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- Title
Optimization and numerical investigation of combined design of blade and endwall on rotor 67.
- Authors
Li, Xin; Meng, Tongtong; Zhou, Ling; Li, Weiwei; Ji, Lucheng
- Abstract
In this work, a combined design of blade and endwall using the Extended Free Form Deformation technique is proposed and implemented on a transonic compressor rotor (the NASA Rotor 67). The best combined design is explored by numerical investigations and optimization via Kriging surrogate model method. As a result, by only modifying the hub and blade under 15 % span, the peak adiabatic efficiency is increased by 0.4 % and the overall aerodynamic performance for all operating conditions is also improved. An analysis shows that the enlarged dihedral angle between the hub and blade restrains boundary layer intersection and development. Meanwhile, the optimized hub changes the pressure distribution and prevents migration of cross-flow. As a result, the low-energy flow in the corner is accelerated downstream and the separation is limited, leading to an effective improvement in throughflow capability and aerodynamic performance in the corner region.
- Subjects
BOUNDARY layer (Aerodynamics); DIHEDRAL angles; ROTORS; TRANSONIC flow; ROTOR vibration
- Publication
International Journal of Turbo & Jet-Engines, 2024, Vol 41, Issue 2, p267
- ISSN
0334-0082
- Publication type
Article
- DOI
10.1515/tjj-2023-0011