Time-Inclined Method for High-Fidelity Rotor/Stator Simulations
The application of the time-inclined method in a fourth-order unstructured flux-reconstruction code for turbomachinery is demonstrated. Inviscid and viscous unsteady results due to the interaction of an incoming gust of total pressure with a linear cascade of flat plates and a linear cascade of T106...
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| Format: | Article |
| Language: | English |
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MDPI AG
2023-05-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/10/5/475 |
| _version_ | 1797601623842750464 |
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| author | Miguel Montiel Roque Corral |
| author_facet | Miguel Montiel Roque Corral |
| author_sort | Miguel Montiel |
| collection | DOAJ |
| description | The application of the time-inclined method in a fourth-order unstructured flux-reconstruction code for turbomachinery is demonstrated. Inviscid and viscous unsteady results due to the interaction of an incoming gust of total pressure with a linear cascade of flat plates and a linear cascade of T106A low-pressure turbine airfoils are reported. The agreement between the time-inclined method and the equivalent full-annulus multipassage solution is very high for both cases. Viscous solutions at Reynolds numbers of <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><msup><mn>10</mn><mn>4</mn></msup></semantics></math></inline-formula> and <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><msup><mn>10</mn><mn>5</mn></msup></semantics></math></inline-formula> were conducted. A high degree of matching was obtained between the time-inclined and the whole annulus approaches. The limitations of the method are explored and discussed. While the evolution of the unsteady boundary layers created by the interaction with the incoming wakes was very well captured, the mixing associated with the trailing edge vortex shedding was less accurate. The critical parameter controlling the method’s accuracy is the local Strouhal number. It was demonstrated that the benefit of retaining the exact blade count in the simulations overcomes the slight differences in the mixing due to the limitation of the time-inclined method to model viscous effects accurately in all situations. |
| first_indexed | 2024-03-11T04:02:58Z |
| format | Article |
| id | doaj.art-b69f0f1a06f2420dab02436ee33beb68 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-11T04:02:58Z |
| publishDate | 2023-05-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-b69f0f1a06f2420dab02436ee33beb682023-11-18T00:00:51ZengMDPI AGAerospace2226-43102023-05-0110547510.3390/aerospace10050475Time-Inclined Method for High-Fidelity Rotor/Stator SimulationsMiguel Montiel0Roque Corral1Department of Fluid Mechanics and Aerospace Propulsion, School of Aeronautical and Space Engineering, Universidad Politécnica de Madrid, 28040 Madrid, SpainDepartment of Fluid Mechanics and Aerospace Propulsion, School of Aeronautical and Space Engineering, Universidad Politécnica de Madrid, 28040 Madrid, SpainThe application of the time-inclined method in a fourth-order unstructured flux-reconstruction code for turbomachinery is demonstrated. Inviscid and viscous unsteady results due to the interaction of an incoming gust of total pressure with a linear cascade of flat plates and a linear cascade of T106A low-pressure turbine airfoils are reported. The agreement between the time-inclined method and the equivalent full-annulus multipassage solution is very high for both cases. Viscous solutions at Reynolds numbers of <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><msup><mn>10</mn><mn>4</mn></msup></semantics></math></inline-formula> and <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><msup><mn>10</mn><mn>5</mn></msup></semantics></math></inline-formula> were conducted. A high degree of matching was obtained between the time-inclined and the whole annulus approaches. The limitations of the method are explored and discussed. While the evolution of the unsteady boundary layers created by the interaction with the incoming wakes was very well captured, the mixing associated with the trailing edge vortex shedding was less accurate. The critical parameter controlling the method’s accuracy is the local Strouhal number. It was demonstrated that the benefit of retaining the exact blade count in the simulations overcomes the slight differences in the mixing due to the limitation of the time-inclined method to model viscous effects accurately in all situations.https://www.mdpi.com/2226-4310/10/5/475high-fidelityscale-resolving simulationsturbomachineryrotor/statortime-inclinedflux reconstruction |
| spellingShingle | Miguel Montiel Roque Corral Time-Inclined Method for High-Fidelity Rotor/Stator Simulations Aerospace high-fidelity scale-resolving simulations turbomachinery rotor/stator time-inclined flux reconstruction |
| title | Time-Inclined Method for High-Fidelity Rotor/Stator Simulations |
| title_full | Time-Inclined Method for High-Fidelity Rotor/Stator Simulations |
| title_fullStr | Time-Inclined Method for High-Fidelity Rotor/Stator Simulations |
| title_full_unstemmed | Time-Inclined Method for High-Fidelity Rotor/Stator Simulations |
| title_short | Time-Inclined Method for High-Fidelity Rotor/Stator Simulations |
| title_sort | time inclined method for high fidelity rotor stator simulations |
| topic | high-fidelity scale-resolving simulations turbomachinery rotor/stator time-inclined flux reconstruction |
| url | https://www.mdpi.com/2226-4310/10/5/475 |
| work_keys_str_mv | AT miguelmontiel timeinclinedmethodforhighfidelityrotorstatorsimulations AT roquecorral timeinclinedmethodforhighfidelityrotorstatorsimulations |