Experimental quantitative turbine bounday-layer investigations using multiple hot film sensor

摘要

In recent years, the quantitative investigation of boundary-layers has become an important tool for developing and designing of components. In particular, the measurement techniques of boundary-layer under low Reynolds Number condition become more important. For this purpose, special multiple hot-film sensors of stick-on type have been developed using thin-film processing techniques and applied to turbine nozzle guide vanes. The instrumented vanes were built into parts of a planar cascade rig and were run on the turbine test facility of cold flow. The hot-film senosrs were also applied to a cone model that was designed so that it originates shock waves, and tested in a wind tunnel using supersonic flow facility to investigate quantitative boundary-layer.