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Tip clearance

About: Tip clearance is a research topic. Over the lifetime, 2637 publications have been published within this topic receiving 32671 citations.


Papers
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Proceedings ArticleDOI
13 Jun 1994
TL;DR: In this article, the role of the passage shock/vortex interaction in generating endwall blockage is discussed, and the radial influence of the tip clearance flow extends to 20 times the physical tip clearance height.
Abstract: Experimental and computational techniques are used to investigate tip clearance flows in a transonic axial compressor rotor at design and part speed conditions. Laser anemometer data acquired in the endwall region are presented for operating conditions near peak efficiency and near stall at 100% design speed and at near peak efficiency at 60% design speed. 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. At part speed, in the absence of the shock, the radial extent is only 5 times the tip clearance height. Both measurements and analysis indicate that under part-speed operating conditions a second vortex, which does not originate from the tip leakage flow, forms in the endwall region within the blade passage and exits the passage near midpitch. Mixing of the leakage vortex with the primary flow downstream of the rotor at both design and part speed conditions is also discussed.Copyright © 1994 by ASME

60 citations

Journal ArticleDOI
TL;DR: In this article, a complete review of the most recent advances in the field of aerodynamic design and operation of transonic axial flow compressors is given, highlighting the most relevant contribution in this field and to suggest the prospects for future developments.

60 citations

Journal ArticleDOI
Yabin Liu1, Lei Tan1
15 Jul 2018-Energy
TL;DR: In this paper, a C groove method is proposed to suppress the tip leakage vortex (TLV) and improve the energy performance of a NACA0009 hydrofoil in tidal energy conversion, and numerical approach with mesh generation and Navior-Stokes equation solution is employed to evaluate the effect of C groove.

60 citations

Patent
05 Jun 2003
TL;DR: In this article, a passive clearance control system for a gas turbine engine component is proposed, which provides a blade shroud that is isolated from the component case and can move radially to maintain blade clearance.
Abstract: A passive clearance control system for a gas turbine engine component. The system provides a blade shroud that is isolated from the component case and can move radially to maintain blade clearance. A plurality of vane sectors define a stator ring including a blade shroud. The stator ring and the control ring are coupled together and mounted within the component by a plurality of radial extending mounting members.

60 citations

Journal ArticleDOI
TL;DR: An experimental and numerical investigation of detailed tip clearance flow structures and their effects on the aerodynamic performance of a modern low-aspect-ratio, high-throughflow, axial transonic fan is presented in this article.
Abstract: An experimental and numerical investigation of detailed tip clearance flow structures and their effects on the aerodynamic performance of a modern low-aspect-ratio, high-throughflow, axial transonic fan is presented. Rotor flow fields were investigated at two clearance levels experimentally, at tip clearance to tip blade chord ratios of 0.27 and 1.87 percent, and at four clearance levels numerically, at ratios of zero, 0.27, 1.0, and 1.87 percent. The numerical method seems to calculate the rotor aerodynamics well, with some disagreement in loss calculation, which might be improved with improved turbulence modeling and a further refined grid. Both the experimental and the numerical results indicate that the performance of this class of rotors is dominated by the tip clearance flows. Rotor efficiency drops six points when the tip clearance is increased from 0.27 to 1.87 percent, and flow range decreases about 30 percent. No optimum clearance size for the present rotor was indicated. Most of the efficiency change occurs near the tip section, with the interaction between the tip clearance flow and the passage shock becoming much stronger when the tip clearance is increased. In all cases, the shock structure was three dimensional and swept, with the shock becoming normal to themore » endwall near the shroud.« less

60 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202354
2022149
202189
2020111
2019116
201897