flow, radial injection can maintain both stable detonation and deflagration. However, it tends to have a lower detonation fraction. Net thrust is used to analyze the propulsion performance. The dual injection scheme reduces fuel consumption with little change in net thrust. Moreover, parallel injection within the dual injection scheme is conducive to realizing the detonation dominant burning, resulting in more significant performance improvements. This study provides valuable insights and support for the optimal design of rotating detonation afterburners.

This study investigates the initiation, transition, and stabilization phases of an annular hydrogen/air rotating detonation engine (RDE), focusing on mode evolution and experimental validation of an active strategy to influence detonation modes via sustained pre-detonator ignition. Following ignition, collision points shift chaotically in a two-wave collision mode, stabilizing as shifting frequency decreases. The pre-detonator ignition continues for 0.2 s, where the reactants continuously injected into the pre-detonator are ignited via spark plug discharge or detonation waves penetrating the pre-detonator, generating periodic hot jets (every 5-15 ms) that eject strong counter-clockwise tangential momentum and products into the combustor. These jets transiently induce a single counter-clockwise wave, re-establishing the original two-wave collisions or transitioning to four-wave collision regimes, demonstrating the capability of sustained pre-detonator ignition to actively disrupt existing modes and markedly promote mode transitions. These findings provide new insights into initiation dynamics and mode modulation mechanisms in hydrogen-fueled RDEs.

Rotating detonation combustors (RDCs) offer significant potential for pressure-gain combustion, but their practical application is strongly constrained by the severe thermal loading in the detonation-head region. Conventional axial film-cooling strategies mainly protect the downstream wall and often provide insufficient shielding near the wave head, where the thermal environment is highly unsteady and closely coupled with detonation-wave dynamics. This work proposes a tangential film-cooling configuration for head-region thermal management in an RDC and investigates its flow evolution, cooling behavior, and interaction with detonation-wave structures using three-dimensional numerical simulations. Particular attention is given to the role of injection angle in controlling coolant development, wall protection, and wave-system response. The results indicate that tangential injection produces a coolant evolution mode distinct from that of conventional axial cooling. Under periodic detonation-wave forcing, the coolant forms a near-wall film in the head region and develops downstream in an oscillatory manner, enabling coupled protection of both the wave-head vicinity and part of the downstream wall. The film-cooling performance in the RDC is evaluated from both local cooling capability and global cooling coverage, showing that the minimum wall temperature is weakly affected by the tangential injection angle, while the Effectiveness Cooling Coefficient (ECC) decreases and becomes more stable as the injection condition approaches the perpendicular injection. The cooling coverage is tested on three temperature thresholds, with concentrated injection near the perpendicular injection favoring local low-temperature protection and fully tangential injection providing larger high-temperature coverage. Tangential cooling also modifies local wave dynamics, especially through the dissipation of reverse shocks and the reorganization of secondary wave structures, but introduces only a small propulsion penalty. These findings show that tangential film cooling provides a viable thermal-management route for the detonation-head region and offers useful guidance for the design of active cooling strategies in practical RDC systems.

Rotating detonation engines (RDEs) are regarded as promising pressure gain combustion devices for high-efficiency propulsion. Targeting the engineering application of kerosene/air RDEs, air-breathing experiments under low-Mach-number conditions were conducted on an annular RDE equipped with an aerospike nozzle using preheated air at an average temperature of 475 K to investigate its propulsion performance and total pressure gain. Stable rotating detonation was achieved over a broad operating range, with a minimum detonation boundary of ϕ=0.67 and ṁtot=533.63g/s. Analysis of specific impulse and specific thrust showed that better overall performance was obtained under moderately lean conditions (ϕ≈0.8–0.9), whereas the specific thrust did not increase monotonically with air mass flow rate. The Equivalent Available Pressure (EAP) was employed to evaluate total pressure gain, and two complementary gain metrics were introduced to distinguish intrinsic detonation-induced total pressure rise from system-level total pressure loss. The intrinsic total pressure gain remained positive throughout the detonation operating range and reached approximately 22%, whereas the system-level total pressure gain remained negative because injection-induced loss consistently exceeded the recovered intrinsic pressure rise. The results indicate that kerosene/air rotating detonation provides a clear intrinsic pressure gain effect under low-preheat air-breathing conditions; however, reducing the injection-related total pressure loss is essential for translating this benefit into engine-level performance improvement.Novelty and significance statement: Air-breathing liquid-fueled rotating detonation remains much less established than gaseous-fueled operation, especially in configurations relevant to practical propulsion. This work advances that area by experimentally investigating a kerosene/air RDE with an aerospike nozzle under low-preheat air-breathing conditions and by combining propulsion performance assessment with total pressure gain evaluation in a unified framework. Its significance lies not only in clarifying the propulsion performance behavior of a practically relevant liquid-fueled air-breathing configuration, but also in separating detonation-induced pressure-rise potential from injection-related system loss, thereby explaining why thermodynamic pressure gain does not automatically translate into engine-level benefit. The study therefore provides an experimentally grounded basis for both performance-oriented evaluation and system-level design of liquid-fueled, air-breathing RDEs.

