Current State of NASA Continuously Rotating Detonation Cycle Engine Development

Teasley, Thomas W.; Fedotowsky, Tessa M.; Gradl, Paul R.; Austin, Benjamin L.; Heister, Stephen D.

doi:10.2514/6.2023-1873

Cited by 12 publications

(2 citation statements)

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“…It was also found that orbital transfer systems costs can be lowered by adopting PDCs [21,22], while the compact configuration of the engine makes it a suitable candidate for powering Unmanned (Combat) Aerial Vehicles [23] and rocket engines [19]. Currently, the advantages of pressuregain combustion propulsion systems are renewing interest in such engines, and interesting new developments in the field of detonation-based engines have been reported over the last year [24][25][26].…”

Section: Introductionmentioning

confidence: 99%

Experimental Pressure Gain Analysis of Pulsed Detonation Engine

Bogoi,

Cuciuc,

Cojocea

et al. 2024

Aerospace

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A pulsed detonation chamber (PDC) equipped with Hartmann–Sprenger resonators has been designed and tested for both Hydrogen/air and Hydrogen/Oxygen mixtures. A full-factorial experimental campaign employing four factors with four levels each has been carried out for both mixtures. Instantaneous static pressure has been measured at two locations on the exhaust pipe of the PDC, and the signal has been processed to extract the average and maximum cycle pressures and the operating frequency of the spark plug. The PDC has been shown to be able to reach sustained detonation cycles over a length below 200 mm, measured from the spark plug to the first pressure sensor. The optimal regimes for both air and Oxygen operation have been determined, and the influence of the four factors on the responses is discussed.

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Section: Introductionmentioning

confidence: 99%

Experimental Pressure Gain Analysis of Pulsed Detonation Engine

Bogoi,

Cuciuc,

Cojocea

et al. 2024

Aerospace

View full text Add to dashboard Cite

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“…Therefore, active research has been conducted on RDE over the past decade. In recent years, practical research and benefits have been reported [9][10][11][12] Research is being conducted to implement PGC, which is realized via detonative combustion. Wu et al [13] carried out thermodynamic cycle analyses and found that detonative combustion is not completely identical to the Humphrey cycle, but it generally has similar characteristics to the Humphrey cycle.…”

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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Air-breathing rotating detonation engine supplied with liquid kerosene: propulsive performance and combustion stability

Perkowski,

Bilar,

Augustyn

et al. 2024

Shock Waves

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Experimental results are presented for a rotating detonation engine supplied with liquid kerosene and preheated air without liquid or gaseous additions to the propellant mixture. Various combustion modes for the generic combustor geometry design were observed—from deflagration, through pulsed combustion and high-frequency instabilities, to stable detonation propagation. Attention was paid to detonation stability (if present), its characteristics, and the propulsive performance of the combustor with a focus on specific thrust and pressure gain through thrust and outlet total pressure measurement. These parameters measured for the observed modes were compared. The stability of the detonation combustion proved not to be critical to achieve high performance of the combustion chamber. For example, high performance was achieved for combustion modes with high-frequency instabilities.

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Current State of NASA Continuously Rotating Detonation Cycle Engine Development

Cited by 12 publications

References 0 publications

Experimental Pressure Gain Analysis of Pulsed Detonation Engine

Experimental Pressure Gain Analysis of Pulsed Detonation Engine

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

Air-breathing rotating detonation engine supplied with liquid kerosene: propulsive performance and combustion stability

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