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Effects of Airfoil-probe Tubes on the Flow Field of a Compressor Cascade

Journal of Thermal Science 2017年第4期26卷 321-330页

作者： MA Hongwei JIN Chao ZHAO Lianpeng MA Rong National Key Laboratory of Science and Technology on Aero-Engines Collaborative Innovation Center of Advanced Aero-EngineSchool of Energy&Power EngineeringBeihang UniversityBeijing100191China

To explore the effects of airfoil-probe tubes and its installment position on the flow field of the compressor cas- cade, and find out the mechanism that how the airfoil-probes affect the aerodynamic characteristics of the com- pressor cascade, this paper performed both numerical and experimcntal works on the same compressor cascade. The experiment mainly focused on the cases of low Mach number （Ma = 0.1）, and cases with different Mach numbers （0.1, 0.3, 0.7） and different incidence angles （-5, 0, 5） are investigated by the numerical method. The case without the airfoil-probe tube was referenced as the baseline, and other three cases with the airfoil-probe tubes installed in different chordwise positions O0%, 50%, 70% of the chord length） were studied. The diameter of the airfoil-probe tube is 3ram, which is configured as 300% amplification of some particular airfoil-probe ac- cording to the geometrical similarity principle. The results show that the airfoil-probe tubes have a negative in- fluenc~ on the flow capacity of the cascade at all investigation points. The separations and the large scale stream- wise vortices that induced by the airfoil-probe tube on the pressure side cause most the losses at the high Mach number. The influence of the airfoil-probe tube on the flow field in the vicinity of the pressure side surface is lo- cal separation at the low Mach number. The airfoil-probe tubes also have a clearly effect on the leakage flow. It decreases the mass flow of the leakage flow and weakens the intensity of the leakage vortex, but enlarges the in- fluence area. The total pressure loss of the case that the tube is installed at the half chordwise position is generally lower than other cases especially at the high Mach number, it can even decrease the losses compared with the ba- sic case.

关键词： airfoil-probe compressor cascade installment position 5-hole probe

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Effects of Suction Side Squealer Tip on the Performance of a Low-Speed Axial Compressor

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Journal of Thermal Science 2012年第3期21卷 223-229页

作者： Jun Zhang Hongwei Ma Jingyang Li School of Jet Propulsion Beihang UniversityXueyuan Road 37BeijingChina Shenyang Aeroengine Research Institute Aviation Industry Corporation of ChinaShenyangChina

This paper presents the investigation of the effects of suction side squealer tip on the performance of an axial compressor. The experiment is carded out in a single-stage large-scale low-speed compressor. The investigated tip geometries include fiat tip as the baseline and suction side squealer tip. The tip clearance of the baseline is 0.5% of the blade span. The static pressure rise characteristic curves of both the rotor and the stage are measured. The flow field at the exit of the rotor is measured by a 5-hole probe under design and off-design conditions. The static pressure on the endwall of the rotor passage is also obtained. The results show that the pressure rise characteristic curves obtained by measuring the pressure on the end wall are almost unchanged by using the suction side squealer tip. The measuring results of the 5-hole probe show the static pressure and the total pressure in tip region is slightly greater than that of the flat tip at the design condition at the exit of the rotor. It also leads to greater averaged static pressure rise and total pressure. At the near stall condition, the averaged static pressure and total pressure is lower than the baseline which is related to the redistribution of the blade load caused by the suction side squealer tip.

关键词： Compressor squealer tip 5-hole probe off-design condition tip leakage flow.

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Experimental Investigation of Effects of Distributed Riblets on Aerodynamic Performance of a Low-speed Compressor

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Journal of Thermal Science 2013年第6期22卷 592-599页

作者： MA Hongwei WEI Wei National Key Laboratory of Science and Technology on Aero-Engines School of Energy and Power EngineeringBeihang University

It is well known that riblet applied on compressor blades is a promising flow control technique. However, detailed investigation of its effects on the flow field of turbomachinery is rare in existing literatures. This paper presents a detailed experimental investigation of effects of distributed riblet on the flow field of an axial compressor iso- lated-rotor stage. The research was performed in a large-scale facility respectively with two configurations, in- eluding grooved hub, and grooved surface on both hub and partial suction surface. The riblet film is rectangle grooved type with a height of 0.1 ram. The flow field at 10% chord downstream from the cascade trailing edge was measured using a mini five-hole pressure probe and a total pressure probe. The testing was conducted at sev- eral operational points under two reduced rotational speeds. Stagnation pressure loss in rotational frame was cal- culated and compared with the control test in which a smooth film was applied to the corresponding position. Results show that with the grooved hub configuration at the design operation point of the lower rotational speed, the riblet film provides an obvious improvement of a 48% reduction of total pressure loss in rotational frame. Also, a distinct weaken hub comer vortex was identified. In the meantime, there exists a deviation of flow angle about 5 degrees at 20%-80% span which previously was not considered to be the affected region.

