Experimental Study on Truncated Conical Rotating Detonation Engines with Diverging Flows

Kotaro Nakata, Kosei Ota, Shiro Ito, Kazuki Ishihara, Keisuke Goto, Itouyama Noboru, Hiroaki Watanabe, Akira Kawasaki, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This study focused on acceleration of propellant to supersonic speed with a compact engine. Increase in the exhaust velocity of a rocket engine leads to improvement of the thrust performance. Several combustion tests were conducted for a small rotating detonation engine (RDE) whose channel is truncated conical shaped (diverging angle (formula presented)), under low back pressure conditions. In these tests, gaseous (formula presented) were used as the propellant, and the mass flow rate were ranged from 56 to 123 g/s. The pressure ratio between the maximum value in the engine and at the exit was approximately 0.16, which was confirmed to be significantly below the critical value for a sonic flow. Namely, the exhaust flow was supersonic, even though there was no convent section in the engine. In a range of propellant mass flow rate, specific impulses were approximately 110% compared to those in a cylindrical RDE with a uniform cross-section combustor.

Original languageEnglish
Title of host publicationAIAA Propulsion and Energy Forum, 2021
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624106118
DOIs
Publication statusPublished - 2021
EventAIAA Propulsion and Energy Forum, 2021 - Virtual, Online
Duration: 2021 Aug 92021 Aug 11

Publication series

NameAIAA Propulsion and Energy Forum, 2021

Conference

ConferenceAIAA Propulsion and Energy Forum, 2021
CityVirtual, Online
Period21/8/921/8/11

ASJC Scopus subject areas

  • Energy(all)
  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Mechanical Engineering

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