A METHOD OF INVESTIGATING THE THERMAL FATIGUE OF GAS TURBINE BLADES WITH PROGRAMMED THERMAL LOADING,
FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
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The thermal fatigue characteristics of turbine blades were investigated in a gas dynamic test stand. The test stand was modified to permit the automatic startup and shutdown of the combustion chamber and a programmed variation in the flow medium temperature. The automatic control system employed a complex of electromechanical time relays to control the functional systems at specified time intervals. The test stand is suitable for conducting extended tests with minimum discrepancies in maintaining regime dictated by subjective factors. The electromechanical time relay was designed to regulate the fuel flow down to one second within a range of 3-180 sec. The gas temperature could be varied from 3 to 100 degrees per second. The investigation also included tests of aircraft turbine blades and vanes made of ZhS-6k alloy. The test simulated the three most typical engine regimes engine startup and shutdown startup, checkout, shutdown starting, takeoff, nominal regime and shutdown.
- Jet and Gas Turbine Engines