DIAGNOSTIC PERFORMANCE TESTING FOR GAS TURBINE ENGINES

摘要

An improved gas turbine engine diagnostic system is disclosedwhich is particularly adapted for direct measurement of compressorperformance, including efficiency and mass flow, for aircraft engines, withouthaving to remove the engine form the aircraft. The system includes aninstrumented compressor air discharge tube which has probes for totalpressure, static pressure and temperature. The instrumented air discharge tubemay be substituted for an existing air discharge tube for the engine to betested, without having to remove the engine. Transducers attached to theseprobes provide signals which are connected to a data recorder or computer.Data can be taken as the engine is run, either on ground test or flight test.The total mass airflow output from the compressor stage for various engineperformance settings can then be calculated using the static pressure, totalpressure and air temperature measurements. At the completion of the test, theinstrumented air tube can be removed and the original one replaced.