Dependence of Thermodynamic Parameters of the Cooling Air Flow on the Profile Attack Angle in the Preliminary Swirl Apparatus
Authors: Samoylov A.V., Siluyanova M.V.
Published in issue: #3(171)/2026
Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts
The article is devoted to the influence of the pre-swirl vane (PWV) angle of attack on the thermodynamic parameters of the cooling-air flow in the high-pressure turbine cooling system of a two-spool gas-turbine engine. A mathematical model of compressible viscous air flow was proposed, based on the solution of Reynolds-averaged Navier–Stokes (RANS) equations, closed by a two-parameter turbulence model SST k–ω, which provides high calculation accuracy both in the wall-boundary region and in the flow core. The momentum and energy conservation equations are written in a cylindrical coordinate system with account for rotation of structural elements and dissipative processes. Special attention was paid to the correct specification of boundary conditions at the PWV inlet (total pressure 1.2 MPa, temperature 700 K, axial velocity 100 m s–¹, tangential velocity 35 m s–¹, turbulence intensity 3%) and at its exit. The model is verified by comparison with experimental data and ANSYS CFX computations. A parametric study yields quantitative correlations between the swirl angle, total-pressure-loss coefficient, exit temperature, flow velocity and turbulence intensity and the vane angle of attack in the 10–35° range. It is shown that increasing the angle beyond 30° slows the growth of swirl and raises dissipative losses due to intensified separation on the vane suction side. An optimum angle-of-attack range of 20–25° is identified that balances swirl effectiveness and hydraulic losses. Empirical correlations suitable for engineering design are proposed. The results can be used in the design and optimization of cooling systems for advanced aero-engines.
EDN NBNNIW
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