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| 1 | Influence of Internal Channel Geometry of Gas Turbine Blade on Flow Structure and Heat Transfer显示文摘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. | Ryszard Szwaba Piotr Kaczynski Janusz Telega Piotr Doerffer | 2017 | Journal of Thermal Science2017，26，6： | 4 |
| 2 | The Effect of Air Humidity on Shock Wave Induced Incipient Separation显示文摘During earlier research on shock wave/boundary layer interaction control, the effect of air humidity flow separation has been observed. This has inspired a more detailed study on the effect of air humidity on shock induced incipient separation and on the involved involved processes. The phenomenon has a twofold nature. In supersonic flow, the condensation of humidity causes flow retardation due to heat addition. The consequent weakening of the shock wave reduces the tendency towards separation. On the other hand, the incipient separation is postponed at the same Mach numbers of interaction. | Piotr DOERFFER Andrzej SZUMOWSKI Shen YU | 2000 | Journal of Thermal Science2000，9，1： | 4 |
| 3 | Flow Structure and Heat Exchange Analysis in Internal Cooling Channel of Gas Turbine Blade显示文摘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. | Ryszard Szwaba Piotr Kaczynski Piotr Doerffer Janusz Telega | 2016 | Journal of Thermal Science2016，25，4： | 3 |
| 4 | Shock Wave Boundary Layer Interaction on Suction Side of Compressor Profile in Single Passage Test Section显示文摘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. | Pawel Flaszynski Piotr Doerffer Ryszard Szwaba Piotr Kaczynski Michal Piotrowicz | 2015 | Journal of Thermal Science2015，24，6： | 3 |
| 5 | Streamwise vortex generation by the rod显示文摘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. | Ryszard SZWABA Pawel FLASZYNSKI Piotr DOERFFER | 2019 | Chinese Journal of Aeronautics2019，32，8： | 2 |
| 6 | Shock Wave Strength Reduction by Passive Control Using Perforated Plates显示文摘强壮的、正常冲击波,在一个机翼,不是仅仅限制上终止一个本地超声的区域空气动力学的性能而且成为高速度的冲动的直升飞机噪音的来源。转子片上的一个被动控制系统(一个穿孔盘子盖住的一个洞) 的应用程序应该减少动人的震动创造的噪音。这篇文章盖住 Bohning/Doerffer 蒸发法律的数字实现进 SPARC 代码并且为接近音速的嘴的相对简单的几何学对试验性的数据包括扩大确认。它是向与减少被动控制设备在的噪音装备的一个直升飞机转子的完整的模拟的第一个步骤徘回并且处于前面的飞行条件。 | Piotr Doerffer Oskar Szulc | 2007 | Journal of Thermal Science2007，16，2： | 2 |
| 7 | Shock Wave Smearing by Passive Control显示文摘正常冲击波,在一个机翼上终止一个本地超声的区域,限制它的表演并且成为来源高加速冲动的噪音。使用被动控制瓦解被建议冲击波。这个方法获得的流动结构的细节数字地被学习。一个新边界条件被开发了,它的应用程序的结果在嘴流动对实验被验证。崩溃被证实了并且详细说明流动细节的分析的冲击波的方法被介绍。由渐渐的压缩的一个冲击波的替换完全改变高速度的来源它的减小的冲动的噪音和熊潜力。关键词接近音速的流动 - 冲击波边界层相互作用 - 被动控制 CLC 数字 O357. | Piotr DOERFFER Oskar SZULC Rainer BOHNING | 2006 | Journal of Thermal Science2006，15，1： | 2 |
| 8 | Numerical Analysis of Shock Induced Separation Delay by Air Humidity显示文摘In this paper numerical calculations of the dry and humid air flows in the nozzle are presented. The dry air flow (adiabatic flow) and the humid air flow (flow with homogeneous condensation, diabatic flow) are modeled with the use of Reynolds Averaged Navier-Stokes (RANS) equations. The comparison of these two types of flow is carried out. The influence of the air humidity on the shock wave location and its interaction with the boundary layer is examined. Obtained numerical results present a first numerical approach of the condensation and evaporation process in transonic flow of humid air. The phenomena considered here are very complex and complicated and need further in-depth numerical analysis. | Piotr DOERFFER Slawomir DYKAS | 2005 | Journal of Thermal Science2005，14，2： | 2 |
| 9 | Secondary Flow Control and Stream wise Vortices Formation 显示文摘 | Piotr P Doerffer Jochen Amecke | 1994 | ASME Paper 94-GT-3761994，，： | 1 |
| 10 | Flow Control Effect on Unsteadiness of Shock Wave Induced Separation显示文摘In usual cases of significant pressure gradients and strong shocks, the front shock takes a fixed location along the wall, at which separation starts. Usually the rear shock is responding to vortex sheding by its deflection angle. In consequence main shock and rear shocks are moving whilst front shock is stable. The goal of the measurements presented here is to find out how the-foot behaves during shock oscillations in the case when front shock is not fixed by the pressure gradient.Unsteady shock behaviour is also investigated when air jet vortex generators(AJVG) are used. Counteraction of the separation is directly related to the influence on unsteady processes in the shock wave induced separation. | Piotr Doerffer Janusz Telega | 2013 | Journal of Thermal Science2013，22，6： | 1 |
