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Numerical Simulation of Unsteady Boundary Layer in Turbomachinery

Author: JiaoHuaBin
Tutor: GeNing
School: Nanjing University of Aeronautics and Astronautics
Course: Aerospace Propulsion Theory and Engineering
Keywords: Turbine Unsteady flow SA model Transition Separate
CLC: V231.3
Type: Master's thesis
Year: 2009
Downloads: 101
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Abstract


Turbomachinery internal flow is very complex, only the steady-state full of traditional methods turbomachinery turbulent boundary layer flow numerical simulation obviously does not meet the engineering requirements. Firstly, based on methods for solving Reynolds averaged Navier-Stokes equations , turbulence models will generate original SA items seen as a transport variables, numerical simulation additional transport equations to consider the introduction of its flow in the transition phenomenon . The finite volume method for spatial discretization , upwind Roe flux difference splitting method and calculation of third-order MUSCL format for liquidity , the viscous fluxes using second-order central difference discretization , while introducing low pretreatment technology . Developed a machine for solving complex flow impeller unsteady numerical method . Secondly , the choice of boundary layer transition flow , steady / unsteady flow separation under the channel separation and cascade flow , the method is numerically validated through comparisons with experimental data revealed that the method is not only common side turbine Lu transition a better prediction performance, but also for steady / unsteady separation of the boundary layer separation point under the conditions and the separation -induced transition simulation also has some accuracy for complex turbomachinery flow simulation provides a simple and efficient numerical methods . Finally, the simulation results show that the boundary layer separation , separation bubble cascade channel size of the turbine has an important impact on the performance , when the separation bubble is small separation bubble , the bubble will lead to separation of the boundary layer from laminar flow rapidly converted into turbulence kinetic energy inside the boundary layer increased flow easily separated on turbine performance improvement plays a positive role. When the separation bubble for the long separation bubble , because of the presence of separation bubbles within the flow area of ??the channel to promote change, channel work at off-design conditions , flow losses increased.

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CLC: > Aviation, aerospace > Aviation > Aero-engine ( propulsion system ) > Engine theory > Aero-engine gas mechanics
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