Experimental analysis of performance and tip dynamic pressure in a compressor cascade with high-speed moving endwall

Kailong Xia; Hefang Deng; Shaopeng Lu; Jinfang Teng; Xiaoqing Qiang; Mingmin Zhu

doi:10.1515/tjj-2023-0025

Article

Experimental analysis of performance and tip dynamic pressure in a compressor cascade with high-speed moving endwall

Kailong Xia , Hefang Deng , Shaopeng Lu , Jinfang Teng , Xiaoqing Qiang and Mingmin Zhu

Published/Copyright: June 27, 2023

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From the journal International Journal of Turbo & Jet-Engines Volume 41 Issue 2

Abstract

This study measured the aerodynamic performance and dynamic pressure signals of a compressor cascade platform with high-speed rotating endwall. Instead of translational movement, the endwall features an innovative large rotating disk. Measurements were conducted on a controlled diffusion airfoil (CDA) under different conditions: tip clearances (3 mm and 2.5 mm), inlet incidences (+6° and −6°), and stationary or high-speed rotating states at 0.5 Ma inflow. The results reveal that endwall movement amplifies circumferential leakage losses, increases kinetic energy, deviates the leakage flow path, and reduces total pressure loss in the leakage core region. Dynamic pressure results reveal greater unsteadiness in the tip region under positive incidence conditions and with larger clearances. Characteristic frequency ranges (8000 Hz for system vibration and 150∼200 Hz for leakage flow development) are identified. Further experimental measurements and high-precision simulations are needed the determine the matching relationship between complex flow behaviour in the blade tip region and characteristic frequency.

Keywords: compressor cascade; dynamic pressure; moving endwall; time–frequency analysis; tip leakage flow

Corresponding author: Jinfang Teng, School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Dongchuan Road, Shanghai 200240, China, E-mail: tjf@sjtu.edu.cn

Funding source: National Natural Science Foundation of China

Award Identifier / Grant number: Unassigned

Funding source: National Science and Technology Major Project

Award Identifier / Grant number: Unassigned

Funding source: Fundamental Research Funds for the Central Universities

Award Identifier / Grant number: Unassigned

Acknowledgments

The authors gratefully acknowledge the support of the National Natural Science Foundation of China (No. 52076129, No. 51576124), the National Science and Technology Major Project (2017-II-0004-0017), the Fundamental Research Funds for the Central Universities, and the United Innovation Center (UIC) of Aerothermal Technologies for Turbomachinery.

Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
Research funding: None declared.
Conflict of interest statement: The authors declare no conflict of interest.

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Received: 2023-03-13

Accepted: 2023-06-12

Published Online: 2023-06-27

Published in Print: 2024-05-27

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Articles in the same Issue

https://doi.org/10.1515/tjj-2023-0025

Keywords for this article

compressor cascade; dynamic pressure; moving endwall; time–frequency analysis; tip leakage flow