Modeling and Impact of High-pressure Turbine Blade Trailing Edge Film Cooling Hole Variations-Reference-Cited by-同舟云学术

Modeling and Impact of High-pressure Turbine Blade Trailing Edge Film Cooling Hole Variations

Published:2020-01-05 Issue: Volume: Page:
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Container-title:AIAA Scitech 2020 Forum
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Author:

Kamenik Jan¹,Toal David J.¹,Keane Andy¹,Högner Lars²,Meyer Marcus³,Shahpar Shahrokh³

Affiliation:

1. University of Southampton

2. Technical University of Dresden

3. Rolls-Royce Group plc

Publisher

American Institute of Aeronautics and Astronautics

Reference23 articles.

1. Montomoli, F., Carnevale, M., D’Ammaro, A., Massini, M., and Salvadori, S., 2015, Uncertainty Quantification in Computational Fluid Dynamics and Aircraft Engines, Springer. doi: 10.1007/978-3-319-14681-2

2. Kolmakova, D., Baturin, O., and Popov, G., 2014, “Effect of Manufacturing Tolerances on the Turbine Blades”, ASME Paper No. GTINDIA2014-8253. doi: 10.1115/GTINDIA2014-8253

3. Högner, L., Voigt, P., Nasuf, A., Voigt, M., Meyer, M., Goenaga, F., Berridge, C., and Vogeler, K., 2016, “Analysis of High Pressure Turbine Nozzle Guide Vanes Considering Geometric Variations”, ASME Paper No. GT2016-57502. doi: 10.1115/GT2016-57502

4. Duffner, J. D., 2008, “The Effects of Manufacturing Variability on Turbine Vane Performance”, PhD thesis,Massachusetts Institute of Technology. Available online: http://hdl.handle.net/1721.1/44933

5. Scharfenstein, J., Heinze, K., Voigt, M., Vogeler, K., and Meyer, M., 2013, “Probabilistic CFD Analysis of High Pressure Turbine Blades Considering Real Geometric Effects”, ASME Paper No. GT2013-94161. doi: 10.1115/GT2013-94161

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