Influence of Combustor Flow With Swirl on Integrated Combustor Vane Concept Full-Stage Performance
Author:
Affiliation:
1. Osney Thermo-Fluids Laboratory, Department of Engineering Science, University of Oxford, Oxford OX2 0ES, UK e-mail:
2. Osney Thermo-Fluids Laboratory, Department of Engineering Science, University of Oxford, Oxford OX2 0ES, UK
Abstract
Publisher
ASME International
Subject
Mechanical Engineering
Link
http://asmedigitalcollection.asme.org/turbomachinery/article-pdf/doi/10.1115/1.4037820/6307491/turbo_140_01_011002.pdf
Reference17 articles.
1. Analytical and Experimental Study of Flow Through an Axial Turbine Stage With Nonuniform Inlet Radial Temperature Profiles,1983
2. Redistribution of Inlet Temperature Distortion in an Axial Flow Turbine Stage;J. Propul. Power,1989
3. Haldeman, C., 1989, “An Experimental Study of Radial Temperature Profile Effects on Turbine Tip Shroud Heat Transfer,” M.S. thesis, Massachusetts Institute of Technology, Cambridge, MA.https://dspace.mit.edu/handle/1721.1/39026
4. Analysis of Hot Streak Effects on Turbine Rotor Heat Load,1996
5. Migration of Combustor Exit Profiles Through High Pressure Turbine Vanes;ASME J. Turbomach.,2009
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