The afterburner is indispensable for the short-term power enhancement of military engines. In order to achieve stable and efficient combustion in the afterburner and reduce the weight of the combustion chamber, it is very important to explore an efficient combustion organization scheme. Rotating detonation engine is an engine that uses continuous rotating propagation of detonation waves in the combustion chamber to generate a stable thrust and detonation waves can propagate continuously and stably with only one-time ignition. In this study, the inline injection mode of the injector in the afterburner is taken as the research background, and the scheme of using rotating detonation jet to enhance the mixing and combustion process of fuel cross-flow and high subsonic parallel flow is proposed for the first time. The results show that the rotating detonation jet combustion enhancement scheme is a promising method to achieve efficient combustion of high-speed non-premixed reactants. As far as the current simulated working conditions are concerned, the maximum combustion efficiency of this method can reach 89.93 %. In addition, there is a suitable rotating detonation combustor size and connected domain distance to achieve the best combustion enhancement effect. Improper geometric parameters will affect the baroclinic torque structure, the strength and continuity of the vortex distribution, and the continuity and area of the flame stability zone, thus affecting the combustion enhancement effect. Three main mechanisms for the enhancement of non-premixed combustion by periodic rotating detonation jet are summarized. Combined with the analysis of cases with different connected domain distance, it is found that the formation of specific baroclinic torque structure and the interaction between shock wave and flame are the dominant mechanisms.

Concerning the significant deficit of detonation wave speed relative to the Chapman-Jouguet (C-J) speed observed in kerosene-fueled rotating detonation engine (RDE) experiments, this study investigates the impact of incomplete kerosene droplet evaporation and its coupling with the equivalence ratio on the detonation performance in RDEs. A quasi-one-dimensional Eulerian-Eulerian multiphase model is developed, integrating gas dynamics with droplet behavior-including rapid droplet breakup, momentum equilibration, and coupled heat and mass transfer processes. Simulation results reveal that incomplete evaporation leads to significant thermal losses and consequent detonation speed deficits, as a sizable fraction of the fuel remains unvaporized prior to the sonic point. Moreover, the detonation performance is found to be highly sensitive to the overall equivalence ratio; an optimum detonation speed is achieved only at ratios exceeding unity, with the peak shifting to higher values as the initial droplet size increases. This "Peak Detonation Speed Shift with Equivalence Ratio" effect explains the pathological detonation phenomena observed in experimental RDEs, where inadequate atomization and localized inhomogeneities result in substantial deviations from the ideal C-J velocity. The findings underscore the importance of enhanced fuel atomization and uniform mixing for improving the thermodynamic efficiency and propulsion performance of liquid-fueled RDEs.

The rotating detonation engine (RDE) has attracted considerable interest due to the total pressure gain, and there is a discernible inclination towards engineering applications. In this paper, a new large-interval-injection rotating detonation combustor (LII-RDC) is proposed to cope with the potential demand for a connected coolant supply strategy, as well as to explore the modulation law for suppressing tangential combustion instability (TCI). Threedimensional numerical simulation is conducted on the ignition, re-initiation, and quenching processes in LIIRDCs. The LII-RDCs with 2 or 3 injection intervals are selected under different injection area ratios and total pressures. The results show that the re-initiation/non-initiation of shock waves (SWs) and the counter-rotating shock waves (CRSWs) determine the evolution trend. For the 2-injection-intervals pattern, the RDWs propagate stably with the interval inner/outer arc lengths of 11/14.1 mm, verifying the feasibility of the LII-RDC and the toughness of the RDWs. For the 3-injection-interval patterns, quenching happens in all the cases after a period of dynamic adjustment. It is an interesting finding and provides important insights into suppressing TCI from the perspective of arranging injection intervals. Furtherly, the re-initiation simultaneously necessitates the chemical reaction edge of premixed fresh gas (PFG) and the persistent relatively high pressure (8 atm or even lower) with a certain duration. In addition, the presence of the LII tends to narrow the upper and lower bounds of the RDW number due to the quenching of the RDWs and counter-ignition (CI) by CRSWs. Under the same injecting total pressure, the full-area inlet pattern fails to ignite, unlike the success of the 2-injection-intervals pattern, indicating that injection intervals favor ignition.

