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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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Journal ArticleDOI
TL;DR: In this article, a multi-block, three-dimensional Navier-Stokes code has been used to compute heat transfer coefficient on the blade, hub and shroud for a rotating high-pressure turbine blade with 172 film-cooling holes in eight rows.

44 citations

Journal ArticleDOI
TL;DR: In this article, empirical and semi-empirical relations have been used to evaluate the secondary losses in turbomachines and the nature and extent of tip clearance flow and the associated losses are briefly reviewed.

44 citations

Journal ArticleDOI
TL;DR: In this paper, the predictive performance of a non-linear turbulence closure in simulating the flow physics pertinent to a high-pressure axial ventilation fan is investigated, which is considered as a promising closure for improving industrial CFD by accounting for non-equilibrium effects.

43 citations

Journal ArticleDOI
TL;DR: In this paper, the authors used a surface-streaking visualization method to identify the time-averaged location of this interface as a line of zero axial shear stress at the casing.
Abstract: Experimental and numerical studies were conducted to investigate tip-leakage flow and its relationship to stall in a transonic axial compressor. The computational fluid dynamics (CFD) results were used to identify the existence of an interface between the approach flow and the tip-leakage flow. The experiments used a surface-streaking visualization method to identify the time-averaged location of this interface as a line of zero axial shear stress at the casing. The axial position of this line, denoted x(zs), moved upstream with decreasing flow coefficient in both the experiments and computations. The line was consistently located at the rotor leading edge plane at the stalling flow coefficient, regardless of inflow boundary condition. These results were successfully modeled using a control volume approach that balanced the reverse axial momentum flux of the tip-leakage flow with the momentum flux of the approach fluid. Nonuniform tip clearance measurements demonstrated that movement of the interface upstream of the rotor leading edge plane leads to the generation of short length scale rotating disturbances. Therefore, stall was interpreted as a critical point in the momentum flux balance of the approach flow and the reverse axial momentum flux of the tip-leakage flow.

43 citations

Patent
12 Sep 2003
TL;DR: In this article, a sealing system for reducing a gap between a tip of a shrouded turbine blade and a stationary shroud of a turbine engine is presented. But the sealing system is not suitable for the case of a single turbine blade.
Abstract: A sealing system for reducing a gap between a tip of a shrouded turbine blade and a stationary shroud of a turbine engine. The sealing system includes one or more seal lands extending from a shrouded turbine blade toward a stationary shroud of a turbine engine. During operation of the turbine engine, the seal lands straighten and extend towards the stationary shroud of the turbine engine, thereby reducing the leakage of air past the shrouded turbine blades and increasing the efficiency of the turbine engine. The sealing system may also include one or more protrusions extending from the stationary shroud towards the tips of the shrouded turbine blades.

43 citations


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