| Gas turbine is widely used in the fields of transportation, metallurgy, powergeneration, requires a higher import gas temperature. In this environment, the keycomponents of the gas turbine are needed cooling protection by film coolingtechnology. One important measure parameter of cooling effect in the film cooling isthe adiabatic efficiency.This paper based on Zhejiang Sci-Tech University of the existing experimentalwind tunnel, carries on the transformation and upgrade, sets up a set of successfulexperiment equipment used to observe and measure the film cooling adiabaticeffectiveness. With flat film cooling as the research key, blowing ratio, jet angle as theresearch object, and research the simple circular hole, the compound angle of circularhole, the antivortex hole, acquiring related experimental data and analysis the data.Numerical simulation as the model of the inserted row circular hole according to theactual situation, compare the experimental results with the numerical calculationresults.Research results mainly include:(1) in the case of single row cylindrical holes ofjets, jet blow ratio at M=0.5has the best adiabatic efficiency, blow ratio increase willlead to the reduction of the adiabatic efficiency, and also it will lead to decrease theeffective coverage area of the film cooling (2)the adiabatic efficiency of single-rowcylindrical holes is better than single one, the best adiabatic efficiency of single-rowis at blow ratio M=0.5, the increase of blow ratio will reduce the adiabatic efficiency.There is film cooling dead area in the near field between the exits of holes.(3) in thecase of the cylinder holes with compound angle, it has a good performance inreduction of film cooling dead area.β=15°,60°,it has the best coolingeffectiveness as M=0.5. β=90°,it is the best of the three, and while the blow ratioM=1.0,it has the better cooling efficiency.(4) both of the two rows cylinderholes,their cooling efficiency are better, both of their effectiveness are increased withthe blow ratio increase and the adiabatic efficiency of the inserted row is also better than the alignments.(5) The numerical analysis the inserted row jet experimentsverify that although there are some differences between the experimental andnumerical, but overall the experimental results and the numerical results are basicallyconsistent, and it proves that the experimental study of the model is successful.(6)under the situation of big blow ratio, at the middle and far filled of main flow theadiabatic efficiency is good, but the adiabatic efficiency of anti-vortex is not high asexpected, the reason is that the position and angle of the sub-hole is not good, andsub-hole’s flow is not sufficient.This research project was supported by Zhenjiang Natural Science Foundation(grant no.Y1090869) and Science and Technology Department of Zhejiang Province(grant no.2012C21052). |
