Aerodynamic performance improvement of a transonic axial compressor by swept and leaned rotors

Nian Zhou Huang, Xu Zhao, Yong Hua Zhang, Xin Yi Wu

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

2 Scopus citations

Abstract

To understand rotors axial sweep and tangential lean effects on transonic axial compressor NASA Rotor37 aerodynamic performance, a numerical study was carried out. Rotor stacking line was described by Bezier polynomials and optimized in axial and tangential direction separately and coupledly. The optimization problem was to achieve the maximum rotor isentropic efficiency at the design point, with a constraint on mass flow rate and pressure ratio. A technique based on concept of function approximation was developed for rotor performance evaluation. Steady and unsteady flow simulations across the rotor were completed to predict performance at various working conditions. It was found that both C shape and S shape stacking line helps to improve rotor efficiency and stall margin. The C shape swept and leaned rotor displays the best performance. The peak efficiency was increased 1.1%, peak total pressure ratio increased 1.6% and the absolute value of stall margin increased 2% compared to Rotor37. Shock wave and tip leakage flow were found to move downstream with less strength. The fluctuation of blade pressure and backflow near stall condition of Rotor37 were analyzed.

Original languageEnglish
Title of host publicationAIAA Propulsion and Energy Forum and Exposition, 2019
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105906
DOIs
StatePublished - 2019
EventAIAA Propulsion and Energy Forum and Exposition, 2019 - Indianapolis, United States
Duration: 19 Aug 201922 Aug 2019

Publication series

NameAIAA Propulsion and Energy Forum and Exposition, 2019

Conference

ConferenceAIAA Propulsion and Energy Forum and Exposition, 2019
Country/TerritoryUnited States
CityIndianapolis
Period19/08/1922/08/19

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