Parametric Performance Evaluation of a Jet Engine Derived from a Turbocharger.

摘要

Previous conceptual studies have shown that it is feasible to construct a low-thrust, jet engine, based on a production turbocharger at relatively low cost. A parametric evaluation was performed on a turbojet engine derived from an AiResearch 1.5 lb(m)/sec airflow turbocharger unit to determine its static performance characteristics and the maximum attainable thrust without augmentation or major component modification. The performance of various turbine housing/nozzle combinations was measured in steady state operation using a much improved instrumentation system, together with various system improvements. Parameters were measured on a common time base and plotted to depict the total performance of the unit over its usable range. Maximum thrust obtained was 97 lb(f), exceeding the initially predicted theoretical value of 67 lb(f) by 45%. Data was reduced to coded 3 digit numbers for programming and plotting using the CDC 6600 computer. The results were machine plots depicting the performance characteristics of the unaugmented engine for use in further studies including augmentation. In addition, computer performance programs for coded raw data were written for future data reduction and analysis. (Author)