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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

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. Source

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

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. Source

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

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. Source

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

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 Source

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

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. Source

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