Aero-Thermal-Structural Optimization of a High-Pressure Turbine Rotor With Robustness Evaluation to In-Service Deterioration
Year: 2025
Type: conference-paper
Abstract: This paper presents a multi-disciplinary optimization conducted on the high-pressure turbine rotor of a commercial turbofan engine. The rotor geometry is parametrized using a compact orthogonal design space, and the system’s response is studied under the aerodynamic, thermal and structural aspects via high-fidelity numerical simulations. The analysis is conducted using proprietary Rolls-Royce flow and structural solvers. The objective functions considered for the aerodynamic, thermal and structural disciplines are respectively high-pressure stage isentropic efficiency, peak near-wall gas temperature and peak von Mises stress on the rotor. The optimization is constrained by rotor capacity and high-pressure stage reaction degree. On the final three-dimensional Pareto front, two designs are selected, achieving a peak stress reduction of 17.5MPa and peak temperature reduction of 27.5K respectively. The sensitivity of these optimal designs to in-service degradation is then evaluated by applying various degrees of deterioration to the nominal designs. This deterioration is intended to replicate the erosion and deformation patterns observed on in-service blades after different numbers of operational cycles. The aerothermal performance of the optima is verified at a higher fidelity by conducting unsteady simulations.
Authors: Mario Carta, Roberto Putzu, Tiziano Ghisu, Shahrokh Shahpar
Institutions: University of Cagliari, Rolls-Royce (United Kingdom)
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: green
OpenAlex ID: W4413217524