关键词： distributed riblet large-scale compressor hub corner vortex loss reduction.

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PIV Measurements of Coolant Flow Field in a Diesel Engine Cylinder Head

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Journal of Thermal Science 2015年第2期24卷 179-184页

作者： MA Hongwei ZHANG Zhenyang XUE Cheng HUANG Yunlong National Key Laboratory of Science and Technology on Aero-engines Collaborative Innovation Center of Advanced Aero-EngineSchool of Energy and Power EngineeringBeihang University China North Engine Research Institute

This paper presents experimental measurements of coolant flow field in the water jacket of a diesel engine cylinder head. The test was conducted at three different flow rates using a 2-D PIV system. Appropriate tracing particles were selected and delivery device was designed and manufactured before the test. The flow parameters, such as velocity, vorticity and turbulence, were used to analyze the flow field. The effects of vortex which was located between the intake valve and the exhaust valve were discussed. The experimental results showed an asymmetric distribution of velocity in the water jacket. This led to an asymmetric thermal distribution, which would shorten the service life of the cylinder head. The structure optimization to the water jacket of cylinder head was proposed in this paper. The experimental system, especially the 2-D PIV system, is a great help to study the coolant flow structure and analyze cooling mechanism in the diesel engine cylinder head.

关键词： coolant flow cylinder head PIV

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Effects of a Kind of Non-smooth blade on the Unsteady Flow Field at the Exit of an Axial Fan

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Journal of Thermal Science 2008年第1期17卷 1-6页

作者： Hongwei MA Jibo GUO School of Jet Propulsion Beijing University of Aeronautics and Astronautics Beijing 100083 China National Key Laboratory on Aero-Engines Beijing 100083 China

An experimental investigation of effects of a kind of streamwise-grooved blade on the unsteady flow field at an exit of an axial-flow fan was performed. The flow field at 25% chord downstream from the trailing edge at hub was measured using a fast-response five-hole pressure probe at different mass-flow conditions. The unsteady flow of the grooved blades was compared with that of the smooth blades. The measurement results indicate that：（1） the grooved blades restrain the velocity fluctuation and the pressure fluctuation by modulating the blade boundary layers, which contributes to the flow loss reduction in the hub region and in the rotor wake region at the design condition; （2） the stream-wise grooves play an important role in restraining the radial migration in the blade boundary layer and abating the tip flow mixing, which contributes to the flow loss reduction in the tip region at the design condition; （3） at the near stall condition, the grooved surface can not reduce the flow loss, even increase the loss nearby when the separation happens in the blade boundary layer.

关键词： axial fan non-smooth blade stream-wise groove unsteady flow.

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Experimental Investigation of Effects of Suction-Side Squealer Tip Geometry on the Flow Field in a Large-scale Axial Compressor using SPIV

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Journal of Thermal Science 2015年第4期24卷 303-312页

作者： MA Hongwei WEI Wei WANG Lixiang TIAN Yangtao Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics School of Energy and Power Engineering Beihang University Collaborative Innovation Center of Advanced Aero-Engine

It is well known that the non-uniform tip geometry is a promising passive flow control technique in ***,detailed investigation of its effects on the unsteady flow field of turbomachinery is rare in the existiug *** paper presents an experimental investigation of effects of suction side squealer tip configuration on both the steady and unsteady flow field of an isolated compressor *** flow field at 10%chord downstream from the trailing edge was measured using a mini five-hole ***,the unsteady flow field inside the passage was investigated using stereo particle image velocimetry(SPIV).The steady results show that the SSQ tip configuration exerts positive effect on the static pressure rise performance of this compressor,and the radial equilibrium at the rotor outlet is obviously *** SSQ tip configuration would create a stronger tip leakage vortex at the formation phase,and it experiences a faster dissipation process around the rear ***,the splitting process of the tip leakage vortex is severer,which is the main cause of the relatively higher probability of the presence of the streamwise reverse *** quantitatively analysis of the tip leakage vortex indicates that the velocity loss inside the blockage region is direct response of the evolutionary procedure of the tip leakage *** keeps increasing until the end of the splitting *** the blockage coefficient grows sustainably,the velocity loss will reduce once the turbulent mixing procedure is dominant.

