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ABSTRACT
This paper presents the effect of an inclined casing groove on the aerodynamic performance of a single-stage transonic axial compressor, NASA Stage 38, using three-dimensional Reynold-averaged-Navier-Stokes equations with the k-ε turbulence model. The research was carried out to examine the effects of four casing groove parameters: angle, width, depth, and location. Validation of a numerical model for a single-stage transonic axial compressor was conducted to evaluate the computational fluid dynamics method. Most of the simulations showed positive results with an increase in stall margin, adiabatic efficiency, and total pressure ratio, in which the maximum stall margin, adiabatic efficiency, and total pressure ratio can be raised by 87.09%, 0.13%, and 1.57%, respectively, as compared to the smooth casing case.
Nomenclature
| EFF | = | Peak efficiency |
| LSZ | = | Low speed zones |
| PR | = | Pressure ratio |
| SL | = | Separation line |
| SM | = | Stall margin |
| SC | = | Smooth casing |
| TR | = | Temperature ratio |
| CR | = | Axial length of the rotor tip blade chord (mm) |
| H | = | Depth of the casing groove (mm) |
| L | = | Axial distance from the rotor tip blade to the casing groove (mm) |
| ṁNS | = | Total pressure ratio at near-stall condition (kg/s) |
| ṁpeak | = | Total pressure ratio at peak efficiency condition (kg/s) |
| Pt,in | = | Total pressure at compressor’s inlet (Pa) |
| Pt,out | = | Total pressure at compressor’s outlet (Pa) |
| Tt,in | = | Total temperature at compressor’s inlet (K) |
| Tt,out | = | Total temperature at compressor’s outlet (K) |
| W | = | Width of the casing groove (mm) |
| α | = | Angle of the casing groove relative to the shroud (º) |
| Ʈ | = | Rotor tip clearance (mm) |
Acknowledgements
The authors are also grateful to the cooperation between Viettel Aerospace Institute (Vietnam), Hanoi University of Science and Technology, and Le Quy Don Technical University for the support during this research.
Disclosure statement
No potential conflict of interest was reported by the author(s).
Data availability statement
The authors confirm that the data supporting the findings of this study are available within the article.
Additional information
Funding
Notes on contributors
Anh-Tuan Nguyen
Anh-Tuan Nguyen is a Lecturer of Hanoi University of Science and Technology (HUST), Vietnam since 2000. He got his Ph.D degree in 2014 from Ritsumeikan University (Japan) in the field of Micro Electromechanical Systems (MEMS). His interest field is on mechatronics, robotics, machine mechanics, material, aircraft structure, composite structure, turbomachine.
Huynh-Duc Vo
Huynh-Duc Vo received an Aerospace engineering degree at Hanoi University of Science and Technology, Vietnam in 2021. He is a graduate student at SeoulTech (Seoul National University of Science and Technology) from 2021. He works in Mechenical Engineering.
Cong-Truong Dinh
Cong-Truong Dinh is a Lecturer and Researcher at HUST (Hanoi University of Science and Technology), Vietnam since 2018 in Aerospace Engineering. Graduated from Inha University, Korea with a Doctoral degree in Mechanical Engineering in 2017. His research interests in Turbomachinery and Propulsion Engineering.
Hoang-Quan Chu
Hoang-Quan Chu is a lecturer and a researcher of Faculty of Aerospace Engineering, Le Quy Don Technical University (LQDTU), Hanoi, Vietnam since 2012. He received his Master’s degree in aerospace Propulsion Systems from ISAE/SUPAERO, Toulouse, France in 2016. His current research interests are Propulsion, Turbomachinery, Aerodynamics, Aeroacoustics, Fluid-Structure Interaction, Computational Fluid Dynamics, and Optimization Techniques.