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Wang L.-L.,Hebei University of Engineering | Hou H.-J.,Hebei University of Engineering | Yang C.,Beijing Institute of Technology | Lao D.-Z.,Beijing Institute of Technology | Li Y.-Z.,Kangyue Technology Ltd Company
Tuijin Jishu/Journal of Propulsion Technology | Year: 2017

To investigate the non-axisymmetric flow in centrifugal compressor internal caused by the asymmetric structure of the volute, the combined experimental and numerical methods(Turbulence model choosing S-A model) are used. The results show that the perturbing pressure wave caused by the high static pressure zone of the volute propagates to the upstream in off-design conditions, which brings the non-axisymmetric flow in the compressor. The non-uniform degrees of the static pressure distribution of the volute in the large flow conditions(0.40kg/s) are more obvious than those of the small flow conditions(0.26kg/s). The strong disturbance pressure wave of the impeller outlet can be transmitted to the circumferential position of the impeller inlet about 180°. In the small flow conditions, the circumferential non-uniform degrees of the radial and tangential velocity of the gas flow through the diffuser are more significant. In the large flow conditions, the air flow fluctuations at volute inlet are more obvious. The blade loading distribution and its fluctuations are also affected by the the non-axisymmetric flow. The loading fluctuations of the main blades in the large flow conditions are mainly affected by the blade pass frequency, but in the small flow condition, they are mainly influenced by the two times of the blade pass frequency. © 2017, Editorial Department of Journal of Propulsion Technology. All right reserved.

Hou H.,Hebei University of Engineering | Wang L.,Hebei University of Engineering | Wang R.,Hebei University of Engineering | Yang Y.,Kangyue Technology Co.
Journal of Thermal Science | Year: 2017

A turbocharger compressor working in commercial vehicles, especially in some passenger cars, often works together with some pipes with complicated geometry as an air intake system, due to limit of available space in internal combustion engine compartments. These pipes may generate various distortions of physical parameters of the air at the inlet of the compressor and therefore the compressor aerodynamic performance deteriorates. Sometimes, the turbocharging engine fails to work at some operation points. This paper investigates the effects of various swirl distortions induced by different bending-torsional intake ducts on the aerodynamic performance of a turbocharger compressor by both 3D numerical simulations and experimental measurements. It was found that at the outlet of the pipes the different inlet ducts can generate different swirl distortions, twin vortices and bulk-like vortices with different rotating directions. Among them, the bulk-like vortices not only affect seriously the pressure distribution in the impeller domain, but also significantly deteriorate the compressor performance, especially at high flow rate region. And the rotating direction of the bulk-like vortices is also closely associated with the efficiency penalty. Besides the efficiency, the transient flow rate through a single impeller channel, or the asymmetric mass flow crossing the whole impeller, can be influenced by two disturbances. One is from the upstream bending-torsional ducts; other one is from the downstream volute. © 2017, Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag Berlin Heidelberg.

Fan H.,Tongji University | Ni J.,Tongji University | Wang H.,Kangyue Technology Co Ltd | Zhu Z.,Kangyue Technology Co Ltd | Liu Y.,Shandong University
SAE Technical Papers | Year: 2016

Turbocharging industry mainly employ steady method in the design and development process in present. However, the unsteady method is becoming more important for the exploration of the advanced turbocharging technique. This paper discusses the influences of A/R value on unsteady performances of a double-entry turbocharger turbine. In the study, numerical simulation has been done by ANSYS CFX software, The turbine have three kinds of A/R values that change in order, and the three schemes has the same unsteady flow boundary conditions. The simulation results show that the unsteady turbine performances have the characteristics loops representing filling and emptying effects. And the unsteady performances of the three schemes have some regular differences. The mean unsteady turbine efficiency decreases with increasing A/R value in the involved range, but the overall entropy of the turbine in a pulse period has no significant differences. In this paper, the flow loss of the turbine is analyzed to explore the mechanism of the influence of A/R value on unsteady turbine performances the from flow field aspect. The study may be helpful to have better understanding and comprehension of the actual working principle of turbocharger turbine and offer reference for future designs. Copyright © 2016 SAE International.

Li D.,Beijing Institute of Technology | Yang C.,Beijing Institute of Technology | Zhou M.,Bohai Shipbuilding Vocational College | Zhu Z.,Kangyue Technology Co. | Wang H.,Kangyue Technology Co.
Science China Technological Sciences | Year: 2012

Three different inlet configurations, including a original straight pipe and two bend pipes with different axial length, for a high speed low mass flow centrifugal compressor were modeled with whole blade passages and simulated unsteadily by 3D viscous Navier-Stokes equations. The performance disparities of compressor stage were tested and verified by experiments in which dynamic pressure data acquisition of internal flow field was performed. As the result shows, the choke point decreases to lower mass flow rate due to the distortion caused by bend-pipe inlet and is aggravated as the rotation speed increases. The distortion effect spreads circumferentially in impeller and makes the flow structure varied. The longer axial distance bent inlet leads to larger radial distortion and heavy blockage at mid-span under large mass flow mainly causes compressor choke margin narrowed. Bend pipe distortion brings an impact up to diffuser on unsteady pressure pulsation caused by blades sweep and the impact appears more powerful when it is closer to volute tongue. © 2011 Science China Press and Springer-Verlag Berlin Heidelberg.

