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Radial turbines offer greater stage work capacity than axial turbines. If this advantage can be coupled with a capability of accommodating high turbine inlet temperatures, radial turbines will permit appreciable simplification of small gas turbine engines for use in future Army vehicles. A two-phase program is being conducted involving the design and testing of a cooled, single-stage, radial inflow turbine. A bicast rotor with solid blades was spun to failure, which occurred at a speed lower than predicted. Two spindle failures prevented a successful destructive spin-test of the rotor damaged in Turbine Build One. The third and final nozzle section was chosen from the two castings submitted by the casting vendor for evaluation. An integral-cored rotor casting was not acceptable for rig test and is being evaluated for possible use as a spin-test part. Turbine Build One was hot tested for seven hours. Considerable foreign object damage was experienced by the turbine, and performance data is not believed to be representative of the turbine design. A replacement turbine rotor and nozzle were prepared and used in Turbine Build Two. Testing was aborted because of high vibrations caused by a turbine rotor-to-shroud rub during the initial stand checkout. Turbine Build Three is now in progress, using hardware salvaged from Build Two. (Author).
A brief review of hot tests is given, and the fabrication status of the test rig is noted.
The report describes the design, fabrication and test of a radial turbine designed to produce 219.6 Btu/lb stage work at 87.5% efficiency, with a 5:1 stage pressure ratio. Turbine inlet gas conditions at design point were 257.5 psia and 2300F. The resulting turbine configuration consisted of an air-cooled, 12-bladed rotor designed for 67,000 rpm, and a 20-vaned air-cooled nozzle section of a reflex-type (supersonic) design. Both parts were designed as IN100 (PWA 658) investment castings. As part of the preliminary design effort, a fabrication study was conducted to evaluate feasible methods of casting the turbine nozzle and rotor. Results showed that the nozzle section could be cast as an integral assembly, but fabrication of the rotor as an integral casting was much more difficult. Bicasting was evaluated as an alternate method of fabricating the rotor, and results showed substantial advantages for the bicasting technique. However, neither method could produce designed rotor properties, and testing was conducted with structurally limited rotors. A test rig was designed and fabricated by the contractor. The test rig consisted of a supercharged gas generator, which had the capability of controlling the turbine load by varying the compressor flow rate. Burner testing preceded turbine testing. (Author).
The objective of this program was the design and fabrication of a air-cooled high-temperature radial turbine (HTRT) intended for experimental evaluation in a warm turbine test facility at the Lewis Research Center. The rotor and vane were designed to be tested as a scaled version (rotor diameter of 14.4 inches diameter) of a 8.021 inch diameter rotor designed to be capable of operating with a rotor inlet temperature (RIT) of 2300 deg. F, a nominal mass flow of 4.56 lbm/sec, a work level of equal or greater than 187 Btu/lbm, and an efficiency of 86% or greater. The rotor was also evaluated to determine it's feasibility to operate at 2500 deg F RIT. The rotor design conformed to the rotor blade flow path specified by NASA for compatibility with their test equipment. Fabrication was accomplished on three rotors, a bladeless rotor, a solid rotor, and an air-cooled rotor.
The objective of this program was the design and fabrication of a air-cooled high-temperature radial turbine (HTRT) intended for experimental evaluation in a warm turbine test facility at the LeRC. The rotor and vane were designed to be tested as a scaled version (rotor diameter of 14.4 inches diameter) of a 8.021 inch diameter rotor designed to be capable of operating with a rotor inlet temperature (RIT) of 2300 F, a nominal mass flow of 4.56 lbm/sec, a work level of equal or greater than 187 Btu/lbm, and efficiency of 86 percent or greater. The rotor was also evaluated to determine it's feasibility to operate at 2500 F RIT. The rotor design conformed to the rotor blade flow path specified by NASA for compatibility with their test equipment. Fabrication was accomplished on three rotors, a bladeless rotor, a solid rotor, and an air-cooled rotor. Snyder, Philip H. Unspecified Center...