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Портал Begell Электронная Бибилиотека e-Книги Журналы Справочники и Сборники статей Коллекции
Heat Transfer Research
Импакт фактор: 1.199 5-летний Импакт фактор: 1.155 SJR: 0.267 SNIP: 0.503 CiteScore™: 1.4

ISSN Печать: 1064-2285
ISSN Онлайн: 2162-6561

Выпуски:
Том 51, 2020 Том 50, 2019 Том 49, 2018 Том 48, 2017 Том 47, 2016 Том 46, 2015 Том 45, 2014 Том 44, 2013 Том 43, 2012 Том 42, 2011 Том 41, 2010 Том 40, 2009 Том 39, 2008 Том 38, 2007 Том 37, 2006 Том 36, 2005 Том 35, 2004 Том 34, 2003 Том 33, 2002 Том 32, 2001 Том 31, 2000 Том 30, 1999 Том 29, 1998 Том 28, 1997

Heat Transfer Research

DOI: 10.1615/HeatTransRes.v42.i1.30
pages 3-23

Turbine Airfoil Leading-Edge Stagnation Aerodynamics and Heat Transfer − A Review

Lee S. Langston
Department of Mechanical Engineering, University of Connecticut, USA
Brian M. Holley
United Technologies Research Center 411 Silver Lane, M/S 129-89 East Hartford, CT 06108, USA

Краткое описание

The focus of this paper is on the fluid mechanics and heat transfer at the stagnation flow region at the leading edge of a turbine cascade airfoil. The fluid mechanics analysis presented is based on the exact solution to the Navier-Stokes equation of Hiemenz for a plane stagnating laminar flow. The heat transfer analysis is based on Hiemenz flow and a stagnation point potential flow, which predict a lower and an upper bound for stagnation region Stanton numbers. Comparisons of data from selected studies of skin friction and surface pressure show that the Hiemenz solution correlates well with the results from a number of stagnation flow experiments. The stagnation point heat transfer from four turbine cascade studies were found to be bounded by an upper limit on the Stanton number predicted by stagnation point potential flow and a lower limit by Hiemenz flow. These upper and lower limits should provide a useful heat transfer tool for the turbine designer.


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