A Twisted Turbine Blade Analysis for a Gas Turbine Engine
Final rept. Sep 96-Feb 97
ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
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An analysis of a twisted turbine blade was performed to determine the regions of maximum stress and moment which occur on a typical gas turbine engine under variable revolutions per second. An extension of the Holzer and Myklestad methods was developed to simulate shear and moment effects occurring from the root of the blade to its outermost extremity. Under numerical simulations, shear force and moments of inertia were realized at changing revolutions per minute by solving the Den Hartog twisted blade equations.
- Jet and Gas Turbine Engines