Film cooling from spanwise-oriented holes in two staggered rows
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Adiabatic effectiveness and iso-energetic heat transfer coefficients are presented from measurements downstream of film-cooling holes inclined at 30 deg. With respect to the test surface in spanwise/normal planes. With this configuration, holes are spaced 3d apart in the spanwise direction and 4d in the streamwise direction in two staggered rows. Results are presented for an injectant to free-stream density ratio near 1.0, and injection blowing ratios from 0.5 to 1.5. Spanwise-averaged adiabatic effectiveness values downstream of the spanwise/normal plane holes are significantly higher than values measured downstream of simple angle holes for x/d < 25--70 (depending on blowing ratio) when compared for the same normalized streamwise location, blowing ratio, and spanwise and streamwise hole spacings. Spanwise-averaged iso-energetic Stanton number ratios range between 1.0 and 1.41, increase with blowing ratio at each streamwise station, and show little variation with streamwise location for each value of blowing ratio tested.
The article of record as published may be found at http://dx.doi.org/101115/1.2841158ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration Houston, Texas, USA, June 5–8, 1995 Conference Sponsors: International Gas Turbine Institute
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Heat transfer, adiabatic effectiveness and injectant distribution downstream of single and double rows of film-cooling holes with compound angles. Wigle, James Michael (Monterey, California. Naval Postgraduate School, 1991-12);Experimental results are presented which describe the development and structure of flow downstream of one row and downstream of two staggered rows of film-cooling holes with compound angle orientations. Results presented ...
Ligrani, P.M.; Ramsey, A.E. (ASME, 1997-10-01);Experimental results are presented that describe the development and structure of flow downstream of a single row of film-cooling holes inclined at 30 deg from the test surface in spanwise/normal planes. With this ...
Heat transfer, adiabatic effectiveness and injectant distributions downstream of single rows and two staggered rows of film-cooling holes with simple and compound angles Jackson, Stephen Mark (Monterey, California. Naval Postgraduate School, 1991-12);Experimental results for two compound angle injection systems (configuration 1 and 3), and for a single injection system (configuration 2) are compared in this thesis. The effects of blowing ratio, spanwise hole spacing, ...