Study of low Reynolds number effects on the losses in low-pressure turbine blade rows
Author:
Affiliation:
1. GMI Engineering and Management Inst., Flint, MI
2. NASA, Lewis Research Center, Cleveland, OH
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1998-3575
Reference40 articles.
1. Boundary-Layer Transition and Separation Near the Leading Edge of a High-Speed Turbine Blade
2. An Investigation of Boundary Layer Development in a Multistage LP Turbine
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1. Predicting Transition in Turbomachinery—Part II: Model Validation and Benchmarking;Journal of Turbomachinery;2004-03-01
2. The effects of blade count on boundary layer development in a low-pressure turbine;38th Aerospace Sciences Meeting and Exhibit;2000-01-10
3. Study of boundary layer development in a two-stage low-pressure turbine;37th Aerospace Sciences Meeting and Exhibit;1999-01-11
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