Improvement for Unstructured Grid Generation and Calculations of Three-Dimensional Turbulent Flow around Turbine Stator Blade Rows with Film Cooling
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Improvement for Unstructured Grid Generation and Calculations of Three-Dimensional Turbulent Flow around Turbine Stator Blade Rows with Film Cooling
Vol. 16, Issue 3, (2001)
作者机构:
1. 清华大学工程力学系,北京,100084
2. 海军航空工程学院青岛分院数学教研室,山东,青岛,266041
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Published:2001
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WANG Bao-guo, LI Rong-xian, MA Zhi-ming, et al. Improvement for Unstructured Grid Generation and Calculations of Three-Dimensional Turbulent Flow around Turbine Stator Blade Rows with Film Cooling[J]. 2001, 16(3).
DOI:
WANG Bao-guo, LI Rong-xian, MA Zhi-ming, et al. Improvement for Unstructured Grid Generation and Calculations of Three-Dimensional Turbulent Flow around Turbine Stator Blade Rows with Film Cooling[J]. 2001, 16(3).DOI:
Improvement for Unstructured Grid Generation and Calculations of Three-Dimensional Turbulent Flow around Turbine Stator Blade Rows with Film Cooling
The generation of prismatic unstructured grid for complex3 D geometries and the application of a new high resolution algorithm for the unstructured grids have been developed in consideration of the engineering background.The unstructured grids are generated on one given S1 surface (i.e.a surface of constant x3 in a three dimensional curved coordinate ( x1
x2
x3)
while the grids on the other S1 surfaces are constructed by a space mapping.The final grids obtained in this way become unstructured on S1 surfaces and structured in x3 direction.Therefore they are composed of pentahedrons.In the generation of the grid on the S1 surface
the triangle elements of 0 type grid are created near the walls.By improving Bowyer Watson method
a scheme of high efficiency is developed to produce unstructured grids in the region far from the walls.The new algorithm consists of a high resolution finite volume scheme for the 3 D Navier Stokes turbulent flow equations.Spatial discretization uses a finite volume.High order Taylor series expansion is employed to march the solution in time.Spacial volume and time step weighting of the residual are employed to produce a stable scheme.A second order smoothing operator and the minmod limiter are developed for shock capturing.The operator retains its order with unstructured grids.Some typical numerical examples
including a turbine stator blade row with film cooling
demonstrate the ability of the algorithm to resolve local flow features.
Numerical simulation for flow field of helicopters based on WENO-piecewise linear scheme
Application strategy and improvement of unstructured dynamic grid method based on elasticity analogy
Research on limiters of unstructured grid
Numerical simulation and comparison of aerodynamic characteristics between ducted and isolated propellers
Numerical simulation of interaction unsteady flows around co-axial rotors in hover
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