This study presents the first systematic investigation of instability mechanisms in four-wave collision regimes of rotating detonation engines (RDEs), within a methane/oxygen-enriched air (30%O2, 50%O2) annular combustor. Compared to two-wave collisions, four-wave collisions exhibit inherently unstable wave symmetry and heightened sensitivity to inflow variations: elevated oxygen enrichment, equivalence ratio, and mass flow rate induce detonation strength imbalance, driving progressive transitions from symmetric four-wave collisions with stationary collision points to inducing collision-point migration (CPM), asynchronous behaviors (Async 4CR), and eventual single-wave dominance. The Async 4CR regime is uniquely characterized by subharmonic components at half the dominant frequency, originating from temporal offsets between successive wave collisions. Its unstable transitions to single-wave modes involve amplified upstream pressure feedback and elevated wall temperature growth rates. To quantify these instabilities, an analytical framework combining pressure peak-interval calculation and auto-correlation was developed to correlate periodic peak bifurcation and CPM dynamics. A linear model linking pressure peak-interval to angular CPM deviations was established based on near-constant CPM velocities, enabling single-sensor tracking of time-resolved CPM trajectories. The nonlinear and stochastic nature of CPM was revealed, featuring arbitrary migration directions, diverse maximal deviation angles (20-45 degrees), and irregular periods (5-39 ms). The model remains valid under temporally oscillating fuel inflow, capturing transiently amplified CPM angles and reduced detonation stability during fuel flow rise. These findings reveal the complex instabilities and mode evolution patterns of four-wave collision regimes in RDEs, critical for advancing mode control and evaluating RDE performance. Novelty and significance (1) This study resolved typical CPM patterns during mode evolutions associated with four-wave collision instabilities. Unstable asynchronous collision regimes unique to four-wave collision systems were identified for the first time. (2) The developed linear model enables quantitative reconstruction of time-resolved CPM trajectories through peak bifurcation analysis of easily-accessible single-sensor pressure, offering direct extensibility to two-wave collisions and other high-frequency signals. (3) The stochastic nature of CPM driven by nonlinear detonation dynamics was underscored, while providing the experimental evidence on the destabilizing effects of time-varying oscillating inflow.

This study investigates the wall heat flux characteristics of rotating detonation combustors, which exhibit unique thermal behaviors distinct from traditional deflagration-based combustion chambers. A series of experimental tests on a compact rotating detonation engine were designed and implemented, utilizing methane/GOX as propellants. High-frequency heat flux measurements were conducted to analyze instantaneous and average heat flux distributions, as well as heat flux distortion characteristics. The effects of mass flow rate and equivalence ratio on heat flux were systematically examined, and three dimensionless parameters were introduced to quantify thermal load fluctuations. The key findings show that the combustor walls experience high-frequency periodic thermal loads, with frequencies consistent with those of the rotating detonation waves. At a constant mass flow rate, both the average heat fluxes in the detonation region and the global heat flux initially rise and then decline with increasing equivalence ratios, reaching maximum values within the range of 1.2-1.3. The heat flux fluctuation intensity is highest in the detonation region, typically ranging between 1.5 and 2.5. The circumferential distortion intensity remains stable at 4%-6% under stable detonation modes. The axial distortion intensity remains within 40%-50% for equivalence ratios below 1 but increases rapidly for equivalence ratios above 1, likely due to the competitive interaction between detonation and deflagration. These results provide critical insights for the thermal protection design of RDCs and advance the engineering application of RDEs.

Incoming flow disturbances severely destabilize rotating detonation waves (RDWs), presenting key challenges for practical rotating detonation engine (RDE) applications. A series of ethylene-air experiments was conducted in a hollow combustor, with detonation initiated via aft-mounted spark ignition. The initiation process and propagation characteristics of detonation waves are analyzed under modulated equivalence ratios. The effects of mass flow rate on detonation wave propagation stability were elucidated. The results indicate that collisions between RDWs and counter-rotating shock waves induced alternating strong and weak detonation wave intensity during initiation. The instability of detonation wave propagation exhibited intensified pressure-frequency oscillations under dynamic equivalence ratio variations. A mass flow rate governing mechanism for detonation wave propagation stability is proposed under non-premixed injection. Elevated mass flow rates increase reactant momentum flux under choked flow sonic injection, enhancing penetration depth and extending axial mixing time. This promotes superior fresh gas mixing uniformity ahead of the detonation front, directly governing RDW intensity and propagation stability. This mechanism remains valid for both steady and variable inflow conditions. The results provide pivotal insights for optimizing RDE operation with incoming flow disturbances, facilitating injection design for rotating detonation combustors.

