Flow characteristics on a 4-stage low-speed research compressor with a cantilevered stator

被引：19
|
作者：
Ju, Zhenzhou [1 ]
Teng, Jinfang [1 ]
Zhu, Mingmin [1 ]
Ma, Yuchen [1 ]
Qiang, Xiaoqing [1 ]
Fan, Lin [2 ]
Yang, Zhong [2 ]
机构：
[1] Shanghai Jiao Tong Univ, Sch Aeronaut & Astronaut, 800 Dongchuan RD, Shanghai 200240, Peoples R China
[2] AECC Commercial Aircraft Engine Co, Shanghai, Peoples R China
来源：
AEROSPACE SCIENCE AND TECHNOLOGY | 2020年 / 105卷
关键词：
LSRC; Cantilevered stator; Flow characteristics; Near stall; Blade loading; Leakage momentum; TIP LEAKAGE FLOW; STALL;
D O I：
10.1016/j.ast.2020.106033
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
This paper presents the experimental and numerical investigation of flow characteristics on the highly loaded 4-stage low-speed research compressor (LSRC) with a Cantilevered Stator of Shanghai Jiao Tong University. A new three-dimensional design for the cantilevered stator in the LSRC was derived using an asymmetrical circumferential bow, and the cantilevered stator near the hub adopted the fore-loading design. The unsteady Reynolds averaged Navier-Stokes (URANS) numerical results were compared with experimental data and the differences were introduced. The evolution of the hub leakage flow at the near stall (NS) operating condition compared with the design point (DP) was analyzed, and design suggestions were provided for the two operating conditions. The present study details the effects of the hub leakage flow on the highly loaded LSRC, and provides some quantified data between the aerodynamic performance and hub leakage flow. Designers needing to better understand the hub leakage flow of a cantilevered stator in a multi-stage compressor will benefit from this paper. (c) 2020 Elsevier Masson SAS. All rights reserved.
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页数：10
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