Aerodynamic Performance Prediction of Highly Loaded Single-Stage Axial-Flow Low-Speed Compressor

• Autorzy: Polansky J. , Cyrus V. , Lavicka D.
• Języki publikacji: EN

Abstrakty

EN

Aerodynamic performance of highly loaded low-speed axial-flow compressor stage was computed by means of commercial code Fluent. The computed data were compared with experimental results obtained in test stage with external diameter of 600 mm. At design condition one could observe reasonable agreement. The difference between theoretical and measured characteristics increased with the growing distance of stage working point from design point. This conclusion is supported by the comparison of experimental and computed rotor and stator blade elements performance at three typical working conditions.

Słowa kluczowe

EN

compressor; rotor; stator blade

PL

stojan ostrza; sprężarka; wirnik

• Wydawca: Wydawnictwo Politechniki Łódzkiej
• Czasopismo: Zeszyty Naukowe. Cieplne Maszyny Przepływowe - Turbomachinery / Politechnika Łódzka
• Rocznik: 2005
• Tom: nr 128, vol. 2
• Strony: 419--426
• Opis fizyczny: Bibliogr. 5 poz.

Twórcy

autor

Polansky J.

• ZČU Plzeň

autor

Cyrus V.

• AHT Energetika Ltd, Praha

autor

Lavicka D.

• ZČU Plzeň

Bibliografia

• [1] Gallimore, S. J., Bolger, J. J., Cumpsty N. A., Taylor, M. J., Wright P. I. and Place, J. M. “The use of sweep and dihedral in multistage axial flow compressor blading”. Part I: University research and methods of development. ASME Paper No. GT-2002-30328, 2002
• [2] Clemen, C., Stark,U., Fridrics,J., Baumgarten,S. and Kosyna, G.. “Effect of mean line shape, sweep and dihedral on stator performance of a highly loaded single-stage axil-flow low-speed compressor”. Proceedings of 6th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics, pp.34 – 45, Lille, March 2005
• [3] Cyrus V.: “Design of axial flow fans with high aerodynamic loading. Forschung im Ingenieuerwesen” – Engineering Research Bd.62 (1996), Nr.3, S.58 – 64.
• [4] Cyrus,V.: “Aerodynamic performance of an axial compressor stage with variable rotor blades and variable inlet guide vanes”. ASME Paper No. 98-GT-151, Stockholm 1998
• [5] Lieblein S.: “Experimental flow in two-dimensional cascades”. NASA SP 36, pp.183