<p>Based on the URANS approach, a numerical model has been developed for controlling temperature separation on the working turbine blades of an aircraft engine and the efficiency of its stage by adjusting the circumferential position of injectors at the combustion chamber outlet and adding a swirl of gas flow inside them. It has been shown that in the absence of flow swirl in the interblade channel, adjusting the location of the heat spot relative to the inlet to this channel exerts differently directed effects on the turbine efficiency and temperature separation in it. When the flow swirls in the heat spot, unidirectional improvement in the aerodynamic and thermal characteristics of the turbine flow does not occur. In this case, the decrease of the turbine efficiency (relative to the case of uniform temperature fields and gas flow velocity) is in the range from 0.19 to 1.08%. A surrogate model based on the IOSO software package is proposed, which is used to optimize the working process in the turbine stage of an aircraft engine in a multicriteria formulation, which allows obtaining a specified number of Pareto-optimal solutions for the turbine efficiency and temperature separation in it.</p>