关键词： tip leakage vortex suction side squealer axial compressor SPIV instantaneous flow field

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Effects of a Kind of Surface Groove on Flow Loss in both Rectangular and Circular Ducts at Different Reynolds Numbers

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Journal of Thermal Science 2016年第5期25卷 389-393页

作者： MA Rong MA Hongwei ZHANG Zhenyang ZHANG Jinghui National Key Laboratory of Science and Technology on Aero-Engines Collaborative Innovation Center of Advanced Aero-EngineSchool of Energy & Power EngineeringBeihang University

Pipes are widely used to transport gas,oil and water in *** reduction in pipes is an increasingly concerned problem to save *** researches have indicated that the non-smooth surface with special structures can reduce flow *** this paper,an experimental investigation has been performed on the effects of a kind of surface groove on the drag in both rectangular and circular duct at different Reynolds *** the experiment of the rectangular duct,total pressure at both inlet and outlet were *** pressure on the wall was measured on the surface with smooth and grooved film *** the circular duct,a boundary layer pressure probe was used to measure the total pressure distribution at both inlet and *** taps at inlet and outlet were used to measure static *** loss coefficient is used to evaluate the effects of the surface groove on drag *** experiment was conducted with the Reynolds number range from 1.28×10~4 to 2.57×10~*** result shows a maximum drag loss reduction of approximately 2.4% in rectangular duct at Reynolds number of 2.4×10~4.A 10%reduction of pipe pressure loss by grooved surface is measured in circular duct at a Reynolds number of 3.0×10~5.

关键词： drag reduction surface groove rectangular duct circular duct

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Effects of Probe Support on the Flow Field of a Low-Speed Axial Compressor

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Journal of Thermal Science 2014年第2期23卷 120-126页

作者： MA Hongwei LI Shaohui WEI Wei National Key Laboratory of Science and Technology on Aero-engines School of Energy and Power EngineeringBeihang University

This paper presents an investigation on the effect of probe support on the flow field of an axial *** experiment is carried out in a large-scale low-speed research compressor.A cylindrical probe support intruding to 50% blade span was installed at 50% chord upstream from the rotor leading *** region from 5° to 32° off the probe support in the direction of rotation at the rotor outlet was measured with a 5-hole probe and a high-response total pressure *** experiment is performed at both near-design and near-stall *** measuring results of 5-hole probe and high-response total pressure probe indicate that the probe blockage effect is different at different blade *** wake of the probe support weakens the leakage vortex intensity at the tip region,leading to greater total pressure *** near-design condition,the presence of probe support has a negative effect on the region from 75% to 92% span,while improves the flow field below 75% *** near stall condition,the probe support has a negative effect on the region from 70% to 90% span,and almost has no influence on the flow field below 70% span.

关键词： probe support compressor 5-hole probe high-response total pressure probe tip leakage flow

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Recent advances of computational aeroacoustics

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Applied Mathematics and Mechanics(English Edition) 2015年第1期36卷 131-140页

作者： Xiao-dong LI Min JIANG Jun-hui GAO Da-kai LIN Li LIU Xiao-yan LI School of Energy and Power Engineering Beihang University beijing Aeronautical Science & Technology Research Institute of Commercial Aircraft Corporation of China beijing Institute of Space Launch Technology Research and Development Center China Academy of Launch Vehicle Technology

Computational aeroacoustics （CAA） is an interdiscipline of aeroacoustics and computational fluid dynamics （CFD） for the investigation of sound generation and propagation from various aeroacoustics problems. In this review, the foundation and research scope of CAA are introduced firstly. A review of the early advances and applications of CAA is then briefly surveyed, focusing on two key issues, namely, high order finite difference scheme and non-reflecting boundary condition. Furthermore, the advances of CAA during the past five years are highlighted. Finally, the future prospective of CAA is briefly discussed.

关键词： aeroacoustics computational aeroacoustics (CAA) high order finite difference scheme non-reflecting boundary condition

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Transient aeroelastic responses and flutter analysis of a variable-span wing during the morphing process

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Chinese Journal of Aeronautics 2013年第6期26卷 1430-1438页

作者： Huang Ren Qiu Zhiping Institute of Solid Mechanics Beihang University

To investigate the transient aeroelastic responses and flutter characteristics of a variablespan wing during the morphing process,a novel frst-order state-space aeroelastic model is *** time-varying structural model of the morphing wing is established based on the Euler-bernoulli beam theory with time-dependent boundary conditions.A nondimensionalization method is used to translate the time-dependent boundary conditions to be *** time-domain aerodynamic forces are calculated by the reduced-order unsteady vortex lattice *** morphing parameters,i.e.,wing span length and morphing speed,are of particular interest for understanding the fundamental aeroelastic behavior of variable-span wings.A test case is proposed and numerical results indicate that the flutter characteristics are sensitive to both of the two morphing *** could be noticed that the aeroelastic characteristics during the wing extracting process are more serious than those during the extending process at the same morphing speed by transient aeroelastic response *** addition,a faster morphing process can get better aeroelastic performance while the mechanism comlexity will arise.

关键词： Galerkin methods Morphing aircraft Time-varying systems Transient aeroelastic Unsteady vortex lattice method Variable-span wing

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