Abstract
An automated procedure is presented for the conjugate, Navier-Stokes/heat-conduction design and analysis of film-cooled turbine airfoil sections. In this procedure, the internal cooling plenums inside of the airfoil and the layer of thermal barrier coating are automatically constructed and computational grids for the main flow-path, cooling plenums, turbine walls, thermal barrier coating, and cooling tubes are generated. Embedded, overlaid grids are used for the cooling tubes allowing for any arbitrary placement without re-gridding of the main flow-path, turbine walls, or cooling plenums. The multi-disciplinary use of embedded, overlaid-grids makes this approach unique and effective for automated optimization procedures. The techniques used to construct the geometry and various computational grids as well as the treatment of embedded, overlaid grids in the NavierStokes procedure are described. Demonstration of the procedure is provided for a transonic turbine vane.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
