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Heat transfer, adiabatic effectiveness and injectant distributions downstream of single and double rows of film-cooling holes with compound angles

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Author
Bishop, David Turner
Date
1990-09
Advisor
Ligrani, Phillip M
Subramanian, Chelakara S.
Second Reader
Ligrani, Phillip M
Subramanian, Chelakara S.
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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 spanwisenormal (Y-Z) planes and at an angle of 35 degrees when projected into the streamwisenormal (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 xd 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 xd=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.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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http://hdl.handle.net/10945/34872
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  • 1. Thesis and Dissertation Collection, all items

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    Heat transfer, adiabatic effectiveness and injectant distributions downstream of single and double rows of film-cooling holes with simple and compound angles 

    Ciriello, Salvatore (Monterey, California. Naval Postgraduate School, 1991-03);
    Experimental results are presented which describe the development and structure of flow downstream of single and double rows of film-cooling holes with both simple and compound angle orientations. Two configurations ...
  • Thumbnail

    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 ...
  • Thumbnail

    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, ...
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