Proceedings Article10.1115/GT2020-15940
Influence of Boundary Layer Skew on the Tip Leakage Vortex of an Axial Compressor Stator
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TL;DR: In this article, a single axial compressor stator row with varying tip gap height (tip gap height/chord length = 2.0%|5.4%|6.7%) was investigated and the results showed that the boundary layer skew has a major influence on the trajectory and size of the tip leakage vortex.
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Abstract: \n For an axial compressor stator with tip gap the boundary layer in the hub end-wall region has a significant influence on the development and progression of the tip leakage vortex. Herein the so-called boundary layer skew, which develops through relative motion of the hub, is of particular interest. Therefore, experimental and numerical investigations of a single axial compressor stator row with varying tip gap height (tip gap height/chord length = 2.0%|5.4%|6.7%) have been conducted. Comparing cases with rotating or stationary hub end-wall segments upstream of the examined vanes allowed to determine the effect of skewed and un-skewed inflow boundary layer. The steady state flow fields up- and downstream of the stator row were measured using five-hole pressure probes. For validation and to improve the understanding of the existing flow phenomena 3D-RANS CFD simulations using a commercial flow solver were carried out. Furthermore, analog cases with no tip gap were examined and considered in the comparisons to extend the knowledge on this boundary layer characteristic. The results show that the boundary layer skew has a major influence on the trajectory and size of the tip leakage vortex for the cases with tip clearance. The effect of reduction of the produced losses decreases with increasing tip gap height.
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Citations
Interaction mechanism between incoming vortex and tip leakage vortex breakdown of a compressor cascade
Zhiyuan Cao,Xi Gao,Jingzhen Yang,Chuxuan Wang,Bo Liu +4 more
TL;DR: The interaction mechanism between incoming vortex and tip leakage vortex breakdown of a compressor cascade is investigated. TVB can be completely removed by the incoming vortex near the suction surface. The flow mechanism is that the interaction between the incoming vortex and tip leakage vortex (TLV) can increase the chordwise momentum at the vortex core and the stability of the TLV.
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Near-Wall Flow in Turbomachinery Cascades—Results of a German Collaborative Project
David Engelmann,Martin Sinkwitz,Francesca di Mare,Björn Koppe,Ronald Mailach,Jordi Ventosa-Molina,Jochen Fröhlich,Tobias Schubert,Reinhard Niehuis +8 more
- 08 May 2021
TL;DR: This article provides a summarizing account of the results obtained in the current collaborative work of four research institutes concerning near-wall flow in turbomachinery, providing a broad picture of the underlying phenomena, ranging from compressors to turbines, from isothermal to non-adiabatic, and from incompressible to compressible flows.
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Cantilevered Tandem Stator in Annular High Speed Test Rig
Roland Rückert,Dieter Peitsch +1 more
TL;DR: In this article , the aerodynamic performance of a cantilevered tandem stator was investigated in a high speed annular test rig at the Technische Universitaet Berlin, where the turning of incoming flow was split up between two blades arranged in succession.
References
Loss Reduction in Axial-Flow Compressors Through Low-Speed Model Testing
TL;DR: In this article, a large, low-speed, aerodynamic model of a high-speed core compressor is designed and fabricated based on aerodynamic similarity principles, and the model is then tested at low speed where high-loss regions associated with three-dimensional endwall boundary layers flow separation, leakage, and secondary flows can be located, detailed measurements made, and loss mechanisms determined with much greater accuracy and much lower cost and risk than is possible in small, high speed compressors.
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Behavior of Tip Leakage Flow Behind an Axial Compressor Rotor
TL;DR: In this article, the effect of tip clearance on axial compressor rotor performance was investigated on the overall performance, work-done factor, blockage factor, and increases in displacement, momentum, and blade-force-deficit thicknesses of the casing wall boundary layer.
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Untersuchungen über den Einfluß der Zuströmgrenzschicht auf die Sekundärströmungen in den Beschaufelungen von Axialturbinen
TL;DR: In this paper, the Einflus verwundener Zustromgrenzschichten auf die Sekundarstromungen an den Schaufelenden unter besonderer Berucksichtigung der Rand-und der Spaltverluste klaren.
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An Experimental Verification of a New Design for Cantilevered Stators With Large Hub Clearances
TL;DR: In this article, a new three-dimensional design for cantilevered stators in axial compressors is presented, with the aim of improving the overall efficiency and losses of rear stage vanes with large relative hub clearances.
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