Flow characteristics on a 4-stage low-speed research compressor with a cantilevered stator-Reference-Cited by-同舟云学术

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

Published:2020-10 Issue: Volume:105 Page:106033
ISSN:1270-9638
Container-title:Aerospace Science and Technology
language:en
Short-container-title:Aerospace Science and Technology

Author:

Ju Zhenzhou,Teng Jinfang,Zhu Mingmin,Ma Yuchen,Qiang Xiaoqing,Fan Lin,Yang Zhong

Funder

Natural Science Foundation of China

National Science and Technology Major Project

Publisher

Elsevier BV

Subject

Aerospace Engineering

Reference19 articles.

1. Effect of the stator hub configuration and stage design parameters on aerodynamic loss in axial compressors;Yoon;J. Turbomach.,2015

2. An experimental verification of a new design for cantilevered stators with large hub clearances;Lange;J. Turbomach.,2013

3. Tip leakage flow in axial compressors;Storer;J. Turbomach.,1991

4. Similarity analysis of compressor tip clearance flow structure;Chen;J. Turbomach.,1991

5. Influence of tip leakage flow and ejection on stall mechanism in a transonic tandem rotor;Han;Aerosp. Sci. Technol.,2018

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1. Impact of non-axisymmetric tip clearance on the aerodynamic and aeroelastic stabilities of a transonic compressor;Aerospace Science and Technology;2024-10

2. Interaction effects between the rotor wake and hub leakage flow in a multi-stage cantilevered compressor;International Journal of Turbo & Jet-Engines;2024-09-05

3. The loss mechanisms and vortex dynamics of rotor platform step geometries in a low-speed research compressor stage;Physics of Fluids;2024-08-01

4. Optimization and experimental study of stationary endwall of stator labyrinth cavity in a low-speed research compressor;Aerospace Science and Technology;2024-04

5. The impact of second-harmonic tip clearance distributions caused by casing Ovalization and blade height variation in a large-scale compressor stage;Aerospace Science and Technology;2024-02

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