Research on flow characteristics of aerostatic circular thrust bearing
In order to improve the pressure distribution, the aerostatic circular thrust bearing with single supply hole was studied. In the computational fluid dynamics (CFD) simulation, the laminar model, the turbulent model, the mixture model of laminar and turbulent were used simultaneously. The micro-char...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Wiley
2018-10-01
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| Series: | The Journal of Engineering |
| Subjects: | |
| Online Access: | https://digital-library.theiet.org/content/journals/10.1049/joe.2018.8975 |
| _version_ | 1818947883739643904 |
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| author | Hechun Yu Guangzhou Wang Wenqi Ma Guoqing Zhang Zexiang Zhao |
| author_facet | Hechun Yu Guangzhou Wang Wenqi Ma Guoqing Zhang Zexiang Zhao |
| author_sort | Hechun Yu |
| collection | DOAJ |
| description | In order to improve the pressure distribution, the aerostatic circular thrust bearing with single supply hole was studied. In the computational fluid dynamics (CFD) simulation, the laminar model, the turbulent model, the mixture model of laminar and turbulent were used simultaneously. The micro-characteristics of the gas flows were analysed based on the simulation results. One test rig was built for measuring the pressure distribution with the single test hole, and the calculated and experimental results were compared. The results showed that when the gas film clearance is small and the gas flow is subsonic completely, the whole gas flow is laminar flow, which should be calculated based on the laminar model and when the gas film thickness is large and there is supersonic flow in some region, which should be calculated according to the mixture model; at the same time, there is no surface of discontinuity for Mach number and pressure distribution, and no shock, and the pressure is recovered due to the boundary layer separation, the change of the flow state and the change of viscosity. The method for testing the pressure distributions with a single test hole is effective. |
| first_indexed | 2024-12-20T08:37:59Z |
| format | Article |
| id | doaj.art-67dd42692642420590aa974dc895597e |
| institution | Directory Open Access Journal |
| issn | 2051-3305 |
| language | English |
| last_indexed | 2024-12-20T08:37:59Z |
| publishDate | 2018-10-01 |
| publisher | Wiley |
| record_format | Article |
| series | The Journal of Engineering |
| spelling | doaj.art-67dd42692642420590aa974dc895597e2022-12-21T19:46:29ZengWileyThe Journal of Engineering2051-33052018-10-0110.1049/joe.2018.8975JOE.2018.8975Research on flow characteristics of aerostatic circular thrust bearingHechun Yu0Guangzhou Wang1Wenqi Ma2Guoqing Zhang3Zexiang Zhao4School of Mechanical & Electrical Engineering, Zhongyuan University of TechnologySchool of Mechanical & Electrical Engineering, Zhongyuan University of TechnologyTransportation Equipment and Marine Engineering College, Dalian Maritime UniversitySchool of Mechanical & Electrical Engineering, Zhongyuan University of TechnologySchool of Mechanical & Electrical Engineering, Zhongyuan University of TechnologyIn order to improve the pressure distribution, the aerostatic circular thrust bearing with single supply hole was studied. In the computational fluid dynamics (CFD) simulation, the laminar model, the turbulent model, the mixture model of laminar and turbulent were used simultaneously. The micro-characteristics of the gas flows were analysed based on the simulation results. One test rig was built for measuring the pressure distribution with the single test hole, and the calculated and experimental results were compared. The results showed that when the gas film clearance is small and the gas flow is subsonic completely, the whole gas flow is laminar flow, which should be calculated based on the laminar model and when the gas film thickness is large and there is supersonic flow in some region, which should be calculated according to the mixture model; at the same time, there is no surface of discontinuity for Mach number and pressure distribution, and no shock, and the pressure is recovered due to the boundary layer separation, the change of the flow state and the change of viscosity. The method for testing the pressure distributions with a single test hole is effective.https://digital-library.theiet.org/content/journals/10.1049/joe.2018.8975flow simulationcomputational fluid dynamicsviscositymachine bearingslaminar flowMach numbersupersonic flowboundary layer turbulencesubsonic flowflow separationpressure distributionaerostatic circular thrust bearingsingle supply holeCFD simulationlaminar modelturbulent modelmixture modelmicrocharacteristicssingle test holegas film clearancelaminar flowgas film thicknesssupersonic flowflow stateflow characteristicssubsonic gas flowMach numberboundary layer separationviscosity |
| spellingShingle | Hechun Yu Guangzhou Wang Wenqi Ma Guoqing Zhang Zexiang Zhao Research on flow characteristics of aerostatic circular thrust bearing The Journal of Engineering flow simulation computational fluid dynamics viscosity machine bearings laminar flow Mach number supersonic flow boundary layer turbulence subsonic flow flow separation pressure distribution aerostatic circular thrust bearing single supply hole CFD simulation laminar model turbulent model mixture model microcharacteristics single test hole gas film clearance laminar flow gas film thickness supersonic flow flow state flow characteristics subsonic gas flow Mach number boundary layer separation viscosity |
| title | Research on flow characteristics of aerostatic circular thrust bearing |
| title_full | Research on flow characteristics of aerostatic circular thrust bearing |
| title_fullStr | Research on flow characteristics of aerostatic circular thrust bearing |
| title_full_unstemmed | Research on flow characteristics of aerostatic circular thrust bearing |
| title_short | Research on flow characteristics of aerostatic circular thrust bearing |
| title_sort | research on flow characteristics of aerostatic circular thrust bearing |
| topic | flow simulation computational fluid dynamics viscosity machine bearings laminar flow Mach number supersonic flow boundary layer turbulence subsonic flow flow separation pressure distribution aerostatic circular thrust bearing single supply hole CFD simulation laminar model turbulent model mixture model microcharacteristics single test hole gas film clearance laminar flow gas film thickness supersonic flow flow state flow characteristics subsonic gas flow Mach number boundary layer separation viscosity |
| url | https://digital-library.theiet.org/content/journals/10.1049/joe.2018.8975 |
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