The Migration of Corner Separation Flow in Multi-Channel Compressor Cascades at High Attack Angle
-
Yu Duan
,
Qun Zheng
Abstract
The corner stall is known as a thorny problem for further increase of aerodynamic load and stability of compressors because of the notable instability separation flow in 3D space. The unsteady flow field in 6 channel rectangle cascades with clearance is studied by numerical simulation of RANS with SST turbulence model and γ-Reθ transition model. The analysis of results shows that with the increase of attack angle, the low energy fluid in the corner region chooses to move along spanwise direction firstly and fluctuates periodically. At critical angle of attack, the low energy fluid adapts to the too large flow drag by breaking through the limitation of local space in identified cascade corner and propagates as a way of unstable stall cells at lateral speed of 27.47% of inlet velocity.
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© 2018 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Editorial
- Study on Global Aerodynamic Shape Optimization of Transonic Compressor Blade
- Original Research Articles
- The Migration of Corner Separation Flow in Multi-Channel Compressor Cascades at High Attack Angle
- Water Film Formation and Performance Effect on Compressor Stage in Water Injection Process
- A Novel Reliability Analysis Method for Turbine Discs with the Mixture of Fuzzy and Probability-Box Variables
- Numerical Study of Unsteady Pulsed Suction through Endwall Bleed Holes in a Highly Loaded Compressor Cascade
- A Study on Torsional Vibration Suppression Method for an Integrated Helicopter / Engine System
- Numerical Simulation of Supersonic Jet Control by Tabs with Slanted Perforation
- Effect of Gurney Flaps on the Aerodynamic Characteristics of NACA 0010 Cascades
- A Study on Nonlinear Model Predictive Control for Helicopter/Engine with Variable Rotor Speed Based on Linear Kalman Filter
- Performance Characteristic Modeling for 2D Compressor Cascades
- Numerical Investigation on Metrological Fidelity of a Shielded Thermocouple Probe and the Effects of Geometrical Parameters
- Experimental Study of Kerosene Ignition and Flame Stabilization in a Supersonic Combustor
- Metaheuristics Optimized Machine Learning Modelling of Environmental Exergo-Emissions for an Aero-Engine
- Nonlinear Model Predictive Control Strategy for Limit Management of Aero-Engines
- Numerical Investigation on the Cold Flow Field of a Typical Cavity-based Scramjet Combustor with Double Ramp Entry
Articles in the same Issue
- Frontmatter
- Editorial
- Study on Global Aerodynamic Shape Optimization of Transonic Compressor Blade
- Original Research Articles
- The Migration of Corner Separation Flow in Multi-Channel Compressor Cascades at High Attack Angle
- Water Film Formation and Performance Effect on Compressor Stage in Water Injection Process
- A Novel Reliability Analysis Method for Turbine Discs with the Mixture of Fuzzy and Probability-Box Variables
- Numerical Study of Unsteady Pulsed Suction through Endwall Bleed Holes in a Highly Loaded Compressor Cascade
- A Study on Torsional Vibration Suppression Method for an Integrated Helicopter / Engine System
- Numerical Simulation of Supersonic Jet Control by Tabs with Slanted Perforation
- Effect of Gurney Flaps on the Aerodynamic Characteristics of NACA 0010 Cascades
- A Study on Nonlinear Model Predictive Control for Helicopter/Engine with Variable Rotor Speed Based on Linear Kalman Filter
- Performance Characteristic Modeling for 2D Compressor Cascades
- Numerical Investigation on Metrological Fidelity of a Shielded Thermocouple Probe and the Effects of Geometrical Parameters
- Experimental Study of Kerosene Ignition and Flame Stabilization in a Supersonic Combustor
- Metaheuristics Optimized Machine Learning Modelling of Environmental Exergo-Emissions for an Aero-Engine
- Nonlinear Model Predictive Control Strategy for Limit Management of Aero-Engines
- Numerical Investigation on the Cold Flow Field of a Typical Cavity-based Scramjet Combustor with Double Ramp Entry
