ITURB
ITURB (Optimal High-Lift Turbine Blade Aero-Mechanical Design)
Sustainable and Green Engines (SAGE)
Joint Technology Initiatives
Call ID: SP1-JTI-CS-2012-01
Topic: ITD-SAGE-02-012
Grant Agreement: no. 323301
Start: October 1st, 2012
Duration: 18 months
Coordinator: University of Genova (I)
Contractors:
1) University of Genova 2) University of Florence 3) University of Padova.
Links:
Abstract:
The need for high speed low pressure turbine modules to be used with innovative aircraft engine concept establishes critical mechanical constraints with very high hub stresses for the rotor blades, thus representing a real challenge for the design. In order to assist the designer with reliable tools it is mandatory to assess the performance of turbine rotor blades of innovative concept with both numerical and experimental investigations.
Starting from a baseline configuration, representative of the state-of-the-art of LPT high-lift rotor blades, an aerodynamic optimization will be performed exploiting modern optimization techniques. These techniques are based on the coupling between fast and flexible parametric handling of the geometries, CFD computations and meta-models like Artificial Neural Networks (ANN) or Radial Basis Functions (RBF). Such an approach will accomplish a multi-objective design aimed at enhancing the aerodynamic performance while meeting mechanical and geometrical constraints.
Tests will be performed on both baseline and optimized rotors within a cold-flow, large-scale laboratory turbine. Tests on turbine configuration will ensure the reproduction of the correct radial equilibrium effects as well as of the rotor-stator aerodynamic interaction. The Reynolds number will be investigated in the range between 50000 and 300000, which represents the operative range of the LP rotor blades of the engine. The large scale of the facility will allow detailed aerodynamic investigations, and an accurate performance analysis.
The numerical and experimental frameworks will allow one to validate and verify the optimized solution and to highlight the key features of the new design with respect to the baseline. The validation of the design and optimization procedures will be accomplished with the availability of detailed experimental data obtained for the innovative rotor blade row in a realistic environment.
Starting from a baseline configuration, representative of the state-of-the-art of LPT high-lift rotor blades, an aerodynamic optimization will be performed exploiting modern optimization techniques. These techniques are based on the coupling between fast and flexible parametric handling of the geometries, CFD computations and meta-models like Artificial Neural Networks (ANN) or Radial Basis Functions (RBF). Such an approach will accomplish a multi-objective design aimed at enhancing the aerodynamic performance while meeting mechanical and geometrical constraints.
Tests will be performed on both baseline and optimized rotors within a cold-flow, large-scale laboratory turbine. Tests on turbine configuration will ensure the reproduction of the correct radial equilibrium effects as well as of the rotor-stator aerodynamic interaction. The Reynolds number will be investigated in the range between 50000 and 300000, which represents the operative range of the LP rotor blades of the engine. The large scale of the facility will allow detailed aerodynamic investigations, and an accurate performance analysis.
The numerical and experimental frameworks will allow one to validate and verify the optimized solution and to highlight the key features of the new design with respect to the baseline. The validation of the design and optimization procedures will be accomplished with the availability of detailed experimental data obtained for the innovative rotor blade row in a realistic environment.
Publications:
Giovannini M, Rubechini F, Marconcini M, Arnone A, Bertini F. 2016. Analysis of a LPT Rotor Blade For a Geared Engine. Part I: Aero-Mechanical Design and Validation. ASME Turbo Expo 2016. ASME paper GT2016-57746.
Giovannini M, Marconcini M, Rubechini F, Arnone A, Bertini F. 2016. Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing. ASME Journal of Turbomachinery. 138(11):111001-1-9.