Thermodynamic Performance Results for Rotating Detonation Rocket Engine with Distributed Heat Addition using Cantera

Burr, Jason R.; Paulson, Eric J.

doi:10.2514/6.2021-3682

Cited by 8 publications

(6 citation statements)

References 27 publications

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“…Detonation combustion with a gas fuelgas oxidizer has been reported to have worse performance than theoretically determined due to non-detonation combustion such as parasitic and commensal combustion. [22][23][24][25] The method of accelerating the vaporization of liquid fuels is believed to encourage other combustions than detonation combustion, like RDCs with gas fuels-gas oxidizers. In this study, using liquid fuel and a gas oxidizer at room temperature suppressed combustions other than detonation combustion, which might have increased the detonation speed compared to other studies.…”

Section: Resultsmentioning

confidence: 99%

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Visualization and Performance Evaluation of a Liquid-Ethanol Cylindrical Rotating Detonation Combustor

Ishihara

Yoneyama

Sato

et al. 2023

Trans. Japan Soc. Aero. S Sci.

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Rotating detonation combustors (RDCs) are among the combustors that use supersonic combustion waves known as detonation waves, and are expected to simplify engine systems and improve thermal efficiency due to their supersonic combustion and compression performance using shock waves. Research is also being actively conducted worldwide on a cylindrical RDC; a RDC without an inner cylinder, which is expected to simplify and downsize the combustor. However, most of the research was performed using gas propellants, and liquid propellants were rarely used. Since liquid propellants are used in many combustors, it is important to evaluate the performance of RDCs with liquid propellants. In this study, a cylindrical RDC with a liquid ethanol-gas oxygen mixture was constructed and tested at a flow rate of 31.5 « 5.0 g/s, an equivalence ratio of 0.46-1.39, and a back pressure of 14.5 « 2.5 kPa. The thrust was shown to depend strongly on the combustor bottom pressure history. In addition, the start-up process of the cylindrical RDC with liquid fuel was clarified by self-luminous and CH + radical visualizations. It was found that the detonation wavefront propagated at a distance of 2-3 mm from the combustor bottom, and the main combustion region was 10-15 mm in height.

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Section: Resultsmentioning

confidence: 99%

“…Moreover, it has been suggested that combustion other than detonation combustion is the cause of the lowerthan-theoretical thrust performance. [23][24][25] As shown above, various studies have been performed, but there are still many issues to be solved. One of them is the applicability of liquid propellants.…”

Section: Introductionmentioning

confidence: 99%

Visualization and Performance Evaluation of a Liquid-Ethanol Cylindrical Rotating Detonation Combustor

Ishihara

Yoneyama

Sato

et al. 2023

Trans. Japan Soc. Aero. S Sci.

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“…As more propellant is consumed by deflagration, less propellant remains to support the detonation wave. Furthermore, deflagration raises the temperature of the mixture ahead of the detonation wave, increasing the effective speed of sound and decreasing the detonation wave Mach number [40]. Researchers have examined the impact of the wall curvature and deflagrative losses.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study on the Propagation Characteristics of Rotating Detonation Wave with Liquid Hydrocarbon/High-Enthalpy Air Mixture