The rotating detonation engine (RDE) is an emerging propulsion concept with significant potential for advanced power generation and aerospace applications. This study presents three-dimensional (3D) numerical simulations of hydrogen–air RDE flow fields to elucidate the underlying mechanisms, explore control strategies, and identify characteristic parameters associated with rotating detonation waves (RDWs) across different operational modes-defined by the number of detonation waves propagating within the combustor. Various operational behaviors are investigated through a multi-ignition approach and by modulating two key parameters: the injection stagnation pressure p_t,in and the injection area ratio A_th/A_ch . Our findings show that different control operations result in self-regulating processes with varying fluctuation amplitudes. Specifically, increasing p_t,in causes significant fluctuations, while increasing A_th/A_ch leads to smoother self-regulation. Moreover, A_th/A_ch is identified as a key factor for the RDE to achieve a positive pressure gain. The concept of non-confinement rate δ is introduced to adjust the critical height value h^* of RDWs, aligning with experimental results. A new equivalent available pressure (EAP) evaluation method based on the total enthalpy, i.e. EAPh, is also preliminarily introduced.

A rotating detonation engine (RDE) is a highly promising detonation-based propulsion system and has been widely researched in recent decades. In this study, BYCFoam, the latest gaseous version of the BYRFoam family, is developed specifically for RDE simulations. It is based on the standard compressible flow solver rhoCentralFoam in OpenFOAM and incorporates several enhancements: improved reconstruction variables and flux schemes; detailed chemistry and transport properties; the utilization of an adaptive mesh refinement (AMR) and dynamic load balancing (DLB). A series of comprehensive numerical tests are conducted, including the shock-tube problem, shock-wave diffraction, homogeneous ignition delay, premixed flame, planar detonation, detonation cellular structure and rotating detonation combustor (RDC). The results demonstrate that BYCFoam can accurately and efficiently simulate the deflagration and detonation processes. This solver enhances the capability of the BYRFoam family for the in-depth exploration of RDE in future research.

With the rotating detonation engine's (RDE) development to engineering applications, the selection and optimization of nozzle is garnering great concerns, with the aim to maximize the performance benefits of this pressure gain propulsion system. The present study represents the first effort to explore the distinct impacts of two commonly used nozzles in RDE, namely, the plug nozzle and the Laval nozzle, on the internal flow and performance within the combustion chamber. Three-dimensional numerical simulations are conducted on non-premixed annular RDEs with plug nozzles and Laval nozzles. It is found that the Laval nozzle induces a forward-leaning wavefront structure in the combustion chamber. Furthermore, the overall pressure gain of the RDE is divided into the injection pressure loss, the average pressure gain at the chamber bottom, and the flow losses downstream, by combining the wavefront coordinate averaged flow field, which is proposed and applied in this study, and laboratory coordinate averaged flow field. The results show that, for the performance of the combustion chamber, while Laval nozzles enhance pressure gains at the chamber bottom and reduce exit flow non-uniformity, they also increase downstream losses. By comparing the RDE performance with the ideal performance of deflagration-based combustors, it is found that the premixed control group exceeded the deflagration ideal performance by 30%. Despite lower combustion efficiency, non-premixed configurations nearly match the ideal deflagration performance, underscoring the inherent advantages of RDEs.

Rotating detonation engines (RDEs) are the most promising pressure-gain combustion devices, but their long-duration operations are hindered by the harsh thermal environment inside the chamber. This study analyzes the instantaneous and average heat loads on chamber walls of RDEs based on the newly developed unsteady conjugate heat transfer (CHT) OpenFOAM solver named multiRegionBYRFoam. To enhance accuracy in predicting heat transfer characteristics compared to decoupled simulations focusing solely on fluid or solid behavior, three-dimensional CHT simulations are conducted for a premixed H2/air annular RDE coupling the detonation simulation with heat conduction in both inner and outer chamber walls. The transient time evolutions of wall heat flux in RDEs are numerically captured for the first time and agree well with experiments. The calculated peak wall heat flux is 1.98 MW/m2 at the inner wall and 2.63 MW/m2 at the outer wall when a single detonation wave propagates with a mass flow rate of 0.227 kg/s. By investigating the influence of inlet flow conditions and detonation modes, valuable guidelines on designing efficient thermal management systems for RDEs are obtained: larger mass flow rates and multi-wave modes result in higher average wall heat flux; the heat flux at the outer wall exceeds that at the inner wall while both walls require effective cooling for gas turbine engines with a rotating detonation combustor. Furthermore, a novel heat transfer model for RDEs is proposed based on a thermal operation map depicting total heat transfer rates to describe the nonlinear impact of mass flow rate and number of detonation waves, which can be employed to predict total wall heat loads under specific operation conditions of RDE.

