naa a22 4500 510765866 CHVBK 20180411083156.0 cr unu---uuuuu 180411e20131201xx s 000 0 eng 10.1007/s11630-013-0667-1 doi (NATIONALLICENCE)springer-10.1007/s11630-013-0667-1 Experimental investigation of effects of distributed riblets on aerodynamic performance of a low-speed compressor [Elektronische Daten] [Hongwei Ma, Wei Wei] It is well known that riblet applied on compressor blades is a promising flow control technique. However, detailed investigation of its effects on the flow field of turbomachinery is rare in existing literatures. This paper presents a detailed experimental investigation of effects of distributed riblet on the flow field of an axial compressor isolated-rotor stage. The research was performed in a large-scale facility respectively with two configurations, including grooved hub, and grooved surface on both hub and partial suction surface. The riblet film is rectangle grooved type with a height of 0.1 mm. The flow field at 10% chord downstream from the cascade trailing edge was measured using a mini five-hole pressure probe and a total pressure probe. The testing was conducted at several operational points under two reduced rotational speeds. Stagnation pressure loss in rotational frame was calculated and compared with the control test in which a smooth film was applied to the corresponding position. Results show that with the grooved hub configuration at the design operation point of the lower rotational speed, the riblet film provides an obvious improvement of a 48% reduction of total pressure loss in rotational frame. Also, a distinct weaken hub corner vortex was identified. In the meantime, there exists a deviation of flow angle about 5 degrees at 20%-80% span which previously was not considered to be the affected region. Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag Berlin Heidelberg, 2013 distributed riblet nationallicence large-scale compressor nationallicence hub corner vortex nationallicence loss reduction nationallicence Ma Hongwei National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, 100191, Beijing, China aut Wei Wei National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, 100191, Beijing, China aut Journal of Thermal Science Springer Berlin Heidelberg 22/6(2013-12-01), 592-599 1003-2169 22:6<592 2013 22 11630 https://doi.org/10.1007/s11630-013-0667-1 text/html Onlinezugriff via DOI 1 research-article jats NATIONALLICENCE 856 40 https://doi.org/10.1007/s11630-013-0667-1 text/html Onlinezugriff via DOI NATIONALLICENCE 700 1- Ma Hongwei National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, 100191, Beijing, China aut NATIONALLICENCE 700 1- Wei Wei National Key Laboratory of Science and Technology on Aero-Engines, School of Energy and Power Engineering, Beihang University, 100191, Beijing, China aut NATIONALLICENCE 773 0- Journal of Thermal Science Springer Berlin Heidelberg 22/6(2013-12-01), 592-599 1003-2169 22:6<592 2013 22 11630 Metadata rights reserved Springer special CC-BY-NC licence nationallicence BK010053 XK010053 XK010000 NATIONALLICENCE NATIONALLICENCE NL-springer