SMALL GAS TURBINE ENGINE COMPONENT TECHNOLOGY - TURBINE. VOLUME 2. PHASE 2 SUMMARY REPORT
CURTISS-WRIGHT CORP WOOD-RIDGE NJ
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The report describes the aerodynamic, thermal, and mechanical design and analysis, fabrication, and experimental evaluation of a transpiration cooled, single stage axial-flow turbine component capable of operation at 2500F average inlet temperature. Phase II report gives the details of manufacture and results of test evaluations. One hundred hours of complete stage testing were accomplished with 2 hours at 2500F. The cascade rig was tested for 87 hours which included 1.2 hours at 2650F. All blading was in excellent condition after the tests and confirmed the efficacy of the thermal design and transpiration cooling as applied to small size blading. A work of 133 Btu per pound was achieved at a low level of efficiency, attributable to stator profile shape and low aspect ratio. One hundred thirty-seven hours of combustor testing at an average exit temperature of 2500F was accomplished with operating characteristics consistent with the turbine requirements. It was concluded that the advanced technology incorporated in the turbine design relative to blade cooling and turbine mechanical integrity are practical and can be applied to the design of advanced small gas turbine.
- Jet and Gas Turbine Engines