Topic
Tip clearance
About: Tip clearance is a research topic. Over the lifetime, 2637 publications have been published within this topic receiving 32671 citations.
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TL;DR: In this paper, a variety of techniques for simulating the effects of rotor tip clearances in multistage axial compressors are discussed, and proper recognition of stage coupling and rematching effects is shown to be key to successful modeling of the overall behavior of actual engine compression systems.
Abstract: A variety of techniques for simulating the effects of rotor tip clearances in multistage axial compressors is discussed. Proper recognition of stage coupling and rematching effects is shown to be key to successful modeling of the overall behavior of actual engine compression systems. The application of a relatively simple one-dimensional unsteady row-by-row systems analysis is presented and shown to compare well to test data from several engine compressors.
25 citations
TL;DR: In this article, the authors performed numerical simulations to predict the film cooling effectiveness and the associated heat transfer coefficient in a 1-1/2 turbine stage, where the leading edge of the rotor blade is film cooled with three rows of film cooling holes.
25 citations
10 Jan 2000
TL;DR: In this paper, the off-design performance characteristics of a transonic axial compressor called NASA Rotor 67 have been analyzed using a three-dimensional time accurate Navier-Stokes analysis.
Abstract: The off-design performance characteristics of a transonic axial compressor called NASA Rotor 67 have been analyzed using a three-dimensional time accurate Navier-Stokes analysis. Rotating stall inception in this highspeed compressor has been studied. The effects of external disturbances such as inlet stagnation pressure distortion on rotating stall have also been simulated. The calculations show that at off-design conditions, reversed flow first forms in the tip clearance region. Its interaction with the shock over the blade leads to compressor stall, and at lower mass flow rates, to surge. It is demonstrated that stall can be eliminated, and stable operation restored, by the use of bleed valves located on the diffuser walls.
25 citations
TL;DR: In this paper, an efficient grid generation scheme was developed for the analysis of turbulent turbomachinery flows and tip clearance flows, and a semi-implicit, pressure-based computational fluid dynamics scheme that directly includes artificial dissipation, and is applicable to both viscous and inviscid flows.
Abstract: The numerical formulation developed here includes an efficient grid generation scheme, particularly suited to computational grids for the analysis of turbulent turbomachinery flows and tip clearance flows, and a semi-implicit, pressure-based computational fluid dynamics scheme that directly includes artificial dissipation, and is applicable to both viscous and inviscid flows. The value of this artificial dissipation is optimized to achieve accuracy and convergency in the solution. The numerical model is used to investigate the structure oftip clearance flows in a turbine nozzle. The structure of leakage flow is captured accurately, including blade-to-blade variation of all three velocity components, pitch and yaw angles, losses and blade static pressures in the tip clearance region. The simulation also includes evaluation of such quantities as leakage mass flow, vortex strength, losses, dominant leakage flow regions, and the spanwise extent affected by the leakage flow. It is demonstrated, through optimization of grid size and artificial dissipation, that the tip clearance flow field can be captured accurately.
25 citations
Dissertation•
01 Jan 1999
TL;DR: Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999 as mentioned in this paper, Boston, Massachusetts, USA.
Abstract: Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.
25 citations