Invention Application
US20120251331A1 Turbine Blade Platform Undercut 有权
涡轮叶片平台底切

Turbine Blade Platform Undercut
Abstract:
A system and method of extending the useable life of a gas turbine blade is disclosed in which the gas turbine blade includes an undercut configuration designed to relieve mechanical and thermal stress imparted into the pedestal region of the airfoil trailing edge. The embodiments of the present invention include turbine blade configurations having different trailing edge undercut configurations as well as additional cooling supplied to the internal passages of the trailing edge region of the turbine blade.
Public/Granted literature
Information query
Patent Agency Ranking
0/0