Heat Transfer, Adiabatic Effectiveness and Injectant Distributions Downstream of Single and Double Rows of Film-Cooling Holes with Compound Angles
Abstract
Experimental results are presented which describe the development and structure of turbulent boundary layer flow downstream of single and double rows of film-cooling holes with compound angles. The film-cooling holes are inclined at an angle of 30 degrees when projected into the spanwise/normal (Y-Z) planes and at an angle of 35 degrees when projected into the streamwise/normal (X-Y) planes with respect to the test surface. Three configurations are used: (1) one row of film-cooling holes with a blowing ratio of m=0.5, (2) one row of film- cooling holes with a blowing ratio of m=1.0, and (3) two staggered row of film- cooling holes with a blowing ratio of m=0.5. Results indicate that the highest eta values are obtained when two rows of compound angle injection cooling holes are employed with a blowing ratio of m=0.5, and that the lowest eta values results when one row of compound angle injection cooling holes is employed with a blowing ratio of m=1.0. Near film cooling holes and for x/d as high as 87, streamwise mean velocity and total pressure distributions show spanwise periodicity near the wall as a result of the discrete nature of film injection. At x/d=10.2, injectant distributions are non-circular in spanwise normal planes. These distributions spread in lateral and normal directions as the boundary layer convects downstream.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1990
- Accession Number
- ADA241095
Entities
People
- David T. Bishop Jr
Organizations
- Naval Postgraduate School