Combustion characteristics of a supersonic combustor model for a JAXA flight experiment
-
Published:2023-05-15
Issue:6
Volume:15
Page:827-844
-
ISSN:1868-2502
-
Container-title:CEAS Space Journal
-
language:en
-
Short-container-title:CEAS Space J
Author:
Takahashi MasahiroORCID, Kobayashi Kan, Tomioka Sadatake
Abstract
AbstractJAXA is conducting a flight-ground test comparison program to clarify the “facility effect” on hypersonic aerodynamics and combustion phenomena and to develop a CFD tool for predicting flight data from ground test data. The aim is a flight experiment to obtain data on aerodynamic heating and supersonic combustion under actual flight conditions and to validate the CFD tool using flight data and the corresponding ground test data. This study aimed at determining a flow-path geometry and a fuel injector configuration for a supersonic combustor suitable for clarifying the influence of the different test flow compositions between flight and ground test conditions on combustion. The candidate configurations proposed by the CFD study were evaluated by direct-connect combustion tests using ethylene fuel. The results showed that a combustor flow was symmetric when the fuel equivalence ratio was low and asymmetric when the equivalence ratio and the pressure in the combustor were high. Because an asymmetric flow is unsuitable for validating CFD based on steady RANS, the total equivalence ratio was limited to 0.44. The combustor model uses two-stage fuel injectors and cavity flame holders to combust ethylene fuel. The depth of the cavity flame holder had little influence on combustion. However, the number of injection holes for the injector located downstream of the cavity affected the combustor pressure. The combustor flow-path design was finalized based on the combustion test results. In addition, an ethylene fuel ignition method using pilot hydrogen injection, adopted for the flight experiment, was also demonstrated successfully.
Funder
Innovative Science and Technology Initiative for Security, ATLA
Publisher
Springer Science and Business Media LLC
Subject
Space and Planetary Science,Aerospace Engineering
Reference17 articles.
1. Yatsuyanagi, N., Chinzei, N., Mitani, T., Wakamatsu, Y., Masuya, G., Iwagami, S., Endo, M., Hanus, G.: Ramjet Engine Test Facility (RJTF) in NAL-KRC, Japan. AIAA Paper 1998-1511 (1998) 2. Tomioka, S., Hiraiwa, T., Kobayashi, K., Izumikawa, M., Kishida, T., Yamasaki, H.: Vitiation effects on scramjet engine performance in Mach 6 flight conditions. J. Propul. Power 23, 789–796 (2007). https://doi.org/10.2514/1.28149 3. Pellett, G.L., Bruno, C., Chinitz, W.: Review of air vitiation effects on scramjet ignition and flameholding combustion processes. AIAA Paper 2002-3880 (2002) 4. Rockwell, R.D., Jr., Goyne, C.P., Haw, W., Krauss, R.H., McDaniel, J.C., Trefny, C.J.: Experimental study of test-medium vitiation effects on dual-mode scramjet performance. J. Propul. Power 27, 1135–1142 (2011). https://doi.org/10.2514/1.B34180 5. Tatman, B.J., Rockwell, R.D., Goyne, C.P., McDaniel, J.C., Donohue, J.M.: Experimental study of vitiation effects on flameholding in a cavity flameholder. J. Propul. Power 29, 417–423 (2011). https://doi.org/10.2514/1.B34687
Cited by
1 articles.
订阅此论文施引文献
订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献
1. JAXA RD1 Flight Experiment on Supersonic Combustion: Part 2 Combustion Test Result;25th AIAA International Space Planes and Hypersonic Systems and Technologies Conference;2023-05-27
|
|