NDLI: Investigation of Tip Clearance Modeling Techniques for a Transonic Compressor Rotor

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Sean, T. Barrows Balasubramian, Ravishankar Chen, Jen-Ping
Copyright Year	2009
Abstract	Computational fluid dynamics (CFD) codes are becoming an integral part of the design and analysis process involved with creating and improving upon new engine designs. This necessitates the investigation and development of accurate modeling techniques for flow simulations with a quick turn around time of typically 48 hours. The present paper is focused on increasing the fidelity of compressor rotor simulations by examining three rotor tip clearance modeling techniques. The first approach models the tip clearance region as a loss-less, periodic, un-gridded region as first proposed by Kirtley et al. The second approach is a modification of this technique to study the vena-contracta effects. The tip clearance region remains un-gridded, but, the physical radial depth of tip clearance is gradually reduced to the smallest constriction typically seen in the tip clearance because of flow phenomena such as the shroud and blade-tip boundary layers. The final approach is a completely gridded tip clearance region of full depth to verify the vena-contracta approach as well as to determine if any increase in fidelity is achieved through this computationally costly procedure. These three tip clearance modeling approaches are applied to the NASA transonic compressor rotor, Rotor-35, in a rotor only configuration and the predicted operational ranges are compared to available LDV data. Span-wise performance characteristics such as total pressure ratio and total temperature ratio are compared at a near peak efficiency and at a near-stall operating point. Tip-vortex resolution and predictions are also examined. The merits and demerits of the three approaches are discussed and recommendations are made for a viable approach in terms of accuracy and computational resources.
Sponsorship	International Gas Turbine Institute
Starting Page	665
Ending Page	672
Page Count	8
File Format	PDF
ISBN	9780791848883
DOI	10.1115/GT2009-60136
e-ISBN	9780791838495
Volume Number	Volume 7: Turbomachinery, Parts A and B
Conference Proceedings	ASME Turbo Expo 2009: Power for Land, Sea, and Air
Language	English
Publisher Date	2009-06-08
Publisher Place	Orlando, Florida, USA
Access Restriction	Subscribed
Subject Keyword	Temperature Computational fluid dynamics Blades Engine design Nasa Rotors Wake turbulence Clearances (engineering) Compressors Modeling Flow (dynamics) Pressure Design Performance characterization Flow simulation Simulation Engineering simulation Resolution (optics) Boundary layers
Content Type	Text
Resource Type	Article

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