Preliminary Evaluation of Turbine Performance with Variable-Area Turbine Nozzles in a Turbojet Engine
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC
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The performance of a two-stage turbine with variable-area first - stage turbine nozzles was determined in the NACA Lewis altitude wind tunnel over a range of simulated altitudes from 15,000 to 44,000 feet and engine speeds from 50 to 100 percent of rated speed. The variable-area turbine nozzles were found to be mechanically reliable and to have negligible leakage losses. Increasing the turbine-nozzle-throat area from 1.15 to 1.67 square feet increased the corrected turbine gas flow or effective turbine nozzle area about 10 percent. At a given corrected turbine speed and turbine speed and turbine pressure ratio, changing the turbine nozzle area from 1.30 to 1.67 square feet lowered the efficiency 3 or 4 percent. The effect of increasing the turbine nozzle area from 1.15 to 1.67 square feet decreasing the turning angle about 7-12 deg would be to lower the turbine efficiency about 5 or 6 percent.
- Jet and Gas Turbine Engines