The Relationship of Spike Stall and Hub Corner Separation in Axial Compressor
-
Bin Jiang
,
Xiangtong Shi
Abstract
The onset of spike stall induced by the interaction of hub corner separation flow with the tip leakage flow is investigated in detail by numerical method in this paper. The time resolved results indicate that the remarkable radial secondary flow from hub to tip near the trailing edge is formed when the compressor approaching rotating stall. The radial secondary flow is unstable and cross-passages propagates, which flows in and away out of the tip region periodically. The disturbance caused by radial secondary flow will influence the tip leakage flow directly by reforming the vortexes in blade tip region. A secondary vortex which comes from the radial migration of corner separation and is induced by the tip leakage vortex appears in the tip region. The simulation result demonstrates that the generation of the secondary vortex is an important symbol of blockage growth in the tip region at the stall inception phase. The disturbance produced by secondary vortex is an incentive of the leading edge overflow and the intensity of secondary vortex could be used as a criterion of rotating stall before leading edge spillage.
Funding statement: The authors wish to thank the financial supports of National Natural Science Foundation of China under Grant No. 51676039 and Fundamental Research Funds (HEUCF150304) for the Central Universities.
Nomenclature
pressure recovery coefficien
isentropic index
total temperature
total pressure ratio
torque
power
rotational speed
relative velocity
tangential velocity of blade tip
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Articles in the same Issue
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- The Relationship of Spike Stall and Hub Corner Separation in Axial Compressor
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Articles in the same Issue
- Frontmatter
- The Relationship of Spike Stall and Hub Corner Separation in Axial Compressor
- Aeroengine Performance Prediction Based on Double-Extremum Learning Particle Swarm Optimization
- Dynamic Characteristics Analysis and Optimization Design of a Simulated Power Turbine Rotor Based on Finite Element Method
- Numerical Prediction of 45° Angled Ribs Effects on U-shaped Channels Heat Transfer and Flow under Multi Conditions
- Effect of Primary Rocket Jet on Thermodynamic Cycle of RBCC in Ejector Mode
- Study on Acoustic Detection of the Working State of Pulse Detonation Engine
- Research on Nozzle Jet Vector Control with Synthetic Jet Technology
- The Effect of TiO2 on Engine Emissions for Gas Turbine engine Fueled with jatropha, butanol, Soya and Rapeseed Oil
