Annular Combustor Test Facility in JAXA

摘要

JAXA AP-6 Annular Combustor Test Facility was renewed in 2007. Now, it can supply airflow at pressures up to 2 MPa, temperatures up to 75.3 K, and flow rate up to 20.5 kg/s. It is even designed to stand the exhaust temperature up to 2000 K. An annular traversing gas and temperature measurement system and a flame monitoring view windows for combustion are also equipped in this facility. Originally, this facility was built in 1975 for the development of the annular combustor for the FJR710 Turbofan-engine, the purely Japanese high-bypass turbofan engine. By virtue of the present modification, we can meet the requirement, for conducting combustion tests of annular combustors, to be installed in the ECO engine, being aimed for production in the "Research and Development for an Environment-Friendly, Small Aircraft Engine" project, supervised by the Ministry of Economy, Trade and Industry. Furthermore, this augmentation gives us an opportunity for developing the low-NO{sub}x annular combustor of the next generation civil aero-engines.