An investigation of the total pressure gain (TPG) in rotating detonation combustors (RDCs) with dilution holes is conducted by the experimental method in this study. The effects of pressure ratios (PR = 4.2–7.2) and equivalence ratios (ER = 0.5–1.5) on the total pressure gain are analyzed in four models, i.e., models A–D, of different throat areas A3.1 and dilution hole area A3.5. When the PR is small, the lowest ER causes the highest TPG, and when the PR is high, the highest ER leads to the highest TPG in Model A. While in models B–D, as ER increases, the TPG increases gradually in all the cases. Comparing the level of TPG between the four models, it is found that the increment of A3.1 and A3.5 results in the enhancement of the TPG. The present study's TPG shows superiority when compared with that of traditional RDC, which indicates that the RDC with dilution holes is more promising for achieving positive TPG in specific configurations. An empirical model considering the throat area A3.1, dilution hole area A3.5, outlet area A8, and heat (released by the fuel combustion) release rate Qv is proposed to better predict the performance of different RDC configurations. Positive total pressure gain is inferred to be promisingly attained at a high A3.1/A8, low A8/A3.5, and a high Qv. Total pressure measured by total pressure rake is verified by comparing with the data calculated by Mach-corrected-static-pressure and mass flow function methods, with relative errors in ±4% and ±15%, respectively.

Film cooling is a promising thermal management solution for rotating detonation combustors (RDCs) maturing toward long-duration engineering implementation. Aimed at elucidating the interaction between air coolant and rotating detonation waves (RDWs) and assessing the cooling performance, three-dimensional numerical simulations are conducted on an RDC utilizing four different film cooling injection inclination angles and compared to a case without coolant injection. Increasing injection angles from 30° to 90° results in a broader detachment region and deeper penetration, negatively influencing the cooling performance. A time-averaged method is adopted to evaluate the overall cooling performance, including axial temperature profiles, film protection coverage, RDC film effectiveness, and pattern factor. The results show that the cylindrical cooling hole with a 30° injection angle outperforms others due to enhanced wall attachment of the coolant and reduced interaction with the mainstream hot gas. Consequently, a low injection angle within the manufacturing limits is recommended for practical applications. Furthermore, this study uncovers several phenomena unique to RDCs when introducing film cooling, absent in conventional gas turbines, such as temperature discrepancy between the inner and outer walls, elevated upstream temperature caused by coolant injection, and non-uniform cooling effectiveness between the two sides of the cooling holes. Finally, the interplay between film cooling and RDW is illustrated through temperature and pressure gradient contours.

Continuous rotating detonation engines have been extensively studied due to their high thermal efficiency. The utilization of solid particles as fuel can effectively reduce costs and enhance detonation performance. We have constructed a compressible gas–solid multimedium flow combustion numerical method, employing the double flux model coupled with fifth-order weighted essentially non-oscillatory and third-order total variation diminishing Runge–Kutta schemes to solve the unsteady multi-component chemical reaction Eulerian–Eulerian equations. Finite-rate methods and surface reaction models are used to simulate the combustion of gaseous mixtures and carbon particles. The effects of the inlet total pressure spatial fluctuations and particle diameter on the flow field characteristics of the continuous rotating detonation engine are investigated. The results indicate that changing the fluctuation period significantly affects the number, propagation direction, and intensity of gas–solid two-phase continuous rotating detonation waves (CRDW). The variation of fluctuation amplitude noticeably alters the combustion characteristics of the two-phase continuous rotating detonation wave, and excessively high amplitudes cannot form continuous rotating detonation waves. Introducing solid particles into fuel significantly mitigates the impact of inlet total pressure spatial fluctuation and promotes propagation stability on the detonation waves. Moreover, when solid particle diameters reach or exceed the micrometer scale, they contribute more favorably to generating a stable detonation flow field. However, excessive particle sizes result in a low surface reaction rate and inadequate contribution of heat released from particle combustion to the propagation of detonation waves.