Study of Sweep and Induced Dihedral Effects in Subsonic Axial Flow Compressor Passages—Part II: Detailed Study of the Effects on Tip Leakage Phenomena
P. V. Ramakrishna,M. Govardhan +1 more
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In this article, a detailed study of rotor tip leakage related phenomena in a low speed axial compressor rotor passages for three sweep configurations [Unswept (UNS), tip chordline swept (TCS), and axially swept (AXS)] is presented.Abstract:
This article presents the detailed study of rotor tip leakage related phenomena in a low speed axial compressor rotor passages for three sweep configurations [Unswept (UNS), Tip Chordline Swept (TCS) and Axially Swept (AXS)]. Fifteen domains are numerically studied with 5 sweep configurations (0°, 20° TCS, 30° TCS, 20° AXS, and 30° AXS) and for 3 tip clearances (0.0%, 0.7% and 2.7% of the blade chord). Results were well validated with experimental data. Observations near the tip reveal that UNS rotor shows high sensitivity than the swept rotors in the blade pressure distribution with change in tip clearance. AXS rotor has high loading capability and less tip clearance effect on blade loading at the near stall mass flow. Downstream shift of the vortex rollup along the chord is observed with increased flow coefficient and increment in the tip gap height. In particular, the effect of flow coefficient is more predominant on this effect. Tip vortex-related flow blockage is less with the swept rotors. Among the rotors, the AXS rotor is found to incur low total pressure losses attributable to tip leakage. Effect of incidence is observed on the flow leakage direction.read more
Citations
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Casing Treatment for Desensitization of Compressor Performance and Stability to Tip Clearance
Mert Cevik,Huu Duc Vo,Hong Yu +2 more
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Desensitization of Axial Compressor Performance and Stability to Tip Clearance size
Engin Erler,Huu Duc Vo,Hong Yu +2 more
TL;DR: In this article, the authors identify and elucidate fundamental flow features associated with the desensitization of performance and aerodynamic stability of an axial compressor rotor to tip clearance change.
Axial compressor blade design for desensitization of aerodynamic performance and stability to tip clearance
TL;DR: In this paper, the authors propose an approach to augment the performance of a single rotor of a Jeu-D-Aube by adding a turbine to the axial axial conventionnel of the rotor.
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Influence of Dihedral Stacking on The Performance of An Axial Fan
Ayhan Nazmi Ilikan,Erkan Ayder +1 more
TL;DR: In this article, the effect of positive dihedral (lean) on the aerodynamic performance of a low speed axial fan is presented. And the performance of both fans are investigated by means of ANSYS CFX commercial CFD software and are validated by experiments.
References
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Journal ArticleDOI
Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor
TL;DR: In this article, the role of the passage shock/leakage vortex interaction in generating endwall blockage is discussed, as a result of the shock/vortex interaction at design speed, the radial influence of the tip clearance flow extends to 20 times the physical tip clearance height.
Journal ArticleDOI
A Criterion for Axial Compressor Hub-Corner Stall
TL;DR: In this article, the authors present a new criterion for estimating the onset of three-dimensional hub-corner stall in axial compressor rotors and shrouded stators, which is based on the Zweifel loading coefficient.
Journal ArticleDOI
The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading—Part I: University Research and Methods Development
Simon John Gallimore,John J. Bolger,Nicholas Cumpsty,Mark J. Taylor,Peter I. Wright,J. M. M. Place +5 more
TL;DR: In this article, the introduction of 3D blade designs into the core compressors for the Rolls-Royce Trent engine with particular emphasis on the use of sweep and dihedral in the rotor designs is described.
Journal ArticleDOI
An Approximate Analysis and Prediction Method for Tip Clearance Loss in Axial Compressors
J. A. Storer,N. A. Cumpsty +1 more
TL;DR: In this paper, a simple model for loss created by the tip clearance flow in axial compressors is presented, based on an experimental program performed in conjunction with the Dawes three-dimensional Navier-Stokes calculation method.