Abstract
This paper presents a performance evaluation of non-axisymmetric casing grooves combined with airflow injection in a transonic axial compressor with NASA Rotor 37, using three-dimensional Reynolds-averaged Navier-Stokes equations with the k-ε turbulence model. An axisymmetric casing groove was divided circumferentially into 36 non-axisymmetric grooves. The numerical results for adiabatic efficiency and total pressure ratio were validated with experimental data. A parametric study for stall margin, stable range extension, peak adiabatic efficiency, and total pressure ratio at peak adiabatic efficiency of the compressor was performed using five parameters: the front and rear lengths, the height of the casing groove, the injection mass flow rate, and the injection angle. The non-axisymmetric casing grooves combined with injection improve greatly the stall margin and stable range extension of the transonic axial compressor, but reduce only slightly the peak adiabatic efficiency in all cases, compared to the results for a smooth casing.
Funding statement: This work was supported by INHA UNIVERSITY Research Grant.
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Articles in the same Issue
- Frontmatter
- Original Research Articles
- Numerical Study of Combinations of Strut and Cavity in a Round Supersonic Combustor
- Design and Numerical Analysis of a Forepart Rotation Vane for a Variable Nozzle Turbine
- Aerodynamic Efficiency Optimization of the 1st Stage of Transonic High Pressure Turbine through Lean and Sweep Angles
- The Effect of Dilution Air Jets on Aero-Engine Combustor Performance
- Simulation of a High Fidelity Turboshaft Engine-Alternator Model for Turboelectric Propulsion System Design and Applications
- Effects of Non-axisymmetric Casing Grooves Combined with Airflow Injection on Stability Enhancement of an Axial Compressor
- Exhaust System for Radial and Axial-Centrifugal Compressor with Pipe Diffuser
- Advanced Exergy Analysis of a Turbofan Engine (TFE): Splitting Exergy Destruction into Unavoidable/Avoidable and Endogenous/Exogenous
- A Preliminary Design System for Turbine Discs
- Tensile Behavior and Microstructural Evolution of the Polycrystalline Nickel-Based Superalloy Applied in Turbine Disk
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Numerical Study of Combinations of Strut and Cavity in a Round Supersonic Combustor
- Design and Numerical Analysis of a Forepart Rotation Vane for a Variable Nozzle Turbine
- Aerodynamic Efficiency Optimization of the 1st Stage of Transonic High Pressure Turbine through Lean and Sweep Angles
- The Effect of Dilution Air Jets on Aero-Engine Combustor Performance
- Simulation of a High Fidelity Turboshaft Engine-Alternator Model for Turboelectric Propulsion System Design and Applications
- Effects of Non-axisymmetric Casing Grooves Combined with Airflow Injection on Stability Enhancement of an Axial Compressor
- Exhaust System for Radial and Axial-Centrifugal Compressor with Pipe Diffuser
- Advanced Exergy Analysis of a Turbofan Engine (TFE): Splitting Exergy Destruction into Unavoidable/Avoidable and Endogenous/Exogenous
- A Preliminary Design System for Turbine Discs
- Tensile Behavior and Microstructural Evolution of the Polycrystalline Nickel-Based Superalloy Applied in Turbine Disk