You are asked to prepare an experimental setup to evaluate the proposed cylindrical, leading-edge region, film cooling geometry for gas turbine blade applications. The required compressed air (25°C), heaters, piping, flow meters, materials, thermocouples, CCD camera, and equipment for calibrations and measurements are available for your use. Please use the transient TLC method to map the surface temperature, heat transfer coefficient, and film cooling effectiveness distributions on the leading-edge surface as shown in below image. Based on the wind tunnel flow and cooling/ heating flow capability, one steady-state blowing ratio (cooling to mainstream mass flux ratio) will be tested: M = 1.0.
a. Show an overall sketch of your experimental test loop and the associated equipment and instrumentation required to conduct the proposed test, i.e., sketch your overall experimental setup along with a suitable flow measuring device and detail your test section design with proper materials using the transient TLC imaging technique.
b. Describe the transient TLC measurement principle, TLC calibration method, and detail the TLC measurement procedures using the transient technique with heated air.
c. Sketch and discuss the expected target surface temperature distributions (contours), heat transfer coefficient and film cooling/heating effectiveness distributions (contours) for one tested blowing ratio M = 1.0 and estimate the possible uncertainty.