Optimization and numerical investigation of combined design of blade and endwall on rotor 67-Reference-Cited by-同舟云学术

Optimization and numerical investigation of combined design of blade and endwall on rotor 67

Published:2023-05-18 Issue:0 Volume:0 Page:
ISSN:0334-0082
Container-title:International Journal of Turbo & Jet-Engines
language:en
Short-container-title:

Author:

Li Xin¹,Meng Tongtong²,Zhou Ling²,Li Weiwei¹,Ji Lucheng¹

Affiliation:

1. Institute for Aero Engine, Tsinghua University , Beijing 100084 , China

2. School of Aerospace Engineering , Beijing Institute of Technology , Beijing 100081 , China

Abstract

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.

Publisher

Walter de Gruyter GmbH

Subject

Aerospace Engineering

Link

https://www.degruyter.com/document/doi/10.1515/tjj-2023-0011/pdf

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