Solution of Turbine Blade Cascade Flow Using an Improved Panel Method
Joint Authors
Source
International Journal of Aerospace Engineering
Issue
Vol. 2015, Issue 2015 (31 Dec. 2015), pp.1-6, 6 p.
Publisher
Hindawi Publishing Corporation
Publication Date
2015-12-08
Country of Publication
Egypt
No. of Pages
6
Abstract EN
An improved panel method has been developed to calculate compressible inviscid flow through a turbine blade row.
The method is a combination of the panel method for infinite cascade, a deviation angle model, and a compressibility correction.
The resulting solution provides a fast flexible mesh-free calculation for cascade flow.
A VKI turbine blade cascade is used to evaluate the method, and the comparison with experiment data is presented.
American Psychological Association (APA)
Lei, Zong-qi& Liang, G.. 2015. Solution of Turbine Blade Cascade Flow Using an Improved Panel Method. International Journal of Aerospace Engineering،Vol. 2015, no. 2015, pp.1-6.
https://search.emarefa.net/detail/BIM-1064506
Modern Language Association (MLA)
Lei, Zong-qi& Liang, G.. Solution of Turbine Blade Cascade Flow Using an Improved Panel Method. International Journal of Aerospace Engineering No. 2015 (2015), pp.1-6.
https://search.emarefa.net/detail/BIM-1064506
American Medical Association (AMA)
Lei, Zong-qi& Liang, G.. Solution of Turbine Blade Cascade Flow Using an Improved Panel Method. International Journal of Aerospace Engineering. 2015. Vol. 2015, no. 2015, pp.1-6.
https://search.emarefa.net/detail/BIM-1064506
Data Type
Journal Articles
Language
English
Notes
Includes bibliographical references
Record ID
BIM-1064506
