Abstract
The present study investigated the performance of micro turbojet engine experimentally at various engine inlet pressure conditions, which covers the altitude up to 3.0 km. A test rig for engine performance measurements was built and installed in the altitude engine test facility located in Korea Aerospace Research Institute, and the performance tests were conducted under the altitude conditions obtained by reducing the engine inlet pressure. In this study, commercially available micro turbojet engine, Jetcat P300-RX, was used and the performance parameters, such as thrust, fuel flow rate, exhaust gas temperature, were measured for various PLA conditions at altitude simulating inlet pressure values. The results showed that as the inlet pressure becomes reduced, which means the altitude increases, the thrust and fuel flow rate of the engine decreases monotonously. For example, the thrust is 257.7N at sea level condition while it decreases to 183.7N at 3.0 km altitude condition. When the corrected performance parameters are introduced, those corrected values present single curve regardless of operating conditions. Those results will be used as the reference data not only for performance improvement of the component but also for indigenous engine development program.
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