Boundary Layer Development in the BR710 and BR715 LP Turbines—The Implementation of High-Lift and Ultra-High-Lift Concepts
Author:
Howell R. J.1, Hodson H. P.1, Schulte V.1, Stieger R. D.1, Schiffer Heinz-Peter2, Haselbach F.2, Harvey N. W.3
Affiliation:
1. Whittle Laboratory, Cambridge University, Cambridge CB3 0DY, United Kingdom 2. Rolls-Royce Deutschland, GmbH, Dahlewitz 15827, Germany 3. Turbine Systems, Rolls-Royce plc, Derby DE24 8BJ, UK
Abstract
This paper describes a detailed study into the unsteady boundary layer behavior in two high-lift and one ultra-high-lift Rolls-Royce Deutschland LP turbines. The objectives of the paper are to show that high-lift and ultra-high-lift concepts have been successfully incorporated into the design of these new LP turbine profiles. Measurements from surface mounted hot film sensors were made in full size, cold flow test rigs at the altitude test facility at Stuttgart University. The LP turbine blade profiles are thought to be state of the art in terms of their lift and design philosophy. The two high-lift profiles represent slightly different styles of velocity distribution. The first high-lift profile comes from a two-stage LP turbine (the BR710 cold-flow, high-lift demonstrator rig). The second high-lift profile tested is from a three-stage machine (the BR715 LPT rig). The ultra-high-lift profile measurements come from a redesign of the BR715 LP turbine: this is designated the BR715UHL LP turbine. This ultra-high-lift profile represents a 12 percent reduction in blade numbers compared to the original BR715 turbine. The results from NGV2 on all of the turbines show “classical” unsteady boundary layer behavior. The measurements from NGV3 (of both the BR715 and BR715UHL turbines) are more complicated, but can still be broken down into classical regions of wake-induced transition, natural transition and calming. The wakes from both upstream rotors and NGVs interact in a complicated manner, affecting the suction surface boundary layer of NGV3. This has important implications for the prediction of the flows on blade rows in multistage environments.
Publisher
ASME International
Subject
Mechanical Engineering
Reference22 articles.
1. Wisler, D. C., 1997, “The Technical and Economic Relevance of Understanding Boundary Layer Transition in Gas Turbine Engines,” NASA Minnowbrook II proceedings. 2. Howell, R. J., Ramesh, O. N., Hodson, H. P., Harvey, N. W., and Schulte, V., 2000, “High Lift and Aft Loaded Profiles for Low Pressure Turbines,” ASME Paper No. 2000-GT-261, accepted for publication in ASME J. Turbomach. 3. Curtis, E. M., Hodson, H. P., Banieghbal, M. R., Denton, J. D., Howell, R. J., and Harvey, N. W., 1996, “Development of Blade Profiles for Low Pressure Turbine Applications,” ASME J. Turbomach. 4. Hodson, H. P., 1993, “Modelling Unsteady Transition and Its Effects on Profile Loss,” ASME Paper No. 1989. 5. Ladwig, M., and Fottner, L., 1993, “Experimental Investigations of the Influence of Incoming Wakes on the Losses of a Linear Turbine Cascade,” ASME Paper No. 93-GT-394.
Cited by
58 articles.
订阅此论文施引文献
订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献
|
|