Aerodynamic test of fixed-geometry and adjustable additional blades in axial-flow compressor stage

• Autorzy: Nezym V
• Języki publikacji: EN

Abstrakty

EN

An application of a flow control equipment in a compressor has been found to give a substantial improvement in the compressor stable operational range. The experimental investigation has been performed with additional blades (of a fixed-geometry and adjustable types) in an axialflow compressor stage. The fixed-geometry type additional blades were installed in the blade-toblade duct of a rotor hub and in hub and tip zones of a guide vane. Total pressure diagrams for the stage embodiments (with and without the fixed-geometry additional blades) are presented. The adjustable tip additional blades were tested in two configurations, along the full length of the rotor blade chord projection, and located only in the inlet part of the rotor blade. This experimental investigation revealed a special importance of the inlet rotor part in rotating stall occurring.

Słowa kluczowe

EN

compressor; performance; rotating stall; additional blades

• Wydawca: Wydawnictwo Instytutu Maszyn Przepływowych PAN
• Czasopismo: Transactions of the Institute of Fluid-Flow Machinery
• Rocznik: 2016
• Tom: nr 132
• Strony: 17--28
• Opis fizyczny: Bibliogr. 11 poz., rys.

Twórcy

autor

Nezym V

• National Aerospace University ‘Kharkov Aviation Institute’,Chkalova 17, Kharkov, 61070, Ukraine

Bibliografia

• [1] Koch C.C., Smith L.H.Jr.: Loss sources and magnitudes in axial-flow compressors. In: ASME Paper 75-Wa/GT-6 (1975), 14.
• [2] Bammert K., Beelte. H.: Investigation of an axial compressor with tandem cascades. J. Eng. Power, Trans. ASME 102(1980), 4, 971–977.
• [3] Wu C.H., Zhuang B., Guo B.: Experimental investigation of tandem blade cascades UIT double-circular arc profiles. ASME Paper 85-GT-94 (1985), 7.
• [4] Nezym V.Yu., Gomez-Mancilla J., Korkishko S.V.: Statistical model for turning angle determination of compressor tandem cascade. Proc. ISROMAC-10 (2004), 6.
• [5] Greitzer E.M., Nikkanen J.P., Haddad D.E., Mazzawy R.S., Joslin H.D.: A fundamental criterion for the application of rotor casing treatment. J. Fluids Eng., Trans. ASME 101(1979), 1, 237–243.
• [6] Smith G.D. Jr., Cumpsty N.A.: Flow phenomena in compressor casing treatment. J. Eng. Gas Turb. Power, Trans. ASME 106(1984), 3, 532–541.
• [7] Fujita H., Takata H.: A study on configurations of casing treatment for axial flow compressors. JSME Bull. 230(1984), 27, 1675–1681.
• [8] Bae J., Breuer K.S., Tan C.S.: Control of tip clearance flows in axial compressors. Proc. AIAA Fluids 2000 Conference & Exhibit (2000), 1–11.
• [9] Nezym V.Yu.: Parametric investigation of casing treatment influence on compressor stable operation. Exp. Therm. Fluid Sci. 29(2004), 2, 209–215.
• [10] Nezym V.Yu.: A statistical model for the effect of casing treatment recess on compressor rotor performance. Exp. Therm. Fluid Sci. 31(2007), 1, 203–214.
• [11] Honda J. et al.: Axial fan. United States Patent, 4152094 (1979), 13

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę.