Abstract
The efficiency of supersonic blade cascades for an impulse turbine designed by the conventional methods is not so high as expected because of the boundary layer separation. In this investigation, for improvement of the efficiency of the supersonic blade cascade, some important problems, such as accurate prediction of the starting Mach number and prevention of the boundary layer separation, are discussed based on the measurements and analysis of the flow in the blade passages designed by the free vortex flow method, which is one of the conventional methods. As the result, some design criteria are proposed.
Sign-in/Register to access full text options 
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.