| 11 | Study of Interaction between Supersonic Flow and Rods Surrounded by Porous Cavity显示文摘在这份报纸,一些初步的计算和实验被执行弄明白流动领域,一些杆通常在被插入到主要流动由一个多孔的洞包围了。作为结果,开始的冲击波严重地与杆,鞠躬冲击波,它的思考,和多孔的墙交往,这被发现,它很好数字地以一些条件被预言。而且,当在多孔的区域的主要流动是完全超声的时,插入杆在多孔的区域增加在上面的墙上做压力。计算也建议三杆引起最宽的吸区域。关键词冲击波 - 可压缩的流动 - 多孔的洞 - 鞠躬冲击波 - 杆 CLC 数字 O354. | Minoru YAGA Kenji YAMAMOTO Piotr DOERFFER Kenyu OYAKAWA | 2006 | Journal of Thermal Science2006，15，4： | 1 |
| 12 | Laminar-Turbulent Transition Tripped by Step on Transonic Compressor Profile显示文摘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. | Pawel Flaszynski Piotr Doerffer Ryszard Szwaba Michal Piotrowicz Piotr Kaczynski | 2018 | Journal of Thermal Science2018，27，1： | 1 |
| 13 | Streamwise Vortex Interaction with a Horseshoe Vortex显示文摘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. | Piotr Doerffer Pawel Flaszynski Franco Magagnato | 2003 | Journal of Thermal Science2003，12，4： | 0 |
| 14 | Effect of Jet Vortex Generators on Shock Wave Induced Separation on Gas Turbine Profile显示文摘The interaction between a shock wave and a boundary layer on a suction side of gas turbine profile,namely Transition Location Effect on Shock Wave Boundary Layer Interaction,was one of main objectives of TFAST project.A generic test section in a transonic wind tunnel was designed to carry out such investigations.The design criteria were to reproduce flow conditions on the profile in wind tunnel as the one existing on the suction side of the turbine guide vane.In this paper,the effect of film cooling and jet vortex generators on the shock wave boundary layer interaction and shock induced separation is presented.Numerical results for Explicit Algebraic Reynolds Stress Model with transition modeling are compared with experimental data. | FLASZYNSKI Pawel DOERFFER Piotr PIOTROWICZ Michal Szewalski | 2021 | Journal of Thermal Science2021，30，4： | 0 |
| 15 | Experimental and Analytical Analysis of Perforated Plate Aerodynamics显示文摘Perforated walls and transpiration flow play an important role in aerodynamics due to an in creasing interest inapplication of flow control by means of blowing and/or suction. An experimental study was carded out which has led to the determination of a transpiration flow characteristics in the form of a simple formula that is very useful in modelling such flows. In connection to this relation a method of 'aerodynamic porosity' determination has been proposed which is much more reliable than geometric description of the porosity. A theoretical analysis of the flow through a perforation hole was also carded out. The flow was considered as compressible and viscous.The gasdynamic analysis led us to a very similar result to the relation obtained from the experiment. The adequacy of the theoretical result is discussed in respect to the experiment. | JürgenZierep RainerBohning Piotr Doerffer | 2003 | Journal of Thermal Science2003，12，3： | 0 |
| 16 | Shock Wave-Boundary Layer Interaction in Forced Shock Oscillations显示文摘The flow in transonic diffusers as well as in supersonic air intakes becomes often unsteady due to shock wave boundary layer interaction.The oscillations may be induced by natureal separation unsteadiness or may be forced by boundary conditions.Significant improvement of CFD tools,increase of computer resources as well as development of experimental methods have again.drawn the attention of researchers to this topic.To investigate the problem forced oscillations of transonic turbulent flow in asymmetric two-dimensional Laval nozzle were considered.A viscous.perfect gas flow,was numerically simulated using the Reynolds-averaged compressible Navier-Stokes solver SPARC,employing a two-equation,eddy viscosity,turbulence closure in the URANS approach.For time-dependent and stationary flow simulations.Mach numbers upstream of the shock between 1.2and 1.4 were considered.Comparison of computed and experimental data for steady states generally gave acceptable agreement.In the case of forced oscillations.a harmonic pressure variation was prescribed at the exit plane resulting in shock wave motion.Excitation frequencies between 0 Hz and 1024Hz were investigated at the same pressure amplitude.The main result of the work carried out is the relation between the amplitude of the shock wave motion and the excitation frequency in the investigated range.Increasing excitation frequency resulted in decreasing amplitude of the shock movement.At high frequencies a natural mode of shock oscillation(of small amplitude) was observed which is not sensitive to forced excitement. | Piotr Doerffer Oskar Szulc Franco Magagnato | 2003 | Journal of Thermal Science2003，12，1： | 0 |
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