Abstract
An intricate nature of the pattern in which working fluid flows over transonic blade cascades generates the need for experimentally studying their characteristics in designing them. Three cascades having identical main geometrical parameters and differing from one another only in the suction side curvature in the outlet area between the throat and trailing edge were tested in optimizing the rotor blade cascade for the reduced flow outlet velocity λ2 ≈ 1. In initial cascade 1, its curvature decreased monotonically toward the trailing edge. In cascade 2, the suction side curvature near the trailing edge was decreased, but the section near the throat had a larger curvature. In cascade 3, a profile with inverse concavity near the trailing edge was used. The cascades were blown at λ2 = 0.7–1.2 and at different incidence angles. The distribution of pressure over the profiles, profile losses, and the outlet angle were measured. Cascade 1 showed efficient performance in the design mode and under the conditions of noticeable deviations from it with respect to the values of λ2 and incidence angle. In cascade 2, flow separation zones were observed at the trailing edge, as well as an increased level of losses. Cascade 3 was found to be the best one: it had reduced positive pressure gradients as compared with cascade 1, and the relative reduction of losses in the design mode was equal to 24%. The profiles with inverse concavity on the suction side near the trailing edge were recommended for being used in heavily loaded turbine stages.
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References
M. E. Deich, Gas Dynamics of Turbine Machinery Blade Cascades (Energoatomizdat, Moscow, 1996) [in Russian].
V. Kh. Abiants, A Theory of Jet Engine Gas Turbines (Mashinostroenie, Moscow, 1979) [in Russian].
B. M. Aronov, M. I. Zhukovskii, and V. A. Zhuravlev, Designing the Profiles of Aircraft Turbine Blades (Mashinostroenie, Moscow, 1978) [in Russian].
E. A. Gukasova, M. I. Zhukovskii, A. M. Zavadovskii, L. M. Zysina-Molozhen, N. A. Sknar’, and V. G. Tyryshkin, Aerodynamic perfection of the steam and gas turbine blade systems (Gosenergoizdat, Moscow, Lemingrad, 1960) [in Russian].
B. I. Mamaev and E. K. Ryabov, “Designing the turbine blade cascade profiles using the dominating curvature method,” Therm. Eng. 26(2) (1979).
B. I. Mamaev, “On selecting the blade profile suction side curvature in the turbine transonic cascade,” Izv. Vyssh. Uchebn. Zaved., Aviats. Tekhn., No. 2, 29–32 (2011).
A. B. Bogod, A. V. Granovskii, and A. M. Karelin, “Achieving better accuracy and shorter computation time in numerically studying the flows in turbine machinery blade cascades,” Therm. Eng. 33(8) (1986).
M. E. Deich and B. M. Troyanovskii, Investigations and Calculations of Axial Turbine Stages (Mashinostroenie, Moscow, 1964) [in Russian].
M. E. Deich, A. V. Gubarev, L. Ya. Lazarev, and A. Jachanmohan, “New nozzle vane cascades for ultrasonic velocities developed at the Moscow Power Engineering Institute,” Teploenergetika, No. 10, 41–52 (1962).
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Original Russian Text © E.V. Mayorskiy, B.I. Mamaev, 2015, published in Teploenergetika.
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Mayorskiy, E.V., Mamaev, B.I. Aerodynamic development and investigation of turbine transonic rotor blade cascades. Therm. Eng. 62, 329–334 (2015). https://doi.org/10.1134/S0040601515050080
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DOI: https://doi.org/10.1134/S0040601515050080