Aeromechanic performance of a single-stage transonic axial compressor with recirculation-bleeding channels

ABSTRACT

This paper presents a new investigation of the recirculation channel combined with bleeding channels, where the recirculation airflow recirculates air from downstream high-pressure region to an upstream through a recirculation channel located on shroud surface in rotor domain and the bleeding airflow through 36 bleeding channels sited on the recirculation channels ejects airflow to the by-pass channel in a single-stage transonic axial compressor used in turbofan engine. The object of this investigation is to reduce the vortex flow in the tip leakage region by finding the effects of recirculation and bleeding channels design on aeromechanic performance of a single-stage axial compressor, NASA Stage 37. A parametric study of the recirculation and bleeding channels were performed using various geometric parameters related to the locations and shapes of the recirculation and bleeding channels to find the effects of recirculation and bleeding channels design on aeromechanic performance, such as pressure ratio, efficiency, stall margin, blade tip deformation and Von-Mises stress. The numerical results showed an increase in aerodynamic performance and decrease in blade tip deformation with recirculation-bleeding channels, compared to the smooth casing.

KEYWORDS:

• Single-stage transonic axial compressor
• recirculation-bleeding channels
• Reynolds-averaged Navier-Stokes analysis
• FSI analysis
• pressure ratio
• efficiency
• stall margin
• blade tip deformation
• Von-Mises stress

Acknowledgements

This work is supported by the Vietnam National Foundation for Science and Technology Development (NAFOSTED) under Grant No. 107.03-2018.20.

Nomenclature

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Disclosure statement

No potential conflict of interest was reported by the authors.

Additional information

Funding

This work was supported by the National Foundation for Science and Technology Development [107.03-2018.20].