Abstract
Abstract The article describes the impact of the gas turbine engine low-pressure turbine blade shroud shelf on the blade profile stress position. Attention is focused directly on the impact of the location of the gravity centre of the shroud shelf on blade stress distribution at the three most critical points of the profile. The paper describes the details of the calculation and the required expressions provided, as well as the results of the calculation example with clear graphical dependencies.
Highlights
The turbine blades are exposed to heavy working conditions
This paper discusses the possibility for load reduction of aerodynamically profiled part of a gas turbine engine turbine non-refrigerated blade by changing the location of the gravity centre of the shroud shelf
The study describes an unloading of the base part of the turbine blade from bending stresses and an additional load reduction from residual bending stresses in the middle of the blade on the “back” side
Summary
The turbine blades are exposed to heavy working conditions. Blades of the modern gas turbine engines often contain shroud shelves (see Fig. 1a). This paper discusses the possibility for load reduction of aerodynamically profiled part of a gas turbine engine turbine non-refrigerated blade by changing the location of the gravity centre of the shroud shelf (see Fig. 1b). In that way contributing to the aerodynamically profiled part of the blade in the medium-radius area in addition to the residual bending forces (followed by bending stress) which remain after removing the base load with skewed method. Even such a small load reduction can extend the lifetime of the blade and increase the overall safety of the structure. The study can be useful for those interested in calculating algorithms that want to gain an in-depth understanding of the specifics, nuances and challenges of calculating a complex detail
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