NDLI: Numerical analysis of film cooling at high blowing ratio

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Numerical analysis of film cooling at high blowing ratio

Content Provider	NASA Technical Reports Server (NTRS)
Author	Ameri, Ali El-Gabry, Lamyaa Heidmann Sr., James
Copyright Year	2009
Description	Computational Fluid Dynamics is used in the analysis of a film cooling jet in crossflow. Predictions of film effectiveness are compared with experimental results for a circular jet at blowing ratios ranging from 0.5 to 2.0. Film effectiveness is a surface quantity which alone is insufficient in understanding the source and finding a remedy for shortcomings of the numerical model. Therefore, in addition, comparisons are made to flow field measurements of temperature along the jet centerline. These comparisons show that the CFD model is accurately predicting the extent and trajectory of the film cooling jet; however, there is a lack of agreement in the near-wall region downstream of the film hole. The effects of main stream turbulence conditions, boundary layer thickness, turbulence modeling, and numerical artificial dissipation are evaluated and found to have an insufficient impact in the wake region of separated films (i.e. cannot account for the discrepancy between measured and predicted centerline fluid temperatures). Analyses of low and moderate blowing ratio cases are carried out and results are in good agreement with data.
File Size	5999445
Page Count	36
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20090020392
Archival Resource Key	ark:/13960/t8nd0z04j
Language	English
Publisher Date	2009-04-01
Access Restriction	Open
Subject Keyword	Fluid Mechanics And Thermodynamics Computational Fluid Dynamics Engine Inlets Gas Turbine Engines Airfoils Temperature Measurement Numerical Analysis Turbulence Models Boundary Layer Thickness Dissipation Mathematical Models Film Cooling Spanwise Blowing Free Flow Heat Transfer Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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