Effective reduction of temperature unevenness in turbine shell blades

Aim . Reduction of temperature unevenness in a shell-type turbine blade under conditions of heat supply and removal. Methodology . The mathematical formulation of the problem of reducing the temperature unevenness of the shell using a system of curved heat sink channels is carried out. The mathematical model was constructed using the condition of continuity of the cooling flow in the channel, data on the source of thermal stress, boundary conditions at the entrance and exit to the cooling channel, restrictions on the height of the channels using interpolation polynomials. Results . The variable height and trajectories of the heat sink channels are calculated for a given uneven temperature field, allowing to intensify cooling in the most thermally loaded area of the shell. Research implications . The theoretical and practical significance lies in the possibility of using the proposed model to develop a deflector shape with curved channels for blades of a gas turbine engine with an internal cooling system.