Near Tip Loss Control With a Winglet Baffle Cavity Tip in a Turbine Cascade
Author:
Affiliation:
1. College of Engineering, Peking University, Beijing 100871, China
2. AECC Commercial Aircraft Engine Co., Ltd., Shanghai 200241, China
Abstract
Funder
National Major Science and Technology Projects of China
National Natural Science Foundation of China
Publisher
ASME International
Subject
Mechanical Engineering,Energy Engineering and Power Technology,Aerospace Engineering,Fuel Technology,Nuclear Energy and Engineering
Link
http://asmedigitalcollection.asme.org/gasturbinespower/article-pdf/143/10/101007/6762213/gtp_143_10_101007.pdf
Reference26 articles.
1. Loss Mechanisms in Turbomachines,1993
2. The Effect of Blade Tip Geometry on the Tip Leakage Flow in Axial Turbine;ASME J. Turbomach.,1992
3. Geometrical Uncertainty in Turbomachinery: Tip Gap and Fillet Radius;Comput. Fluids,2011
4. Aerodynamics of Tip Leakage Flows Near Partial Squealer Rims in an Axial Flow Turbine Stage;ASME J. Turbomach.,2005
5. The Tip Leakage Flow of an Unshrouded High Pressure Turbine Blade With Tip Cooling,2009
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1. Aerothermal effects of squealer openings on a cavity tip in a turbine cascade;International Journal of Turbo & Jet-Engines;2023-09-25
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