首页> 外文会议>ASME Turbo Expo: Turbomachinery Technical Conference and Exposition >DEVELOPMENT OF NEW SINGLE AND HIGH-DENSITY HEAT-FLUX GAUGES FOR UNSTEADY HEAT TRANSFER MEASUREMENTS FOR A ROTATING TRANSONIC TURBINE
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DEVELOPMENT OF NEW SINGLE AND HIGH-DENSITY HEAT-FLUX GAUGES FOR UNSTEADY HEAT TRANSFER MEASUREMENTS FOR A ROTATING TRANSONIC TURBINE

机译:用于旋转跨音速涡轮机的非定常热传递测量的新型单和高密度热通量计的开发

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This paper presents the development and implementation of a new generation of double-sided heat-flux gauges at The Ohio State University Gas Turbine Laboratory (GTL) along with heat transfer measurements for film-cooled airfoils in a single-stage high-pressure transonic turbine operating at design corrected conditions. Double-sided heat flux gauges are a critical part of turbine cooling studies, and the new generation improves upon the durability and stability of previous designs while also introducing high-density layouts that provide better spatial resolution. These new customizable high-density double-sided heat flux gauges allow for multiple heat transfer measurements in a small geometric area such as immediately downstream of a row of cooling holes on an airfoil. Two high-density designs are utilized: Type A consists of 9 gauges laid out within a 5 mm by 2.6 mm (0.20 inch by 0.10 inch) area on the pressure surface of an airfoil, and Type B consists of 7 gauges located at points of predicted interest on the suction surface. Both individual and high-density heat flux gauges are installed on the blades of a transonic turbine experiment for the second build of the High-Pressure Turbine Innovative Cooling program (HPTIC2). Run in a short duration facility, the single-stage high-pressure turbine operated at design-corrected conditions (matching corrected speed, flow function, and pressure ratio) with forward and aft purge flow and film-cooled blades. Gauges are placed at repeated locations across different cooling schemes in a rainbow rotor configuration. Airfoil film-cooling schemes include round, fan, and advanced shaped cooling holes in addition to uncooled airfoils. Both the pressure and suction surfaces of the airfoils are instrumented at multiple wetted distance locations and percent spans from roughly 10% to 90%. Results from these tests are presented as both time-average values and time-accurate ensemble averages in order to capture unsteady motion and heat transfer distribution created by strong secondary flows and cooling flows.
机译:本文提出了在俄亥俄州州大学燃气轮机实验室(GTL)的新一代双面热量磁通量的开发和实施以及在单级高压跨音型涡轮机中的薄膜冷却翼型的传热测量在设计纠正条件下运行。双面热通量计是涡轮机冷却研究的关键部分,新一代的耐用性和稳定性的耐用性和稳定性也在引入提供更好的空间分辨率的高密度布局。这些新的可定制的高密度双面热量磁通量允许在小几何区域中进行多次传热测量,例如在翼型上的一排冷却孔的行下游。使用两种高密度设计:A型由9℃的9个仪表组成,在翼型的压力表面上5毫米×2.6毫米(0.20英寸×0.10英寸)区域,B型由7个仪表组成,位于点预测吸入表面的兴趣。单个和高密度的热通量计均安装在高压涡轮机创新冷却程序(HPTIC2)的第二个构建的跨音涡轮机实验的刀片上。在短持续时间设施中运行,单级高压涡轮机在设计校正的条件下操作(匹配校正速度,流量和压力比),前后吹扫流动和薄膜冷却刀片。在彩虹转子配置中,仪表横跨不同冷却方案的重复位置。除了未冷却翼型外,翼型薄膜冷却方案还包括圆形,风扇和先进的形状的冷却孔。翼型的压力和抽吸表面都在多个湿润的距离位置仪表,百分比从大约10%到90%。这些测试的结果呈现为时间平均值和时间准确的集合平均值,以捕获由强次级流量和冷却流产生的不稳定运动和传热分布。

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