Accession Number : ADA257325


Title :   A Study of Film Cooling Downstream of One and Two Rows of Holes Oriented in Spanwise/Normal Planes


Descriptive Note : Master's thesis


Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA


Personal Author(s) : Ramsey, Anthony E


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a257325.pdf


Report Date : Sep 1992


Pagination or Media Count : 269


Abstract : Experimental results are presented which describe the development and structure of flow downstream of a single row and two staggered rows of film- cooling holes with compound angle orientations. With the configuration studied, holes are inclined at 90 degrees with respect to the test surface when projected into the streamwise/normal plane, and 30 degrees with respect to the test surface when projected into the spanwise/normal plane. Within each row, holes are spaced 6.0 hole diameter apart in the spanwise direction which gives 3.Od spacing between adjacent holes for the staggered row arrangement. Also presented are plots showing the streamwise development of injectant distributions and streamwise development of mean velocity distributions. Spanwise averaged values of the adiabatic film-cooling effectiveness depend mostly on four parameters: hole angle orientation, spanwise hole spacing, number of rows of film-cooling holes (one or two), and blowing ratio. Spanwise averaged values of the adiabatic film-cooling effectiveness are generally greatest at low x/d and decrease with increasing x/d values for any given blowing ratio. Spanwise averaged effectiveness values decrease with blowing ratio for x/d less than 40 except for data for m=2.5. This trend generally reverses itself at higher x/d values. Spanwise averaged isoenergetic Stanton number ratios range between 1.0 and 1.5 and show little variation as x/d increases for each value of blowing ratio, however for each x/d, values increase with increasing blowing ratio. Compound angle injection, film cooling, turbulent boundary layer.


Descriptors :   *TURBULENT BOUNDARY LAYER , *GAS TURBINES , *FILM COOLING , TEST AND EVALUATION , VELOCITY , ANGLES , DIAMETERS , COOLING , CONFIGURATIONS , BOUNDARY LAYER FLOW , COMBUSTION CHAMBER LINERS , STREAMFLOW ANALYSIS , REYNOLDS NUMBER , ADIABATIC CONDITIONS , GAS TURBINE BLADES , HOLES(OPENINGS) , SURFACES , INJECTION , STRUCTURES , BOUNDARY LAYER , TURBULENT FLOW


Subject Categories : Fluid Mechanics
      Thermodynamics
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE