Bifurcation in Rotating Detonation Engine Operation with Continuously Variable Fuel Injection Location

Plaehn, Ethan W.; Walters, Ian V.; Gejji, Rohan; Slabaugh, Carson D.

doi:10.2514/1.b38801

Cited by 8 publications

(1 citation statement)

References 51 publications

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“…Goto et al [18] performed experimental research using two different fuel injectors of varying sizes and observed differences in detonation velocity based on the injector diameter. Plaehn et al [19] carried out experimental research on the influence of the injector location on the RDE length direction, and the results indicated that when it is located more than 5 mm away from the RDE head, a transition to deflagration occurred. Matsuoka et al [20] conducted an experimental study with a geometric blockage ratio and suggested that the RDE operation is limited in the region of the lower geometric blockage ratio.…”

Section: Introductionmentioning

confidence: 99%

Effects of Injector Configuration on the Detonation Characteristics and Propulsion Performance of Rotating Detonation Engine (RDE)

Koo,

Lee,

Kim

et al. 2023

Aerospace

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Fuel injection and mixing affect the characteristics of detonation initiation and propagation, as well as the propulsion performance of rotating detonation engine (RDE). A study on the injector is carried out in the present investigation. A rectangular-shaped hole-type fuel injector (RHFI) and slit-type fuel injector (SFI) were designed and compared experimentally at equivalent conditions. The investigation of the detonation propagation modes and the analysis of propulsion performance were carried out using fast Fourier transform (FFT), short-time Fourier transform (STFT), and unwrapped image post-processing. Under 50, 75, and 100 g/s flow rate conditions at an equivalence ratio of 1.0 ± 0.05, the RHFI has relatively stable detonation propagation characteristics, higher thrust, and specific impulse performance. Additionally, the results of the experiment indicate that the number of detonation waves affects performance.

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Section: Introductionmentioning

confidence: 99%

Effects of Injector Configuration on the Detonation Characteristics and Propulsion Performance of Rotating Detonation Engine (RDE)

Koo,

Lee,

Kim

et al. 2023

Aerospace

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Rotating detonation combustor performance informed through a novel megahertz-rate stagnation pressure measurement

Dille,

Frederick,

Slabaugh

et al. 2024

Physics of Fluids

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An experimental stagnation pressure measurement technique is presented for a rotating detonation combustor (RDC). Schlieren imaging enables rotating detonation wave passage to be correlated with oscillations observed in the under-expanded exhaust plume. By measuring the spatiotemporal variation in exhaust plume divergence angle, stagnation pressure measurements of the RDC were acquired at a rate of 1 MHz. Combustor mass flux was varied between 202 and 783 kg/m2s, producing equivalent available pressures (EAPs) in the range of 3.42–13.5 bar. Time-averaged stagnation pressure measurements gathered using this technique were in agreement with the measured EAP within ±1.5%. Time-resolved stagnation pressure measurements allow for the pressure ratio produced across detonation wave cycles to be determined. For the conditions tested, detonation pressure ratios and wave speeds decreased while increasing the mean operating pressure of the combustor. Numerical modeling of the conditions tested indicates that the decrease in pressure ratio and wave speed is a result of elevated levels of combustion prior to the detonation wave arrival (i.e., “preburning”). Simultaneous OH* chemiluminescence measurements within the combustion chamber show an increase in preburned heat release relative to detonative heat release for increasing operating pressures of the RDC, in agreement with the results of the numerical model. Modeled chemical kinetic timescales decrease by approximately the same magnitude by which the preburning mass fraction increased in the range of operating pressures tested, suggesting that the faster reaction rates associated with higher pressure combustion may be the reason for increased preburning within the combustor.

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Liquid fuels in rotating detonation engines: Advances and challenges

Zhu,

Zhang,

Chen

et al. 2024

Physics of Fluids

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The rotating detonation engine (RDE) has attracted considerable interest as a potential new propulsion system, owing to its ability to self-pressurize, its high thrust-to-weight ratio, and its simple structure. This paper provides a comprehensive review of the latest research advancements and challenges associated with the application of liquid fuels in RDEs. The study begins by focusing on the applicability of various liquid fuels in RDEs, examining the effects of fuel parameters—such as the equivalence ratio, the total temperature, the degree of pre-evaporation, and the droplet diameter—on detonation wave propagation and engine performance. Subsequently, the impact of inlet parameters and the optimization of combustor performance on detonation waves, along with control methods for mode-switching mechanisms, are investigated. Finally, the paper summarizes the common issues and challenges encountered in the application of liquid fuels in RDEs. These include droplet atomization, mixing and evaporation, detonation wave control, and combustor cooling. To address these challenges, future developments in RDEs may focus on four key areas: the use of complex fuels (such as blending fuels, sustainable aviation fuel, and other biofuels), detonation wave mode control, combustor cooling technologies, and the integration of RDEs with turbomachinery. These advancements will further propel the development of liquid-fueled rotating detonation technology.

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Bifurcation in Rotating Detonation Engine Operation with Continuously Variable Fuel Injection Location

Cited by 8 publications

References 51 publications

Effects of Injector Configuration on the Detonation Characteristics and Propulsion Performance of Rotating Detonation Engine (RDE)

Effects of Injector Configuration on the Detonation Characteristics and Propulsion Performance of Rotating Detonation Engine (RDE)

Rotating detonation combustor performance informed through a novel megahertz-rate stagnation pressure measurement

Liquid fuels in rotating detonation engines: Advances and challenges

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