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Shock Wave Induced Separation Control By Streamwise Vortices

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Journal of Thermal Science 2005年第3期14卷 249-253页

作者： ryszard szwaba Technical University of Liberec Faculty of Mechanical Engineering Division of Power Engineering. Halkova 6 461 17 Liberec Czech Republic

Control of shock wave and boundary layer interaction finds still a lot of attention. Methods of this interaction control have been especially investigated in recent decade. This research was mostly concerned with flows without separation. However, in many applications shock waves induce separation often leads to strong unsteady effects. In this context it is proposed to use streamwise vortices for the interaction control. The results of experimental investigations are presented here. The very promising results were obtained, meaning that the incipient separation was postponed and the separation size was reduced for the higher Mach numbers. The decrease of the RMS of average shock wave oscillation was also achieved.

关键词：震动波边界层分离控制流动性旋涡

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

Flow Structure and Heat Exchange Analysis in Internal Cooling Channel of Gas Turbine Blade

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Journal of Thermal Science 2016年第4期25卷 336-341页

作者： ryszard szwaba Piotr Kaczynski Piotr Doerffer Janusz Telega Institute of Fluid-Flow Machinery Polish Academy of Sciences(IMP PAN)

This paper presents the study of the flow structure and heat transfer,and also their correlations on the four walls of a radial cooling passage model of a gas turbine blade.The investigations focus on heat transfer and aerodynamic measurements in the channel,which is an accurate representation of the configuration used in aeroengines.Correlations for the heat transfer coefficient and the pressure drop used in the design of radial cooling passages are often developed from simplified models.It is important to note that real engine passages do not have perfect rectangular cross sections,but include coiner fillet,ribs with fillet radii and special orientation.Therefore,this work provides detailed fluid flow and heat transfer data for a model of radial cooling geometry which possesses very realistic features.

关键词：冷却通道流动结构燃气轮机叶片换热分析发动机结构传热特性通道模型圆角半径

Influence of Internal Channel Geometry of Gas Turbine Blade on Flow Structure and Heat Transfer

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Journal of Thermal Science 2017年第6期26卷 514-522页

作者： ryszard szwaba Piotr Kaczynski Janusz Telega Piotr Doerffer Institute of Fluid-Flow Machinery Polish Academy of Sciences (IMP PAN) Fiszera 14 80-952 Gdansk POLAND

This paper presents the study of the influence of channel geometry on the flow structure and heat transfer, and also their correlations on all the walls of a radial cooling passage model of a gas turbine blade. The investigations focus on the heat transfer and aerodynamic measurements in the channel, which is an accurate representation of the configuration used in aeroengines. Correlations for the heat transfer coefficient and the pressure drop used in the design of internal cooling passages are often developed from simplified models. It is important to note that real engine passages do not have perfect rectangular cross sections, but include a corner fillets, ribs with fillet radii and a special orientation. Therefore, this work provides detailed fluid flow and heat transfer data for a model of radial cooling geometry which has very realistic features.

关键词：流动结构几何形状燃气轮机叶片传热流道发动机结构通道模型冷却通道

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

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 proposed.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.Near the sidewalls the suction slots are applied for the corner flow structure control.It allows to control the Axial Velocity Density Ratio(AVDR),important parameter for compressor cascade investigations.Numerical results for Explicit Algebraic Reynolds Stress Model with transition modeling are compared with oil flow visualization,schlieren and Pressure Sensitive Paint.Boundary 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