Accession Number : AD0683215

Title :   TRANSITION AND COMPRESSOR SYSTEMS OF A CENTRIPETAL-FLOW TURBINE,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Freyman,Yu. I.

Report Date : 01 AUG 1968

Pagination or Media Count : 14

Abstract : Operation of a centripetal turbine in the transition and compressor regimes during sharp decreases of flow rate through the turbine is discussed, and experimental characteristics of a turbine operating in these regimes are presented. An approximate equation is derived to find the conditions of sudden transition from turbine to compressor operation. Experimental characteristics in the turbine-compressor transition regions for a centripetal turbine are presented graphically, and the locations of the transition jumps are found to be adequately represented by the derived equation. Transition back to the turbine regime occurs at a different point, thus forming a hysteresis loop for the transition processes. Graphs of the internal power of the turbine show that it absorbs substantial power in the compressor regimes and can thus be used as a brake under these conditions. Increased hysteresis effects are expected for high temperature gas operation (tests were made with compressed air). (Author)

Descriptors :   (*GAS TURBINES, PERFORMANCE(ENGINEERING)), COMPRESSORS, AERODYNAMIC CHARACTERISTICS, HYSTERESIS, USSR

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE