Abstract
The paper aims to develop adequate means to measure the effectiveness of cooling technology of turbine blades. The used methodologies are the mathematical modeling of movement and heat transfer in the boundary layer of the working medium near the curved surface of the turbine blade and also using empirical data on the critical flow regimes. The mathematical model of film cooling of turbine engine blades under film formation on the punched surface with blind damping cavities is offered. On the basis of numerical research with the use of the offered model the option for essential (providing in analyzed conditions decrease in adiabatic temperature of a wall on 200 K) increase in efficiency of film cooling at the expense of a partial laminarization of a turbulent interface on the punched surface is revealed.
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