The aerodynamic performance of the compressor-drive turbine of the DOE Upgraded Gas Turbine (UGT) engine was determined in low-temperature air. The nominal turbine-inlet temperature was 320 K. Inlet pressures were varied between 0.4 and 2.4 bars absolute. The turbine blading used in these tests consisted of duplicates of the stator and rotor castings used in development engine tests. The as-received cast rotor blades had a significantly thicker profile than design and a fairly rough surface finish. Because of these blade profile imperfections three turbine rotor configurations were evaluated. These were the as-cast rotor, a reduced-roughness rotor, and a rotor with the blade profiles thinned to near the design profile. Tests to determine the effect of Reynolds number on the turbine performance were also made. (Author)
Cold-air performace of compressor-drive turbine of department of energy upgraded automobile gas turbine engine. II. Stage Performance
Leistung bei niedriger Lufttemperatur kompressorbetriebener Gasturbinen am Beispiel einer verbesserten Fahrzeuggasturbine. II. Teil: Leistungsbewertung
US Government Reports ; Okt ; 1-18
1982
18 Seiten
Report
Englisch
The ERDA/Chrysler Upgraded Gas Turbine Engine Objectives and Design
Kraftfahrwesen | 1976
|The ERDA/Chrysler Upgraded Gas Turbine Engine Objectives and Design
SAE Technical Papers | 1976
|