Design and stability study of a distortion-tolerant axial compressor based on an alternating stator layout

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology Pub Date : 2025-02-01 DOI:10.1016/j.ast.2024.109810

Wenguang Fu , Junyang Yu , Rui Zuo , Peng Sun , Wei Wang

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引用次数: 0

Abstract

To effectively suppress flow separation in the corner regions of a compressor, improve aerodynamic performance, and enhance distortion tolerance, this study focuses on a single-stage high-load transonic axial flow compressor and introduces a novel and effective unconventional stator design known as an alternating stator (AS) vane layout. This study examines the relationship between the AS layout and the flow separation in the corner regions from a fluid dynamics perspective and investigates the enhancement effects of different AS designs on the compressor's aerodynamic performance and stability margin (SM). Numerical investigations indicate that the alternating layout scheme, which is developed by locally adjusting the inlet geometric angle of the stator vanes, can effectively improve the aerodynamic performance and stability of the compressor. Compared to the original compressor design, the scheme with a 12° adjustment in the blade tip's geometric angle significantly increases both the total pressure ratio and efficiency. This scheme also enhances the SM by 34.69 %. With this alternating layout, the novel stator arrangement induces differentiation in the flow field structure among adjacent passages. Internally, an alternating separation forms at the top and root corner regions of the adjacent stator passages, effectively preventing extensive flow separation from occurring at the top or root corner regions of the compressor and thereby delaying a compressor stall. When this design is applied to the compressor stage with inlet distortion conditions, the AS scheme with a 12° adjustment in the blade tip's geometric angle effectively improves the compressor's aerodynamic performance and distortion tolerance and holds significant potential for expanding the stable operating range of the compressor with inlet distortion conditions. Relative to the original design, the SM of the AS compressor can be increased by 83.09 %.

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来源期刊

Aerospace Science and Technology 工程技术-工程：宇航

CiteScore

10.30

自引率

28.60%

发文量

654

审稿时长

54 days

期刊介绍： Aerospace Science and Technology publishes articles of outstanding scientific quality. Each article is reviewed by two referees. The journal welcomes papers from a wide range of countries. This journal publishes original papers, review articles and short communications related to all fields of aerospace research, fundamental and applied, potential applications of which are clearly related to: • The design and the manufacture of aircraft, helicopters, missiles, launchers and satellites • The control of their environment • The study of various systems they are involved in, as supports or as targets. Authors are invited to submit papers on new advances in the following topics to aerospace applications: • Fluid dynamics • Energetics and propulsion • Materials and structures • Flight mechanics • Navigation, guidance and control • Acoustics • Optics • Electromagnetism and radar • Signal and image processing • Information processing • Data fusion • Decision aid • Human behaviour • Robotics and intelligent systems • Complex system engineering. Etc.