Douaissia O. Improvement of the mathematical model of the working process in the oil cavity of the rotor support of the aircraft gas-turbine engine

Object – working process in aircraft GTE rotor support oil cavity; goal – to improve the math model of working process in aircraft GTE rotor support oil cavity by reasonable choice of boundary conditions and heterogeneous flow structure, which allows in process of rotor support development to define the influence of geometric and operation parameters on oil distribution and heat transfer coefficient near chamber walls forms an oil cavity; methods – methods of thermohydraulic processes modeling, theory of differential and integral calculus, multiphase media mechanics, theory of similarity and heat-mass transfer; results – the math model of working process in rotor support oil cavity was improved and 3D CFD-model was developed, which allowed to define the influence of operation parameters, disperse phase size and gravity on phase distribution and heat transfer in the oil cavity and to check the validity of the Busam’s correlation; novelty – the math model of the thermohydraulic processes in aviation gas turbine engine rotor support oil cavity was improved by the justified choice of boundary conditions and heterogeneous flow structure and this approach dissemination to near-wall flow area, which allows, in process of engine’s rotor support development, to define the influence of geometric and operation parameters on oil distribution and heat transfer coefficient in the oil cavity without specifying of additional conditions associated with drop-air flow and oil film interaction in near-wall area, for the first time, based on the simulation results it was defined the influence of boundary conditions – disperse phase size on phase distribution and heat transfer in gas-turbine engine’s rotor support oil cavity, which is shown in wall layer thermal resistance on chamber surface of oil cavity changing, which allows to improve the accuracy of heat transfer coefficient determination, for the first time, based on the results of thermohydraulic processes simulation, a significant influence of gravity on oil circumference distribution in near-wall area of rotor support oil cavity has been revealed, which leads to asymmetric distribution of heat transfer coefficient and justifies the necessity to use a three-dimensional model of oil cavity for thermohydraulic processes analysis; the degree of implementation –implemented in JSC «Motor Sich», SE «Progress» and in educational process of National Aerospace University Kharkiv Aviation Institute; industry – propulsion engineering.