Mid and High Temperature Rotor Program for a 30 kW Gas Turbine Generator Set.

摘要

The objective of this program was the advancement of small radial inflow turbine technology in the area of operation at higher turbine inlet gas temperatures. A two-phase program was structured. In the first phase, two mid-temperature range 4.50-inch tip diameter radial inflow turbine rotors, were designed for a 30-kW gas turbine with a maximum turbine inlet nozzle temperature of 2200 F. One rotor was internally air-cooled and the other conduction-cooled in a monorotor (integral turbine and compressor) arrangement. On the basis of performance, structural and cost analyses, the monorotor arrangement was selected for continued development evaluation. A ceramic high temperature rotor was also studied for operation at a maximum turbine inlet nozzle temperature of 2600 F. Estimated failure probability for this high temperature rotor study was too high to warrant continuation.