Accession Number : AD0689221

Title :   A METHOD OF INVESTIGATING THE THERMAL FATIGUE OF GAS TURBINE BLADES WITH PROGRAMMED THERMAL LOADING,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Kravchuk,L. V. ; Kuriat,R. I. ; Khalimon,F. F.

Report Date : 04 MAR 1968

Pagination or Media Count : 12

Abstract : 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.

Descriptors :   (*GAS TURBINE BLADES, FATIGUE(MECHANICS)), THERMAL STRESSES, TURBOJET ENGINES, GAS TURBINES, TEST METHODS, USSR

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE