| Gas turbine is a high-precision power plant that is widely used in industrial fields.With the development of science technology and industry,higher performance and thermal efficiency of gas turbine are requested.higher cycle thermal efficiency is accompanied by higher pre-turbine temperatures.Gas turbine cooling technology has become the main measure to solve the increasing inlet temperature of the turbine,which is becoming higher and higher than the allowable temperature of the material.Film cooling is an extremely important part of gas turbine cooling technology.In this paper,after the numerical calculation of several common film holes,the positive and negative effects of flow field and heat transfer characteristics on the film cooling caused by their structure are analyzed and summarized.With the summary of the hole-shaped structure that is beneficial to film cooling,A shaped hole of double jet is established,the flow field and film cooling performance of which were analyzed.In this paper,an original scheme for the front chamber of a high pressure aviation turbine guide vane is obtained by modeling,which has been optimized.In the optimization process,the design law of gas film cooling design for gas turbine vanes is summarized,that is,“from the leading edge to the trailing edge,jets from holes complement each other,design in adiabatic conditions,verify in conjugate heat transfer simulation”.The design of the film cooling scheme is sequentially carried out along the leading edge to the trailing edge.By considering the cooperation between rows of cooling holes,a better film cooling jet coverage and cooling efficiency are obtained.At the same time,the strength of the guide vanes was analyzed,and the low stress design was carried out on some high stress areas.The original design of turbine rotor cool structure is all cross rib,and several high temperature regions exist in the leading edge and the tip region.In this paper,the leading edge and tip cooling structures of the turbine rotor are optimized.By analyzing and comparing several optimization schemes,The appropriate scheme was selected,reducing the maximum surface temperature of the rotor and the area of high temperature region.In view of the fact that some high-temperature regions still exist in the suction side of the designed turbine guide vanes,the double jet shaped-holes are applied to a gas turbine guide vane,which has been compared with circular hole as inclined holes of suction side in the adiabatic and conjugate heat transfer conditions.It was found that the double jet shaped-hole can effectively improve the cooling effect of the suction side while being applied as the inclined hole to the suction surface. |
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