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Streamwise vortex generation by the rod

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Chinese Journal of Aeronautics 2019年第8期32卷 1903-1911页

作者： Ryszard SZWABA pawel flaszynski Piotr DOERFFER Department of Experimental Aerodynamics Institute of Fluid Flow Machinery Polish Academy of Sciences

The technology development related to aerodynamics is leading to ever increasing loads of wings, airfoils and turbine and compressor blades. The increase in aerodynamic forces is often leading to flow separation and depreciation of the aerodynamic performance of flying objects or propulsion systems. Flow control methods are required to avoid these negative effects. In the recent two decades the flow control by means of air-jet vortex generators has been also intensively investigated. In this method a streamwise vortex is introduced by an oblique jet. The necessity to supply air by a pipe system may be considered a disadvantage. In order to eliminate this feature, it has been proposed to put out a rod instead of a jet. It has been shown that the application of a rod can introduce the same effect as a jet, as long as the streamwise vortex generation is concerned and appropriate dimensions are used. The present paper focuses on the influence of rod vortex generators on a flow pattern downstream. The results presented here concern experimental and numerical investigations and provide guidelines for the design of a new flow control method dedicated mainly to external flows.

关键词： Air-jet vortex generator Boundary layer Flow control Rod vortex generator Streamwise vortices

Streamwise Vortex Interaction with a Horseshoe Vortex

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Journal of Thermal Science 2003年第4期12卷 304-309页

作者： Piotr Doerffer pawel flaszynski Franco Magagnato IMP PAN Fiszera 14 PL-80 952 Gdansk PolandIMP PAN Fiszera 14 PL-80 952 Gdansk PolandFGS Karlsruhe University Kaiserstr.12 D-76 128 Karlsruhe Germany

Flow control in turbomachinery is very difficult because of the complexity of its fully 3-D flow structure. The authors propose to introduce streamwise vortices into the control of internal flows. A simple configuration of vortices was investigated in order to better understand the flow control methods by means of streamwise vortices. The research presented here concerns streamwise vortex interaction with a horseshoe vortex. The effects of such an interaction are significantly dependent on the relative location of the streamwise vortex in respect to the leading edge of the profile. The streamwise vortex is induced by an air jet. The horseshoe vortex is generated by the leading edge of a symmetric profile. Such a configuration gives possibility to investigate the interaction of these two vortices alone. The presented analysis is based on numerical simulations by means of N-S compressible solver with a two-equation turbulence model.

关键词：流体控制马蹄形涡流溪流形涡流三维流体结构数值模拟空气动力学

Shock Wave Boundary Layer Interaction on Suction Side of Compressor Profile in Single Passage Test Section

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Journal of Thermal Science 2015年第6期24卷 510-515页

作者： pawel flaszynski Piotr Doerffer Ryszard Szwaba Piotr Kaczynski Michal Piotrowicz The Szewalski Institute of Fluid-Flow Machinery Polish Academy of Sciences (IMP PAN)

The shock wave boundary layer interaction on the suction side of transonic compressor blade is one of the main objectives of TFAST project(Transition Location Effect on Shock Wave Boundary Layer Interaction).In order to investigate the flow structure on the suction side of a profile,a design of a generic test section in linear transonic wind tunnel was *** experimental and numerical results for the flow structure investigations are shown for the flow conditions as the existing ones on the suction side of the compressor *** the sidewalls the suction slots are applied for the corner flow structure *** allows to control the Axial Velocity Density Ratio(AVDR),important parameter for compressor cascade *** results for Explicit Algebraic Reynolds Stress Model with transition modeling are compared with oil flow visualization,schlieren and Pressure Sensitive *** layer transition location is detected by Temperature Sensitive Paint.

关键词：边界层转捩压气机叶片相互作用激波试验段单通道跨音速风洞外形

Laminar-Turbulent Transition Tripped by Step on Transonic Compressor Profile

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Journal of Thermal Science 2018年第1期27卷 1-7页

作者： pawel flaszynski Piotr Doerffer Ryszard Szwaba Michal Piotrowicz Piotr Kaczynski The Szewalski Institute of Fluid-Flow Machinery Polish Academy of Sciences(IMP PAN) Fiszera 14GdanskPoland

The shock wave boundary layer interaction on the suction side of transonic compressor blade is one of the main objectives of TFAST project(Transition Location Effect on Shock Wave Boundary Layer Interaction). The experimental and numerical results for the flow structure investigations are shown for the flow conditions as the existing ones on the suction side of the compressor profile. The two cases are investigated: without and with boundary layer tripping device. In the first case, boundary layer is laminar up to the shock wave, while in the second case the boundary layer is tripped by the step. Numerical results carried out by means of Fine/Turbo Numeca with Explicit Algebraic Reynolds Stress Model including transition modeling are compared with schlieren, Temperature Sensitive Paint and wake measurements. Boundary layer transition location is detected by Temperature Sensitive Paint.

关键词：压缩机侧面音速相互作用流动条件温度敏感边界层冲击波