SURROGATE MODELING TO OPTIMIZE THE WORKING PROCESS IN THE TURBINE STAGE

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 effi ciency of its stage by adjusting the circumferential position of injectors at the combustion chamber outlet and adding a swirl of gas fl ow inside them. It has been shown that in the absence of fl ow swirl in the interblade channel, adjusting the location of the heat spot relative to the inlet to this channel exerts diff erently directed eff ects on the turbine effi ciency and temperature separation in it. When the fl ow swirls in the heat spot, unidirectional improvement in the aerodynamic and thermal characteristics of the turbine fl ow does not occur. In this case, the decrease of the turbine effi ciency (relative to the case of uniform temperature fi elds and gas fl ow 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 specifi ed number of Pareto-optimal solutions for the turbine effi ciency and temperature separation in it.
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 effi ciency of its stage by adjusting the circumferential position of injectors at the combustion chamber outlet and adding a swirl of gas fl ow inside them. It has been shown that in the absence of fl ow swirl in the interblade channel, adjusting the location of the heat spot relative to the inlet to this channel exerts diff erently directed eff ects on the turbine effi ciency and temperature separation in it. When the fl ow swirls in the heat spot, unidirectional improvement in the aerodynamic and thermal characteristics of the turbine fl ow does not occur. In this case, the decrease of the turbine effi ciency (relative to the case of uniform temperature fi elds and gas fl ow 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 specifi ed number of Pareto-optimal solutions for the turbine effi ciency and temperature separation in it.
Author:  D. K. Popova, N. N. Kortikov
Keywords:  rotor–stator interaction, fl ow swirl, combustion chamber, temperature separation, clocking eff ect, turbine stage, IOSO technology, multicriteria optimization
Page:  73