CFD Modeling of Mixed-Phase Icing
-
Lifen Zhang
,
Zhenxia Liu
Abstract
Ice crystal ingestion at high altitude has been reported to be a threat for safe operation of aero-engine in recently. Ice crystals do not accrete on external surface because of cold environment. But when they enter the core flow of aero-engine, ice crystals melt partially into droplets due to higher temperature. Air-droplets-ice crystal is the mixed-phase, which will give rise to ice accretion on static and rotating components in compressor. Subsequently, compressor surge and engine shutdowns may occur. To provide a numerical tool to analyze this in detail, a numerical method was developed in this study. The mixed phase flow was solved using Eulerian–Lagrangian method. The dispersed phase was represented by one-way coupling. A thermodynamic model that considers mass and energy balance with ice crystals and droplets was presented as well. The icing code was implemented by the user-defined function of Fluent. The method of ice accretion under mixed-phase conditions was validated by comparing the results simulated on a cylinder with experimental data derived from literature. The predicted ice shape and mass agree with these data, thereby confirming the validity of the numerical method developed in this research for mixed-phase conditions.
Funding statement: Funding: National Natural Science Foundation of China (grant No. 51406167), Fundamental Research Funds for the Central Universities (No. 3102014JCQ01051).
Acknowledgements
The authors would like to thank National Natural Science Foundation of China (grant No. 51406167) and the Fundamental Research Funds for the Central Universities (No. 3102014JCQ01051) for their supports.
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©2016 by De Gruyter
Artikel in diesem Heft
- Frontmatter
- Full-Range Mathematical Modeling of Turboshaft Engine in Aerospace
- Modeling and HIL Simulation of Flight Conditions Simulating Control System for the Altitude Test Facility
- Investigation of Detailed Flow in a Variable Turbine Nozzle
- A Study on the Installed Performance Seeking Control for Aero-Propulsion under Supersonic State
- Study of the Standard k-ε Model for Tip Leakage Flow in an Axial Compressor Rotor
- Experimental Study of Propulsion Performance by Single-Pulse Rotating Detonation with Gaseous Fuels-Oxygen Mixtures
- Finite Element Analysis for Turbine Blades with Contact Problems
- CFD Modeling of Mixed-Phase Icing
- Effect of Steam Addition on the Flow Field and NOx Emissions for Jet-A in an Aircraft Combustor
- An Integrated Optimization Design Method Based on Surrogate Modeling Applied to Diverging Duct Design
- Numerical Study of Unsteady Properties of Ethylene/Air Turbulent Jet Diffusion Flame with Detached Eddy Simulation
- Influence of Rotor-Stator Interaction on Flow Stability in Centrifugal Pump Based on Energy Gradient Method
Artikel in diesem Heft
- Frontmatter
- Full-Range Mathematical Modeling of Turboshaft Engine in Aerospace
- Modeling and HIL Simulation of Flight Conditions Simulating Control System for the Altitude Test Facility
- Investigation of Detailed Flow in a Variable Turbine Nozzle
- A Study on the Installed Performance Seeking Control for Aero-Propulsion under Supersonic State
- Study of the Standard k-ε Model for Tip Leakage Flow in an Axial Compressor Rotor
- Experimental Study of Propulsion Performance by Single-Pulse Rotating Detonation with Gaseous Fuels-Oxygen Mixtures
- Finite Element Analysis for Turbine Blades with Contact Problems
- CFD Modeling of Mixed-Phase Icing
- Effect of Steam Addition on the Flow Field and NOx Emissions for Jet-A in an Aircraft Combustor
- An Integrated Optimization Design Method Based on Surrogate Modeling Applied to Diverging Duct Design
- Numerical Study of Unsteady Properties of Ethylene/Air Turbulent Jet Diffusion Flame with Detached Eddy Simulation
- Influence of Rotor-Stator Interaction on Flow Stability in Centrifugal Pump Based on Energy Gradient Method