Kangyue Technology Co. | Date: 2013-06-12

A pulse flow-channel-variable turbine device includes a turbine housing (1) in which a turbine impeller and an air outlet are arranged. An exhaust manifold (6) is connected to the inlet of the turbine housing (1). An internal flow channel is arranged inside the turbine housing (1), and a turbine housing outlet is arranged on the internal flow channel close to the turbine impeller. The internal flow channel is divided into a left-side flow channel and a right-side flow channel by a middle partition board disposed therein. The left-side flow channel and the right-side flow channel are respectively provided with a cambered partition board which is fixedly connected to the middle partition board at one end and is arranged close to the turbine housing outlet at another end. The device divides the interiors of the exhaust manifold and the turbine housing into four different flow areas, and realizes an effective utilization of the engine exhaust pulse energy both under a high and a low operating conditions consequently.

Kangyue Technology Co. | Date: 2013-01-24

A centrifugal compressor, including: a housing, the housing including: an inlet, a flow channel, an impeller outlet, and an air diffusing channel; a centrifugal impeller disposed inside the housing; a rotating wall, the rotating wall including a front cascade; and a rotating disc, the rotating disc including a rear cascade. The impeller outlet is disposed adjacent to a rear part of the centrifugal impeller and is connected to the flow channel via the air diffusing channel. The rotating wall is disposed between the centrifugal impeller and the housing. The front cascade is disposed inside the front part of the rotating wall and is connected to a dynamic driving device. The rotating disc is disposed inside the housing adjacent to the air diffusing channel and is in a rigid connection with the rotating wall.

Kangyue Technology Co. | Date: 2013-06-12

An electric composite multi-stage centrifugal compressor device includes a compressor housing (1), on which are provided an air-converging flow channel (14) and a compressor inlet (4). A compressor centrifugal impeller (2) is mounted inside the compressor housing (1). A compressor impeller outlet (11) is provided on the compressor housing (1) at a position adjacent to the end of the compressor centrifugal impeller (2). The compressor impeller outlet (11) is in communication with the air-converging flow channel (14) by an air-diffusing channel (9). A compressor rotation wall (28) is provided between the compressor centrifugal impeller (2) and the compressor housing (1). A front row blade cascade (21) provided on the front end of the compressor rotation wall (28) is transmissionally connected to a power-driving device. A rotation disk (24) is provided inside the compressor housing (1) at a position adjacent to the air-diffusing channel (9). A back row blade cascade (25) is provided on the rotation disk (24) fixedly connected to the compressor rotation wall (28). When the compressor runs at a high speed, the device realizes a three-stage working at a comparable size to that of and a same centrifugal impeller rotational speed as that of a conventional centrifugal compressor, so that the compression ratio of the compressor is efficiently improved.

Kangyue Technology Co. | Date: 2013-02-03

A turbine device, including: a turbine housing including an inlet, a flow channel, an outlet, a middle partition, an arced partition; a turbine impeller; a gas outlet; and an exhaust manifold. The turbine impeller and the gas outlet are arranged inside the turbine housing. The exhaust manifold is connected to the inlet. The flow channel is arranged inside the turbine housing. The outlet is arranged on the flow channel close to the turbine impeller. The middle partition is disposed inside the flow channel and divides the flow channel into a left flow channel and a right flow channel. The arced partition is arranged in both the left and right flow channels. One end of the arced partition is in a rigid connection with the middle partition, and the other end of the arced partition is close to the outlet of the turbine housing.

A variable geometry turbine (VGT) for turbochargers incorporates a turbine nozzle having a plurality of vanes, each vane having an airfoil with an inner disc and an outer disc. A first nozzle plate incorporates pockets to receive the inner discs with the inner discs substantially flush with a nozzle surface on the first nozzle plate. A second nozzle plate has pockets to receive the outer discs with outer discs substantially flush with a second nozzle surface. An integral actuation system rotates the plurality of vanes for variation of the nozzle geometry.

A variable geometry turbine for turbochargers in exhaust gas recirculation engines incorporates a turbine housing having an exhaust inlet with a first side receiving exhaust from cylinders having exhaust gas recirculation (EGR) and a second side receiving exhaust from non-EGR cylinders. The first side has a first EGR-driving passage and a second EGR-driving passage and the second side having a first non-EGR-driving passage and a second non-EGR-driving passage. A first control valve is associated with the second EGR-driving passage and a second control valve is associated with the second non-EGR-driving passage. A controller is adapted to control the first and second control valves.

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