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Wen H.,Jiangsu University of Science and Technology | Sang J.,Jiangsu University of Science and Technology | Zhong Q.,Jiangsu University of Science and Technology | Liu H.,Chongqing Jiangjin Shipbuilding Industry Co.
UPB Scientific Bulletin, Series D: Mechanical Engineering | Year: 2015

In this paper the turbulence dynamics and the noise source of a centrifugal turbocharger compressor were analyzed using Computational Fluid Dynamics (CFD) techniques. The effects of the diffuser radius and the inlet angle of vane leading edge on the aerodynamic performance were also researched. In order to increase the static pressure recovery coefficient and reduce the total pressure loss coefficient, one kind optimized diffuser was developed. The results show that: The static pressure recovery coefficient and the total pressure loss coefficient increase gradually in the radial direction. The regions of the separate flows, the secondary flows and the wake flows are the main noise sources in diffuser; the shedding of thick boundary layer and the vortex motion result in the high-level noise. © 2015, Politechnica University of Bucharest. All rights reserved.

Sang J.-J.,Jiangsu University of Science and Technology | Wen H.-B.,Jiangsu University of Science and Technology | Liu H.-D.,Chongqing Jiangjin Shipbuilding Industry Co. | Yang X.-L.,Jiangsu University of Science and Technology
Neiranji Gongcheng/Chinese Internal Combustion Engine Engineering | Year: 2015

Based on the Reynolds-averaged Navier-Stokes equations and Realizable k-ε two-equation turbulence model, simulation model of the compressible flow of the internal air in a turbocharger compressor was built by CFD software. The function of the charging pressure ratio and compressor efficiency with the flow rate was analyzed under different operating couditions, and the distribution and interaction effect of the velocity and pressure in the rotor region and diffusion region were further studied. The analytical results show that the highest efficiency of the compressor is achieved at 28 200 r/min. The air backflow induced by the meiobar at the middle of the pressure side of the main blades, and the air turbulence induced by the meiobar at the suction side of the main blades are the two main causes for influencing the compressor efficiency. The flow characteristics at the blade leading edge are different from that of the afterbody. The vortex loss appears at the inlet of the diffuser easily. © 2015, Chinese Society for Internal Combustion Engines. All right reserved.

Wen H.-B.,Jiangsu University of Science and Technology | Xu W.-J.,Chongqing Jiangjin Shipbuilding Industry Co. | Bao S.-N.,Jiangsu University of Science and Technology | Xia Z.-W.,Jiangsu University of Science and Technology
Neiranji Gongcheng/Chinese Internal Combustion Engine Engineering | Year: 2013

Noise generation mechanism of the marine diesel engine turbocharger was discussed, and an experimental study on the spectrum analysis and sound intensity identification of dominant noise source was carried out. The results show that the spectrum of aerodynamic noise at compressor entrance consists of narrowband tip clearance noise (TCN), discrete blade passing frequency (BPF) noise and its harmonics. The volute radiation noise is primarily generated by the volute structural vibration, caused by TCN and rotor shaft frequency and its harmonics. The turbocharger noise energy distributes in a wide range of 1000~8000 Hz, and the acoustical power increases about 20 dB, almost linearly with the rotating speed increasing from 50% to rated value.

Yang C.-L.,ChongQing JiangJin Shipbuilding Industry Co | Yang C.-L.,Chongqing University | Yang C.-L.,Harbin Engineering University | Wang G.-J.,Chongqing University | And 2 more authors.
Applied Mechanics and Materials | Year: 2014

Numerical simulation method is adopted to simulate and research Self-Recirculation Casing Treatment(SRCT) on expanding the scope of steady work of high-pressure-ratio centrifugal compressor, and increase the compressor surge margin. Contrast the influences which are caused by structure sizes of the SRCT on the performance of compressor. The results showed that SRCT make the compressor stable operating range average broaden more than 13% on all kinds of speed, the surge margin increased by 11% at most. During the structure sizes, the distance between the bleed slot and the splitter blade has the largest affect on the performance of centrifugal compressor, followed by the bleed slot width, others have less affect. SRCT make the distribution of the compressor impeller inlet relative Mach number is more uniform, weaken the phenomenon of blade leading edge local high Mach number. It is also decrease the blade inlet positive incidence, inhibit separation of the blade surface boundary layer. © (2014) Trans Tech Publications, Switzerland.

