Abstract
The results of numerical simulation of film cooling of the turbine rotor blade with the flow of coolant to the area of the leading edge through three rows of cylindrical holes. To determine the effect of surface curvature on film cooling effectiveness, and a comparison of results obtained with the results of simulation modeling of flow of a plate with film cooling at the inlet cylindrical region. The studies were conducted at the magnitude of the blowing ration of 0.5 to 2.0. Dimensions calculation model and input data received characteristic of the high pressure turbine blades of high-temperature gas turbine engine. Modelling performed using software package ANSYS CFX. The result obtained by calculations that the presence of the cylindrical profiled surfaces instead of flat surface leads to a significant decrease in the average film cooling effectiveness, both cylindrical and the concave surfaces in the investigated range blowing ration values. For all blowing ration film cooling effectiveness parameter values on the suction side is much higher than the pressure side. At the same time, the average efficiency of the film cooling on the suction side when m < 1.5 is higher than on a plot of flat wall, and when m > 1.5 marginally below. Application dependencies obtained on models with flat walls, for the calculation of the film cooling efficiency of suction side and pressure side of the blades is only possible with such amendments as may be determined by the results of this work.
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