Synchronized Initiation of Two Cylindrical Rotating Detonation Engines

Author:

Sakata Rinpei1,Inada Masahiro1,Itouyama Noboru1,Matsuoka Ken1,Kasahara Jiro1ORCID,Kawasaki Akira2ORCID,Matsuo Akiko3,Funaki Ikkoh4

Affiliation:

1. Nagoya University, Nagoya 464-8603, Japan

2. Shizuoka University, Hamamatsu 432-8561, Japan

3. Keio University, Yokohama 223-8522, Japan

4. JAXA Institute of Space and Astronautical Science, Sagamihara 252-5210, Japan

Abstract

A coupled cylindrical rotating detonation engine (RDE) with two cylindrical RDEs (both combustors had a combustor inner diameter of 23 mm and an axial length of 30 mm) placed next to each other was tested for rocket clustering application. The objective of the experiment was to achieve two-engine synchronized initiation with a single igniter. Experiments were conducted on the inner wall of the combustors with different connecting-hole diameters and wall heights to evaluate the ignition delay time, combustion mode, and propulsion performance. The propellants were gaseous ethylene and oxygen, and experiments were conducted under constant conditions of mass flow rate ([Formula: see text]), equivalence ratio ([Formula: see text]), and backpressure (approximately 10 kPa). When the two combustion chambers were completely separated by a wall, ignition occurred with a time delay of 260 ms in the chamber without an igniter. However, when a large hole ([Formula: see text] diameter) was placed in the wall separating the two combustion chambers, synchronous initiation was successful. Synchronous initiation was also successful when the wall height was lowered (7-mm height). Under both conditions, the same level of specific impulse was achieved as for RDEs operating at the same mass flux.

Funder

Japan Society for the Promotion of Science

Japan Aerospace Exploration Agency Institute of Space and Astronautical Science

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

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