The development of a high pressure turbine requires the accurate prediction of flow within and around film cooling holes. However, the length scales inherent to film cooling flows produce a large disparity against those of the mainstream flow; hence they cannot be resolved by a mesh generated for an aerodynamics analysis. Furthermore, the process of meshing cooling holes is not only time consuming but cumbersome; thus making the parametric study of film cooling effectiveness for a given blade geometry, using hole geometry and distribution, very difficult in a design environment. In this paper an immersed mesh block (IMB) approach is proposed which allows the refined mesh of a cooling hole to be immersed into the coarser mesh of a nozzle guide vane (NGV) and solved simultaneously while maintaining mass conservation. By employing two-way coupling, the flow physics in and around cooling holes is able to interact with the mainstream; hence the length scales of both types of flow are appropriately resolved. A generic cooling hole design can then be mapped to a given aerofoil geometry multiple times to achieve an appropriate distribution of cooling holes. The results show that for a realistic transonic blade, a configuration consisting of up to 200 cooling holes can be efficiently and accurately calculated—while retaining the original aerodynamic mesh but with a much enhanced resolution for the film cooling.
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January 2013
Research-Article
Use of an Immersed Mesh for High Resolution Modeling of Film Cooling Flows
L. He
L. He
e-mail: li.he@eng.ox.ac.uk
Osney Thermofluids Laboratory
Department of Engineering Science
Southwell Building, Osney Mead
Oxford, OX2 0ES, United Kingdom
Osney Thermofluids Laboratory
Department of Engineering Science
Oxford University
Southwell Building, Osney Mead
Oxford, OX2 0ES, United Kingdom
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B. Lad
e-mail: bharat.lad@eng.ox.ac.uk
L. He
e-mail: li.he@eng.ox.ac.uk
Osney Thermofluids Laboratory
Department of Engineering Science
Southwell Building, Osney Mead
Oxford, OX2 0ES, United Kingdom
Osney Thermofluids Laboratory
Department of Engineering Science
Oxford University
Southwell Building, Osney Mead
Oxford, OX2 0ES, United Kingdom
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 13, 2011; final manuscript received August 9, 2011; published online October 30, 2012. Editor: David Wisler.
J. Turbomach. Jan 2013, 135(1): 011022 (9 pages)
Published Online: October 30, 2012
Article history
Received:
July 13, 2011
Revision Received:
August 9, 2011
Citation
Lad, B., and He, L. (October 30, 2012). "Use of an Immersed Mesh for High Resolution Modeling of Film Cooling Flows." ASME. J. Turbomach. January 2013; 135(1): 011022. https://doi.org/10.1115/1.4006398
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