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Development of high temperature turbine subsystem technology to a ''technology readiness status'': Phase II. Progress report for March 1978

Technical Report ·
DOI:https://doi.org/10.2172/5011904· OSTI ID:5011904
Design data affecting the planned facilities services for the HGPDT have been accumulated. A decision was made to increase the stiffness of the nozzle support plate. Thermocouple rakes rather than gas sampling probes will be used for temperature measurements in the second stage nozzle test configuration. Detailed design of the water cooled gas path liner for the turbine simulator test is complete. Detailed design effort on the heat transfer airfoil is underway. Coordinates for the transonic cascade nozzle and walls have been developed. Pressure gauges have been checked out, heat transfer gauges are being fabricated. The optical system for taking Schlieren photographs has been set up on the tunnel. Soil boring tests and a site survey of the area where the Pilot Gas Clean up System will be constructed, have been completed. Efforts have been initiated to define a new fixed bed CGS-combined cycle system using four 73 MW size gas turbines at 12 : 1 pressure ratio. The status of the TRV design as compared to the goal in a simple cycle operation is described. IN706 has been selected for the rotor wheels and spacers. Rotor critical speed studies have been performed for the two and three bearing rotor configurations. The low Btu gas staging point has been lowered from 57 to 49 percent load to reduce the size of the combustor liner in the pilot zone. The radiation from distillate oil has been estimated. A layout of the fuel nozzle test rig has been completed. Aerodynamic design of the first stage bucket has been completed. Alternative fabrication approaches have been identified.
Research Organization:
General Electric Co., Schenectady, N.Y. (USA). Gas Turbine Div.
OSTI ID:
5011904
Report Number(s):
FE-1806-44
Country of Publication:
United States
Language:
English