Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure Turbines
AbstractThe turbine tip geometry can significantly alter the performance of the turbine stage; its design represents a challenge for a variety of reasons. Multiple disciplines are involved in its design and their requirements limit the creativity of the designer. Multi-Disciplinary Design Optimisation (MDO) offers the capability to improve the performance whilst satisfying all the design constraints. This paper presents a novel design of a turbine tip achieved via MDO techniques. A fully parametrised Computer-Aided Design (CAD) model of the turbine rotor is used to create the squealer geometry and to control the location of the cooling and dust holes. A Conjugate Heat Transfer Computational Fluid Dynamics (CFD) analysis is performed for evaluating the aerothermal performance of the component and the temperature the turbine operates at. A Finite Element (FE) analysis is then performed to find the stress level that the turbine has to withstand. A bi-objective optimisation reduces simultaneously the aerodynamic loss and the stress level. The Multipoint Approximation Method (MAM) recently enhanced for multi-objective problems is chosen to solve this optimisation problem. The paper presents its logic in detail. The novel geometry offers a significant improvement in the aerodynamic performance whilst reducing the maximum stress. The flow associated with the new geometry is analysed in detail to understand the source of the improvement. View Full-Text
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Caloni, S.; Shahpar, S.; Toropov, V.V. Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure Turbines. Aerospace 2018, 5, 116.
Caloni S, Shahpar S, Toropov VV. Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure Turbines. Aerospace. 2018; 5(4):116.Chicago/Turabian Style
Caloni, Stefano; Shahpar, Shahrokh; Toropov, Vassili V. 2018. "Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure Turbines." Aerospace 5, no. 4: 116.
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