High-Temperature-Turbine Technology Program. Phase 2. Technology Test and Support Studies. Topical Report. Transpiration Cooled Turbine Vane Aerodynamic Cascade Test Results and Analysis

摘要

Testing was conducted to determine the aerodynamic performance of a turbine vane using transpiration air-cooling (TAC) and a vane of identical profile with no cooling provisions to determine the effect of cooling on vane kinetic energy efficiency and loss coefficient. The test configuration was a 60 exp 0 , 10-vane section of a first-stage turbine stator designed for 1.6 pressure ratio, cooling air flow equal to 6.1% of primary flow, 3000 exp 0 F turbine inlet temperature, and primary-to-coolant temperature ratio of 2.7. To enable comparison with other investigations, tests were conducted at three pressure ratios, 1.4, 1.5 and 1.6, three coolant flows, 75, 100, and 120% of design, and three primary-to-coolant temperature ratios, 2.70, 1.55 and 1.15. Efficiency, loss-coefficient, and flow-capacity test results were in good agreement with predicted values for both the TAC and uncooled vanes. The testing demonstrated that it is necessary to conduct test evaluations of transpiration air-cooled components at or near-design coolant-to-gas stream temperature ratio in order to achieve correct results. (ERA citation 08:035724)