TY - JOUR
T1 - Investigation into the effective injector area of a rotating detonation engine with impact of backflow
AU - Goto, K.
AU - Yokoo, R.
AU - Kawasaki, A.
AU - Matsuoka, K.
AU - Kasahara, J.
AU - Matsuo, A.
AU - Funaki, I.
AU - Kawashima, H.
N1 - Funding Information:
The present rotating detonation engine development was subsidized by the “Study on Innovative Detonation Propulsion Mechanism” Research-and-Development Grant Program (Engineering) of the Institute of Space and Astronautical Science of the Japan Aerospace Exploration Agency and the “Research and Development of an Ultra-High-Thermal-Efficiency Rotating Detonation Engine with Self-Compression Mechanism” Advanced Research Program for Energy and Environmental Technologies of the New Energy and Industrial Technology Development Organization. The fundamental device development was subsidized by Grant-in-Aid for Scientific Research (A), No. 24246137. The test piece and test chamber were manufactured by Yasuda Koki Co., Ltd., Mizutani Seiki Co., Ltd., and Nakamura Construction Co., Ltd. Funding was provided by Japan Society for the Promotion of Science (Grant Nos. JP19H05464, JP18KK0127, JP17H03480, JP17K18937), Institute of Space and Astronautical Science.
Funding Information:
The present rotating detonation engine development was subsidized by the “Study on Innovative Detonation Propulsion Mechanism” Research-and-Development Grant Program (Engineering) of the Institute of Space and Astronautical Science of the Japan Aerospace Exploration Agency and the “Research and Development of an Ultra-High-Thermal-Efficiency Rotating Detonation Engine with Self-Compression Mechanism” Advanced Research Program for Energy and Environmental Technologies of the New Energy and Industrial Technology Development Organization. The fundamental device development was subsidized by Grant-in-Aid for Scientific Research (A), No. 24246137. The test piece and test chamber were manufactured by Yasuda Koki Co., Ltd., Mizutani Seiki Co., Ltd., and Nakamura Construction Co., Ltd. Funding was provided by Japan Society for the Promotion of Science (Grant Nos. JP19H05464, JP18KK0127, JP17H03480, JP17K18937), Institute of Space and Astronautical Science.
Publisher Copyright:
© 2021, The Author(s), under exclusive licence to Springer-Verlag GmbH, DE part of Springer Nature.
PY - 2021/10
Y1 - 2021/10
N2 - For rotating detonation engines, the high-pressure region behind the detonation causes backflow into the plenum, making it difficult to properly design injectors to achieve the target pressure balance due to blockage of a part of the injector area during engine operation. In this paper, we present the pressure and thrust measurement of a rotating detonation engine with two different triplet injectors (fuel injector diameters of 0.8 mm and 1.0 mm) using gaseous methane, gaseous ethylene, and gaseous oxygen. The detonation wave propagation velocity with the fuel injector diameter of 0.8 mm was approximately 200 m/s higher than that with the fuel injector diameter of 1.0 mm. Combustor pressures and specific impulses were almost identical for both fuel injector diameters in this study. For our evaluation of the extent to which the available injector area can be utilized during engine operation, the effective injector area ratio was defined as the ratio of the plenum pressure during burn time to the pre-ignition value. Regardless of fuel species and fuel injector orifice diameter, the effective injector area ratio decreased proportionally with the ratio of combustor pressure to pre-ignition plenum pressure. This result implies that the pressure balance between the upstream plenum pressure and the combustor pressure can be roughly determined taking the effect of backflow into consideration.
AB - For rotating detonation engines, the high-pressure region behind the detonation causes backflow into the plenum, making it difficult to properly design injectors to achieve the target pressure balance due to blockage of a part of the injector area during engine operation. In this paper, we present the pressure and thrust measurement of a rotating detonation engine with two different triplet injectors (fuel injector diameters of 0.8 mm and 1.0 mm) using gaseous methane, gaseous ethylene, and gaseous oxygen. The detonation wave propagation velocity with the fuel injector diameter of 0.8 mm was approximately 200 m/s higher than that with the fuel injector diameter of 1.0 mm. Combustor pressures and specific impulses were almost identical for both fuel injector diameters in this study. For our evaluation of the extent to which the available injector area can be utilized during engine operation, the effective injector area ratio was defined as the ratio of the plenum pressure during burn time to the pre-ignition value. Regardless of fuel species and fuel injector orifice diameter, the effective injector area ratio decreased proportionally with the ratio of combustor pressure to pre-ignition plenum pressure. This result implies that the pressure balance between the upstream plenum pressure and the combustor pressure can be roughly determined taking the effect of backflow into consideration.
KW - Backflow
KW - Injector
KW - Propulsive performance
KW - Rotating detonation engine
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U2 - 10.1007/s00193-021-00998-9
DO - 10.1007/s00193-021-00998-9
M3 - Article
AN - SCOPUS:85102896520
SN - 0938-1287
VL - 31
SP - 753
EP - 762
JO - Shock Waves
JF - Shock Waves
IS - 7
ER -