Zhang M.,Northwestern Polytechnical University | Gou W.,Northwestern Polytechnical University | Li L.,Northwestern Polytechnical University | Li L.,Chongqing University | And 3 more authors.
Structural and Multidisciplinary Optimization | Year: 2015

The newly designed structures are employed to improve the high pressure turbine (HPT) disk to the expected performance. The twin-web disk (TWD) has been proven to be the future trend of the HPT disk due to its breakthrough in weight loss, strength and heat transfer efficiency compared to the conventional single web disk (SWD). Because of the multi-physics working conditions and intense coupling of multiple disciplines, the conventional design of the HPT disk is a labor intensive work. A series of design procedures, including asymmetrical computational fluid dynamics (CFD) analysis, inverse distance weighted (IDW) interpolation method, multidisciplinary feasible method (MDF), and design of experiments (DOE), are proposed to obtain the proper design for both TWD and SWD in an efficient way. In the present work, the multidisciplinary design of optimization (MDO) has been performed to find the proper shape of the TWD disk with the minimum mass. The results showed that the TWD exhibits a better performance in heat transfer and weight loss than SWD. The modeling and optimization procedure of this work can be referred for engineering design. © 2015 Springer-Verlag Berlin Heidelberg

Tong F.,Northwestern Polytechnical University | Gou W.,Northwestern Polytechnical University | Li L.,Northwestern Polytechnical University | Li L.,Chongqing Jiangjin Shipbuilding Industry Co. | And 4 more authors.
Advances in Mechanical Engineering | Year: 2015

In this article, the effects of film cooling holes arrangement and groove depth on the heat transfer and film cooling performance of blade tip are investigated. For this numerical research, a high-pressure turbine blade with the squealer tip is applied, and the tip clearance is given to be 0.8€‰mm (1% of the blade span). Simultaneously, a typical tip cooling technology of film holes in the groove floor is used. The number of film holes is fixed at 10, and two kinds of holes arrangements are considered: (1) equidistance distribution and (2) dense distribution near the leading edge. Three groove depths are studied with the values of 1.5, 2.0, and 2.5€‰mm (1.875%, 2.5%, and 3.125% of the blade span, respectively). The results show that the area-averaged film cooling effectiveness is higher when the holes distribute densely near the leading edge, and the cooling effect of the groove depth with 2.0€‰mm is obviously high compared with the other two depths. © 2015 SAGE Publications Ltd, unless otherwise noted. Manuscript content on this site is licensed under Creative Commons Licenses.

Liu C.,Harbin Engineering University | Cao Y.,Harbin Engineering University | Zhang W.,Harbin Engineering University | Ming P.,Harbin Engineering University | Liu Y.,Chongqing Jiangjin Shipbuilding Industry Co.
ICSV 2016 - 23rd International Congress on Sound and Vibration: From Ancient to Modern Acoustics | Year: 2016

Turbocharger aerodynamic noise has been one of the major noise sources of the diesel generator of the ship, which not only increases the environmental pollution, but also does harm to the crew health. Therefore, it is of vital necessity to study the noise characteristics before the control. In this paper, the aerodynamic noise prediction of marine turbocharger compressor was made by using Computational Fluid Dynamics (CFD) and Indirect Boundary Element Method (IBEM). The mesh of single stator and rotor blade passage was divided, and the unsteady viscous flow in the centrifugal compressor was simulated based on the finite volume method. Besides, the boundary element model of the volute was established in order to take the scattering effect on sound propagation into account. The pressure fluctuation of rotor inlet plane was monitored and the data was used as sound source information in acoustic calculation, the radiation noise field of compressor was predicted by IBEM. A series of experiments about turbocharger noise was designed and performed, and the sound pressure of the turbocharger radiation noise field was measured. Finally, through comparing the results of numerical simulation with the experiment values, the noise spectrum agrees well with them. Therefore, the coupling method combining CFD and IBEM can be used for compressor noise calculations.

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