A closely combined experimental and computational fluid dynamics (CFD) study on a transonic blade tip aerothermal performance at engine representative Mach and Reynolds numbers is presented here and its companion paper (Part II). The present paper considers surface heat-transfer distributions on tip surfaces and on suction and pressure-side surfaces (near-tip region). Spatially resolved surface heat-transfer data are measured using infrared thermography and transient techniques within the Oxford University high speed linear cascade research facility. The Rolls-Royce PLC HYDRA suite is employed for numerical predictions for the same tip configuration and flow conditions. The CFD results are generally in good agreement with experimental data and show that the flow over a large portion of the blade tip is supersonic for all three tip gaps investigated. Mach numbers within the tip gap become lower as the tip gap decreases. For the flow regions near the leading edge of the tip gap, surface Nusselt numbers decrease as the tip gap decreases. Opposite trends are observed for the trailing edge region. Several “hot spot” features on blade tip surfaces are attributed to enhanced turbulence thermal diffusion in local regions. Other surface heat-transfer variations are attributed to flow variations induced by shock waves. Flow structure and surface heat-transfer variations are also investigated numerically when a moving casing is present. The inclusion of moving casing leads to notable changes to flow structural characteristics and associated surface heat-transfer variations. However, significant portions of the tip leakage flow remain transonic with clearly identifiable shock wave structures.
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October 2011
Research Papers
Transonic Turbine Blade Tip Aerothermal Performance With Different Tip Gaps—Part I: Tip Heat Transfer
Q. Zhang,
Q. Zhang
Department of Engineering Science,
University of Oxford
, Osney Mead, Oxford OX2 0ES, UK
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D. O. O’Dowd,
D. O. O’Dowd
Department of Engineering Science,
University of Oxford
, Osney Mead, Oxford OX2 0ES, UK
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L. He,
L. He
Department of Engineering Science,
University of Oxford
, Osney Mead, Oxford OX2 0ES, UK
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M. L. G. Oldfield,
M. L. G. Oldfield
Department of Engineering Science,
University of Oxford
, Osney Mead, Oxford OX2 0ES, UK
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P. M. Ligrani
P. M. Ligrani
Department of Engineering Science,
University of Oxford
, Osney Mead, Oxford OX2 0ES, UK
Search for other works by this author on:
Q. Zhang
Department of Engineering Science,
University of Oxford
, Osney Mead, Oxford OX2 0ES, UK
D. O. O’Dowd
Department of Engineering Science,
University of Oxford
, Osney Mead, Oxford OX2 0ES, UK
L. He
Department of Engineering Science,
University of Oxford
, Osney Mead, Oxford OX2 0ES, UK
M. L. G. Oldfield
Department of Engineering Science,
University of Oxford
, Osney Mead, Oxford OX2 0ES, UK
P. M. Ligrani
Department of Engineering Science,
University of Oxford
, Osney Mead, Oxford OX2 0ES, UKJ. Turbomach. Oct 2011, 133(4): 041027 (9 pages)
Published Online: April 27, 2011
Article history
Received:
July 11, 2010
Revised:
July 22, 2010
Online:
April 27, 2011
Published:
April 27, 2011
Citation
Zhang, Q., O’Dowd, D. O., He, L., Oldfield, M. L. G., and Ligrani, P. M. (April 27, 2011). "Transonic Turbine Blade Tip Aerothermal Performance With Different Tip Gaps—Part I: Tip Heat Transfer." ASME. J. Turbomach. October 2011; 133(4): 041027. https://doi.org/10.1115/1.4003063
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