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Numerical research on near stall characteristics of a transonic axial compressor based on wavelet analysis

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Abstract

An axial single-stage high-speed test rig is numerically studied in this paper with half-annulus URANS simulations to describe the flow characteristics at the near stall condition. Wavelet analysis is applied to demonstrate the time–frequency characteristics of the near-tip pressure signals captured by the numerical probes at different circumferential and axial positions. The detailed tip flow fields and wavelet transform results are combined to depict the generation and propagation of the spike-type stall inception. According to the wavelet spectrum, characteristic frequencies correspond to the temporal and spatial features of the rotating stall, such as the fluctuation of the shock wave, self-oscillation and propagation of tip leakage vortex et al. Consequently, the detection of typical spike stall inception can be significantly brought forward by identifying the crucial rotating disturbance and its development for the onset of stall inception. Then, the specific tip flow fields are also discussed to reveal the flow mechanism of stall inception evolution, including the leading edge spillage and the trailing edge backflow. Further investigation shows that the stall inception with smooth casing corresponds to the radial separation vortex caused by the tip leading edge spillage, which continues to develop and propagate in the circumferential direction and finally induces the stall.

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Data availability

Some or all data, models or code that support the findings of this study are available from the corresponding author upon reasonable request.

Abbreviations

DSFT:

Discrete spatial Fourier transform

DTC:

Darmstadt transonic compressor

EMD:

Empirical mode decomposition

HHT:

Hilbert-Huang transform

ILU:

Incomplete lower upper

LE:

Leading edge

NS:

Near stall

PE:

Peak efficiency

PS:

Pressure surface

RANS:

Reynolds average Navier–stokes

SS:

Suction surface

SST:

Shear stress transport

STFT:

Short time Fourier transform

TE:

Trailing edge

URANS:

Unsteady Reynolds average Navier–Stokes

C ax :

Axial chord length

η * :

Isentropic efficiency

N :

Rotating speed

π * :

Total pressure ratio

T :

Rotating period of the DTC rotor

ω 0 :

Central frequency

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Acknowledgements

The authors wish to extend thanks to the United Innovation Center (UIC) of Aerothermal Technologies for Turbomachinery, and the Innovation Fund from the Engineering Research Center of Aerospace Science and Technology, Ministry of Education. Particular thanks go to Mr. Maximilian Jüngst and the Institute of Gas Turbines and Aerospace Propulsion in Technische Universität Darmstadt, who offered the geometry of the compressor stage and presented detailed experimental results in previous research. Sincere thanks to the ASME committee and Publishing Administrator for permitting the publication of the conference paper (GT2022-82366) [29] in this journal.

Funding

The authors gratefully acknowledge the supports from the Natural Science Foundation of Shanghai (23ZR1435400), the Aeronautical Science Foundation of China (2019ZB057006), Fundamental Research Funds for the Central Universities, Shanghai Municipal Education Commission (2023-02-7), and the United Innovation Center (UIC) of Aerothermal Technologies for Turbomachinery.

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Authors and Affiliations

  1. School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai, China

    Kailong Xia, Mingmin Zhu, Hefang Deng, Xiaoqing Qiang & Jinfang Teng

  2. AECC Commercial Aircraft Engine Co., Ltd, Shanghai, China

    Junda Feng

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  1. Kailong Xia
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  2. Mingmin Zhu
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  3. Junda Feng
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  4. Hefang Deng
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Correspondence to Mingmin Zhu.

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Xia, K., Zhu, M., Feng, J. et al. Numerical research on near stall characteristics of a transonic axial compressor based on wavelet analysis. AS (2023). https://doi.org/10.1007/s42401-023-00245-2

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