A compressible three‐dimensional design method for radial and mixed flow turbomachinery blades

Abstract

SUMMARYA fully three-dimensional compressible inverse design method for the design of radial and mixed flow turbomachines is described. In this method the distribution of the circumferentially averaged swirl velocity r vo on the meridional geometry of the impeller is prescribed and the corresponding blade shape is computed iteratively. Two approaches are presented for solving the compressible flow problem. In the approximate approach the pitchwise variation in density is neglected and as a result the algorithm is simple and efficient. In the exact approach the velocities and density are computed throughout the three-dimensional flow field by employing a fast fourier transform in the tangential direction. The results of the approximate and exact approach are compared for the case of a high-speed (subsonic) radial-inflow turbine and it is shown that the difference between the blade shapes computed by the two methods is well within the manufacturing tolerances. The method was validated by calculating the flow through a designed high-speed radial-inflow turbine by using a three-dimensional inviscid Euler solver. Very good correlation was obtained between the specified and computed T V&distributions.

Historical Perspective on Fluid Machinery Flow Optimization in an Industry

“…Zangeneh [9] proposed a 3-D inverse design theory for designing mixed and radial flow fluid machines, where the blade configuration was obtained numerically for a prescribed blade loading distribution. As you may understand in relation with Figs.…”

Advances in Aerodynamic Design of Gas Turbines Compressors

“…In the last two decades, three-dimensional inverse design methods have emerged and been applied successfully for a wide range of designs, involving both radial/mixed flow turbomachinery blades and wings (Zangeneh, 1991;Demeulenaere & Van Den Braembussche, 1996;Dulikravich & Baker, 1999). Quite a new approach to the 3D design of axial compressor bladings has been recently proposed by Tiow, 2002.…”

Low Speed Design of Rear Rotor in Contra-Rotating Axial Flow Pump

“…Since Zangeneh [7] has indicated that the secondary flow could be well controlled with the blade designed as leading edge loaded at tip and trailing edge loaded at hub, the idea of variable maximum camber position is adopted in the new rear rotor RR3 design. Compared to the RR2 with the consistent maximum camber x f /l positioned at 40% to chord length over the whole blade span, the x f /l of RR3 adopts 40% at the tip and smoothly shifts into 60% at the hub.…”