Jia,

Zhang,

Meng

et al. 2023

Aerospace

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Rotating detonation engines (RDEs) are a promising propulsion technology featuring high thermal efficiency and a simple structure. To adapt the practical engineering applications of ramjet RDEs, rotating detonation combustion using a liquid hydrocarbon and pure air mixture will be required. This paper presents an experimental study on the propagation characteristics of rotating detonation waves with a liquid hydrocarbon and high-enthalpy air mixture in a hollow cylindrical chamber. The parameters, such as the equivalence ratio and inlet mass flux, are considered in this experiment. The frequency and the propagation velocity of rotating detonation combustion are analyzed under typical operations. The experimental results show that the peak pressure and propagation velocity of the rotating detonation wave are close to the C-J theoretical values under the inlet mass flux of 400 kg/(m2s). Both the propagation velocity and peak pressure of the rotating detonation wave decrease as the mass flux and equivalence ratio are reduced while the number of detonation wavefronts increases. Detonation wave instability tends to occur when the inlet mass flux decreases. There is a transition progress from thermo-acoustic combustion to rotating detonation combustion in the experiment under the condition of mass flux 350 kg/(m2s) and the equivalent ratio 0.8. The static pressure in the chamber is higher during detonation combustion than during thermo-acoustic combustion. These experimental results provide evidence that rotating detonation waves have the potential to significantly improve propulsion performance. The findings can serve as a valuable reference for the practical engineering application of rotating detonation engines.

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“…The rotating detonation rocket engine (RDRE) is an emerging engine technology that can revolutionize space propulsion. This detonation-based engine with supersonic combustion-driven shock waves offers several advantages over traditional rocket systems such as lower injection pressures 2 , a significant size/weight reduction due to the compact combustion zone 3,4 , lower pressure requirements for the gas generator and drive pumps 2 , less susceptibility to acoustic instabilities due to mode locking, and increased specific impulse performance on the order of 10% 5,6 . Detonation-based rocket engine technology can create new cost-competitive markets that result in considerable savings and accelerate space exploration through versatility in engine thrust scaling and streamlined system integration.…”

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confidence: 99%

“…4 Maurice J. Zucrow Laboratories, Purdue University, West Lafayette, IN 47907, USA. 5 William E. Boeing Department of Aeronautics and Astronautics, University of Washington, Seattle, WA 98195, USA. 6 Naval Research Laboratory, Washington, DC 20375, USA.…”

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confidence: 99%

Experimental validation of rotating detonation for rocket propulsion

Bennewitz,

Burr,

Bigler

et al. 2023

Sci Rep

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Space travel requires high-powered, efficient rocket propulsion systems for controllable launch vehicles and safe planetary entry. Interplanetary travel will rely on energy-dense propellants to produce thrust via combustion as the heat generation process to convert chemical to thermal energy. In propulsion devices, combustion can occur through deflagration or detonation, each having vastly different characteristics. Deflagration is subsonic burning at effectively constant pressure and is the main means of thermal energy generation in modern rockets. Alternatively, detonation is a supersonic combustion-driven shock offering several advantages. Detonations entail compact heat release zones at elevated local pressure and temperature. Specifically, rotating detonation rocket engines (RDREs) use detonation as the primary means of energy conversion, producing more useful available work compared to equivalent deflagration-based devices; detonation-based combustion is poised to radically improve rocket performance compared to today’s constant pressure engines, producing up to 10$$\%$$ % increased thrust. This new propulsion cycle will also reduce thruster size and/or weight, lower injection pressures, and are less susceptible to engine-damaging acoustic instabilities. Here we present a collective effort to benchmark performance and standardize operability of rotating detonation rocket engines to develop the RDRE technology readiness level towards a flight demonstration. Key detonation physics unique to RDREs, driving consistency and control of chamber dynamics across the engine operating envelope, are identified and addressed to drive down the variability and stochasticity observed in previous studies. This effort demonstrates an RDRE operating consistently across multiple facilities, validating this technology’s performance as the foundation of RDRE architecture for future aerospace applications.

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Thermodynamic Performance Results for Rotating Detonation Rocket Engine with Distributed Heat Addition using Cantera

Cited by 8 publications

References 27 publications

Visualization and Performance Evaluation of a Liquid-Ethanol Cylindrical Rotating Detonation Combustor

Visualization and Performance Evaluation of a Liquid-Ethanol Cylindrical Rotating Detonation Combustor

Experimental Study on the Propagation Characteristics of Rotating Detonation Wave with Liquid Hydrocarbon/High-Enthalpy Air Mixture

Experimental validation of rotating detonation for rocket propulsion

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