Flight Demonstration of Detonation Engine System Using Sounding Rocket S-520-31: Performance of Rotating Detonation Engine

Goto, Keisuké; Matsuoka, K.; Matsuyama, Koichi; Kawasaki, Akira; Watanabe, Hiroaki; Itouyama, Noboru; Ishihara, Kaoru; Buyakofu, Valentin; Noda, Tomoyuki; Kasahara, Jiro; Matsuo, Akiko; Funaki, Ikkoh; Nakata, Daisuke; Uchiumi, Masaharu; Habu, Hiroto; Takeuchi, Shinsuke; Arakawa, Satoshi; Masuda, Junichi; Maehara, Kenji; Nakao, Tatsuro; Yamada, Kazuhiko

doi:10.2514/6.2022-0232

Cited by 10 publications

(2 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The test results promise RDE engines with lower ignition delay time as compared to conventional propellants such as hydrogen or kerosene. The Japanese space agency has already tested an RDE in space in 2021 [159][160][161]. These experiments are a clear indication of the future of RDEs as a propulsion device for space technologies.…”

Section: Application Of Rdes In Propulsionmentioning

confidence: 99%

A Review of Pressure Gain Combustion Solutions for Aerospace Propulsion

Purushothaman

Renuke

Sorce

et al. 2022

Volume 4: Cycle Innovations; Cycle Innovations: Energy Storage

View full text Add to dashboard Cite

Recent developments in Pressure Gain Combustion (PGC) technology have demonstrated its ability to achieve higher thermal efficiencies and lower carbon emissions as compared to conventional gas turbine counterpart working in Brayton cycle. Ongoing studies suggest the possibility of implementing PGC in aircraft engines by replacing the high-pressure section (HP compressor, combustion chamber and HP turbine) with a PGC system. This, coupled with research on advanced materials and cooling solutions, offers the potential for higher overall gas turbine efficiency and fuel economy, contributing towards emission reduction of the aviation sector. This paper aims at a comprehensive review of PGC technology solutions applied in the area of aero propulsion. Reported background covers the historic as well as ongoing research activities at the component level, the cycle level, and the propulsion application of Pulse Detonation Engine (PDE), Rotating Detonation Engine (RDE), Oblique Detonation Wave Engine (ODWE), Free Piston Composite Cycle Engine (FP-CCE), and wave rotor engines. The analytical, numerical, and experimental research work is reviewed, providing also a comparison of PGC engine conceptual designs with existing gas turbine engines used in aerospace propulsion.

show abstract

Section: Application Of Rdes In Propulsionmentioning

confidence: 99%

A Review of Pressure Gain Combustion Solutions for Aerospace Propulsion

Purushothaman

Renuke

Sorce

et al. 2022

Volume 4: Cycle Innovations; Cycle Innovations: Energy Storage

View full text Add to dashboard Cite

show abstract

“…The expected thermal efficiency of a gas turbine system incorporating RDCs was estimated at 66.4%. 7) RDCs have been demonstrated in space, 8) and research and development for practical use of RDCs are currently being conducted. [9][10][11] In this way, RDCs are being actively researched by research institutes all over the world.…”

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.

Self Cite

View full text Add to dashboard Cite

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.

show abstract