The results of the numerical analysis of the flow capacity and other parameters at the different turbine vanes are presented in this paper. Two plane cascades with the same geometrical throat but with a different shape of suction surface have been investigated by means of the 2D Navier-Stokes code [1]. Stacked with these profiles two vane rows with tip meridional opening have been investigated by means of the 3D Euler code [2] and the 3D Navier-Stokes code [3]. The numerical investigation of two full-scale annular vane rows is confirmed by experimental mass flow performance, obtained in a range of exit isentropic Mach number on the mean diameter from Ma2 is = 0.7 to Ma2 is = 1.3.

The paper presents the detail investigation of temperature field evolution through multistage cooled turbines. An investigation bases on simple enough numerical simulation and allows for transient, heat transfer, viscous and some other important effects on temperature field transformation. Herewith the special test data for a number of cooled turbines are used. The developed numerical code has the following peculiarities: - a time-marching method for the unsteady Euler equation system; - a special algorithm of flow parameters averaging in mixing planes in the middle of axial gaps; - a monotone implicit scheme of second or third order accuracy in space and time. The code has been used for a numerical study of the flow pattern in a number of multistage aviation and industrial turbines. The described simulation demonstrates satisfactory correlation between the numerical and experimental data for temperature gradient attenuation in the flowpath of investigated cooled turbines.

This paper presents results of a complex numerical and experimental investigation of the flow structure and losses in the Vane (Ma2is = 1.0, Re = 9.8*105) and Blade (Ma2is = 1.12, Re = 7.8*105) straight cascades on transonic modes. The measurements of turbulence pulsation and mean flow velocity upstream, within and downstream of the cascades were made by means of laser anemometer (LA). The static and total pressure fields were measured upstream and downstream of the cascades to determine profile losses. The static pressure distribution on the suction and pressure surfaces was measured as well. Comparisons were made with predictions using 2D Navier–Stokes analysis. The use of the both experimental and numerical approaches allowed to eliminate separated zones more accurately, to define how these zones affected on flow structure and losses.

The paper presents the detailed investigation of the flow structure and losses in a hub and tip sections of the last blade of the multistage turbine. The design of the last blade has been carried out on the basis of the in-house blade generator (BLAGEN) which allows to create optimal plane sections (usually 3–5) along blade height and to stack whole blades of various 3D shapes. The viscous flow structure and the loss variation have been investigated at the endwall sections of the last blade by means of 2D and 3D Navier–Stokes codes. These investigations have been carried out for a wide range of modes and incidences. As a result the influence of the following parameters (maximum thickness-to-chord ratio, leading metal angle, Re number, exit Ma number and etc.) on the flow structure and losses has been investigated. On the basis of these investigations some recommendations for the last blades design have been developed. Numerical investigations have been validated by the comparison between numerical and test data for the outlet flow.

The results of numerical analysis of turbine flow capacity and other parameters at different turbine rows are presented in this paper. Mass flow calculations by 3D Euler code has been controlled by means of 3D Navier-Stokes code taking into account inlet turbulence intensity and turbulence scale. The use of complicated numerical approaches (3D Euler or 3D Navier-Stokes codes) for mass flow definition demands close attention to quality of numerical techniques. Various reasons of inaccuracy of mass flow definition by using different 3D numerical approaches are analyzed.