The effective control of the tip-leakage flow and loss is of great significance to improve the aerodynamic performance of the turbine.In this paper,the evolution mechanism of tip-leakage flow in a transonic high press...The effective control of the tip-leakage flow and loss is of great significance to improve the aerodynamic performance of the turbine.In this paper,the evolution mechanism of tip-leakage flow in a transonic high pressure turbine with a squealer tip is investigated with numerical simulation methods.The impacts of squealer geometric,such as the inclined pressure side rim and squealer rim width,on the vortex structure in the gap and tip-leakage loss are discussed.The results show that the scraping vortex inside the cavity plays the role of aero-labyrinth seal,and forms interlocking sealing labyrinth structure with the rims on both sides,which has an effective sealing effect on the tip-leakage flow.The inclined pressure side squealer rim inhibits the development of the pressure side squealer corner vortex,which is beneficial to expand the influence range of the scraping vortex and enhance the sealing effect on the tip-leakage flow.The increase of the suction side squealer rim width reduces the effective flow area at the gap exit,which is conducive to reduction of the tip-leakage flow rate and tip-leakage loss.However,the increase of the pressure side squealer rim width strengthens the pressure side squealer corner vortex and limits the development space of the scraping vortex,causing the adverse effects on the control of tip-leakage flow.展开更多
The accurate simulation of boundary layer transition process plays a very important role in the prediction of turbine blade temperature field. Based on the Abu-Ghannam and Shaw （AGS） and c-Re h transition models, a ...The accurate simulation of boundary layer transition process plays a very important role in the prediction of turbine blade temperature field. Based on the Abu-Ghannam and Shaw （AGS） and c-Re h transition models, a 3D conjugate heat transfer solver is developed, where the fluid domain is discretized by multi-block structured grids, and the solid domain is discretized by unstructured grids. At the unmatched fluid/solid interface, the shape function interpolation method is adopted to ensure the conservation of the interfacial heat flux. Then the shear stress transport （SST） model, SST ＆ AGS model and SST ＆ c-Re h model are used to investigate the flow and heat transfer characteristics of Mark II turbine vane. The results indicate that compared with the full turbulence model （SST model）, the transition models could improve the prediction accuracy of temperature and heat transfer coefficient at the laminar zone near the blade leading edge. Compared with the AGS transition model, the c-Re h model could predict the transition onset location induced by shock/boundary layer interaction more accurately, and the prediction accuracy of temperature field could be greatly improved.展开更多
For the numerical simulation of flow systems with various complex components, the traditional one-dimensional （1D） network method has its comparative advantage in time consuming and the CFD method has its absolute a...For the numerical simulation of flow systems with various complex components, the traditional one-dimensional （1D） network method has its comparative advantage in time consuming and the CFD method has its absolute advantage in the detailed flow capturing. The proper coupling of the advantages of different dimensional methods can strike balance well between time cost and accuracy and then significantly decrease the whole design cycle for the flow systems in modern machines. A novel multi-fidelity coupled simulation method with numerical zooming is developed for flow systems. This method focuses on the integration of one-, two-and three-dimensional codes for various components. Coupled iterative process for the different dimensional simulation cycles of sub-systems is performed until the concerned flow variables of the whole system achieve convergence. Numerical zooming is employed to update boundary data of components with different dimen-sionalities. Based on this method, a highly automatic, multi-discipline computing environment with integrated zooming is developed. The numerical results of Y-Junction and the air system of a jet engine are presented to verify the solution method. They indicate that this type of multi-fidelity simulationmethod can greatly improve the prediction capability for the flow systems.展开更多
基金support of the National Science Foundation of China(No.51406003)the National Science and Technology Major Project(J2019-II-0019-040)。
文摘The effective control of the tip-leakage flow and loss is of great significance to improve the aerodynamic performance of the turbine.In this paper,the evolution mechanism of tip-leakage flow in a transonic high pressure turbine with a squealer tip is investigated with numerical simulation methods.The impacts of squealer geometric,such as the inclined pressure side rim and squealer rim width,on the vortex structure in the gap and tip-leakage loss are discussed.The results show that the scraping vortex inside the cavity plays the role of aero-labyrinth seal,and forms interlocking sealing labyrinth structure with the rims on both sides,which has an effective sealing effect on the tip-leakage flow.The inclined pressure side squealer rim inhibits the development of the pressure side squealer corner vortex,which is beneficial to expand the influence range of the scraping vortex and enhance the sealing effect on the tip-leakage flow.The increase of the suction side squealer rim width reduces the effective flow area at the gap exit,which is conducive to reduction of the tip-leakage flow rate and tip-leakage loss.However,the increase of the pressure side squealer rim width strengthens the pressure side squealer corner vortex and limits the development space of the scraping vortex,causing the adverse effects on the control of tip-leakage flow.
基金National Natural Science Foundation of China(Grant No.91130013)Innovation Foundation of BUAA for PhD Graduates(YWF-12-RBYJ-010)Specialized Research Fund for the Doctoral Program of Higher Education(20101102110011)for funding this work
文摘The accurate simulation of boundary layer transition process plays a very important role in the prediction of turbine blade temperature field. Based on the Abu-Ghannam and Shaw （AGS） and c-Re h transition models, a 3D conjugate heat transfer solver is developed, where the fluid domain is discretized by multi-block structured grids, and the solid domain is discretized by unstructured grids. At the unmatched fluid/solid interface, the shape function interpolation method is adopted to ensure the conservation of the interfacial heat flux. Then the shear stress transport （SST） model, SST ＆ AGS model and SST ＆ c-Re h model are used to investigate the flow and heat transfer characteristics of Mark II turbine vane. The results indicate that compared with the full turbulence model （SST model）, the transition models could improve the prediction accuracy of temperature and heat transfer coefficient at the laminar zone near the blade leading edge. Compared with the AGS transition model, the c-Re h model could predict the transition onset location induced by shock/boundary layer interaction more accurately, and the prediction accuracy of temperature field could be greatly improved.
基金National Weapon Equipment Pre-research Foundation of China(0C410101110C4101)Innovation Foundation of BUAA for PhD Graduates(YWF-13-A01-15)for funding this work
文摘For the numerical simulation of flow systems with various complex components, the traditional one-dimensional （1D） network method has its comparative advantage in time consuming and the CFD method has its absolute advantage in the detailed flow capturing. The proper coupling of the advantages of different dimensional methods can strike balance well between time cost and accuracy and then significantly decrease the whole design cycle for the flow systems in modern machines. A novel multi-fidelity coupled simulation method with numerical zooming is developed for flow systems. This method focuses on the integration of one-, two-and three-dimensional codes for various components. Coupled iterative process for the different dimensional simulation cycles of sub-systems is performed until the concerned flow variables of the whole system achieve convergence. Numerical zooming is employed to update boundary data of components with different dimen-sionalities. Based on this method, a highly automatic, multi-discipline computing environment with integrated zooming is developed. The numerical results of Y-Junction and the air system of a jet engine are presented to verify the solution method. They indicate that this type of multi-fidelity simulationmethod can greatly improve the prediction capability for the flow systems.
