Nozzle geometry variations on the discharge coefficient
Numerical works have been conducted to investigate the effect of nozzle geometries on the discharge coefficient. Several contoured converging nozzles with finite radius of curvatures, conically converging nozzles and conical divergent orifices have been employed in this investigation. Each nozzle an...
| Main Authors: | , , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
KeAi Communications Co., Ltd.
2016-03-01
|
| Series: | Propulsion and Power Research |
| Subjects: | |
| Online Access: | http://www.sciencedirect.com/science/article/pii/S2212540X16000031 |
| _version_ | 1797713126217482240 |
|---|---|
| author | M.M.A. Alam T. Setoguchi S. Matsuo H.D. Kim |
| author_facet | M.M.A. Alam T. Setoguchi S. Matsuo H.D. Kim |
| author_sort | M.M.A. Alam |
| collection | DOAJ |
| description | Numerical works have been conducted to investigate the effect of nozzle geometries on the discharge coefficient. Several contoured converging nozzles with finite radius of curvatures, conically converging nozzles and conical divergent orifices have been employed in this investigation. Each nozzle and orifice has a nominal exit diameter of 12.7×10−3 m. A 3rd order MUSCL finite volume method of ANSYS Fluent 13.0 was used to solve the Reynolds-averaged Navier–Stokes equations in simulating turbulent flows through various nozzle inlet geometries. The numerical model was validated through comparison between the numerical results and experimental data. The results obtained show that the nozzle geometry has pronounced effect on the sonic lines and discharge coefficients. The coefficient of discharge was found differ from unity due to the non-uniformity of flow parameters at the nozzle exit and the presence of boundary layer as well. |
| first_indexed | 2024-03-12T07:31:50Z |
| format | Article |
| id | doaj.art-149b98dc632b489d8eaa938eea19537b |
| institution | Directory Open Access Journal |
| issn | 2212-540X |
| language | English |
| last_indexed | 2024-03-12T07:31:50Z |
| publishDate | 2016-03-01 |
| publisher | KeAi Communications Co., Ltd. |
| record_format | Article |
| series | Propulsion and Power Research |
| spelling | doaj.art-149b98dc632b489d8eaa938eea19537b2023-09-02T21:44:04ZengKeAi Communications Co., Ltd.Propulsion and Power Research2212-540X2016-03-0151223310.1016/j.jppr.2016.01.002Nozzle geometry variations on the discharge coefficientM.M.A. Alam0T. Setoguchi1S. Matsuo2H.D. Kim3Institute of Ocean Energy, Saga University (IOES), 1, Honjo, Saga-shi, Saga 840-8502, JapanInstitute of Ocean Energy, Saga University (IOES), 1, Honjo, Saga-shi, Saga 840-8502, JapanDepartment of Advanced Technology Fusion, Saga University, JapanDepartment of Mechanical Engineering, Andong National University, KoreaNumerical works have been conducted to investigate the effect of nozzle geometries on the discharge coefficient. Several contoured converging nozzles with finite radius of curvatures, conically converging nozzles and conical divergent orifices have been employed in this investigation. Each nozzle and orifice has a nominal exit diameter of 12.7×10−3 m. A 3rd order MUSCL finite volume method of ANSYS Fluent 13.0 was used to solve the Reynolds-averaged Navier–Stokes equations in simulating turbulent flows through various nozzle inlet geometries. The numerical model was validated through comparison between the numerical results and experimental data. The results obtained show that the nozzle geometry has pronounced effect on the sonic lines and discharge coefficients. The coefficient of discharge was found differ from unity due to the non-uniformity of flow parameters at the nozzle exit and the presence of boundary layer as well.http://www.sciencedirect.com/science/article/pii/S2212540X16000031Boundary layerCompressible flowReynolds-averaged Navier–Stokes (RANS)Shear layerSonic linesSupersonic core |
| spellingShingle | M.M.A. Alam T. Setoguchi S. Matsuo H.D. Kim Nozzle geometry variations on the discharge coefficient Propulsion and Power Research Boundary layer Compressible flow Reynolds-averaged Navier–Stokes (RANS) Shear layer Sonic lines Supersonic core |
| title | Nozzle geometry variations on the discharge coefficient |
| title_full | Nozzle geometry variations on the discharge coefficient |
| title_fullStr | Nozzle geometry variations on the discharge coefficient |
| title_full_unstemmed | Nozzle geometry variations on the discharge coefficient |
| title_short | Nozzle geometry variations on the discharge coefficient |
| title_sort | nozzle geometry variations on the discharge coefficient |
| topic | Boundary layer Compressible flow Reynolds-averaged Navier–Stokes (RANS) Shear layer Sonic lines Supersonic core |
| url | http://www.sciencedirect.com/science/article/pii/S2212540X16000031 |
| work_keys_str_mv | AT mmaalam nozzlegeometryvariationsonthedischargecoefficient AT tsetoguchi nozzlegeometryvariationsonthedischargecoefficient AT smatsuo nozzlegeometryvariationsonthedischargecoefficient AT hdkim nozzlegeometryvariationsonthedischargecoefficient |