Analysis for predicting adiabatic wall temperatures with single hole coolant injection into a low speed crossflow
- Author
- Graham, R. W.
- Published
- JAN 1, 1981.
- Physical Description
- 1 electronic document
- Additional Creators
- Papell, S. S. and Wang, C. R.
Online Version
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- Restrictions on Access
- Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access - Summary
- Assuming the local adiabatic wall temperature equals the local total temperature in a low speed coolant mixing layer, integral conservation equations with and without the boundary layer effects are formulated for the mixing layer downstream of a single coolant injection hole oriented at a 30 degree angle to the crossflow. These equations are solved numerically to determine the center line local adiabatic wall temperature and the effective coolant coverage area. Comparison of the numerical results with an existing film cooling experiment indicates that the present analysis permits a simplified but reasonably accurate prediction of the centerline effectiveness and coolant coverage area downstream of a single hole crossflow streamwise injection at 30 degree inclination angle.
- Other Subject(s)
- Collection
- NASA Technical Reports Server (NTRS) Collection.
- Note
- Document ID: 19810004790.
Accession ID: 81N13301.
E-628.
NASA-TM-81620.
Ann. Intern. Gas Turbine Conf.; 8-12 Mar. 1981; Houston, TX; United States. - Terms of Use and Reproduction
- No Copyright.
View MARC record | catkey: 15720619