Prediction of Pressure Loss in Injector for Rotating Detonation Engines Using Single-element Simulations

Suzuki, Tomohito; Matsuo, Akiko; Daimon, Yu; Kawashima, Hideto; Kawasaki, Akira; Matsuoka, K.; Kasahara, Jiro

doi:10.2514/6.2020-3879

Cited by 3 publications

(2 citation statements)

References 7 publications

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“…7 provides the development of the flame position and the cell number ratios (nC) for examining the gains of the AMR method. The cell number ratio is obtained with the relationship given in Equation (8). In the Equation ( 8), nAMR and nCONS.…”

Section: Fig 6 Pressure Distribution Along the Detonation Tubementioning

confidence: 99%

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Numerical Investigation on Pulse Detonation Engine Performance Under Different Equivalence Ratio

Kocaaslan

2024

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Detonation-based engines have a higher thermal efficiency than deflagration-based engines and are therefore widely studied. In this study, the effect of initiation conditions on the detonation wave propagation and the performance of a pulse detonation engine, one type of detonation-based engine, was numerically investigated. Hydrogen-oxygen mixtures with equivalence ratios of φ=0.8, 1.0, and 1.2 were defined as initiation conditions with constant pressure and temperature. The numerical simulations were conducted using the transient explicit density-based solver in the ANSYS Fluent commercial software. The adaptability of the adaptive mesh refinement method in detonation-based engines was explored in the numerical studies, reducing the average total cell count by a factor of 2.617, and obtaining consistent results according to validation studies. The adaptive mesh refinement method was also used in numerical simulations where different equivalence ratios were defined. It was determined that an increase in the equivalence ratio resulted in an increase in the detonation wave velocity. Also, an increase in thrust distribution at the nozzle exit was observed before the blowdown stage, and the calculated thrust values for φ=0.8, φ=1.0, and φ=1.2 were 248.28 N, 264.5 N, and 270.83 N, respectively.

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Section: Fig 6 Pressure Distribution Along the Detonation Tubementioning

confidence: 99%

“…At the lowest compression ratio, the efficiency of detonation is 8% higher than deflagration. Suzuki et al [8] stated that detonation-based engines are 13% more efficient than conventional thermal engines.…”

Section: Introductionmentioning

confidence: 99%