Liquid-Cooling System of an Aircraft Compression Ignition Engine: A CFD Analysis
The present work deals with an analysis of the cooling system for a two-stroke aircraft engine with compression ignition. This analysis is carried out by means of a 3D finite-volume RANS equations solver with <i>k</i>-<inline-formula> <math display="inline"> <sem...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
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MDPI AG
2020-05-01
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| Series: | Fluids |
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| Online Access: | https://www.mdpi.com/2311-5521/5/2/71 |
| _version_ | 1797568112614178816 |
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| author | Alessandro Coclite Maria Faruoli Annarita Viggiano Paolo Caso Vinicio Magi |
| author_facet | Alessandro Coclite Maria Faruoli Annarita Viggiano Paolo Caso Vinicio Magi |
| author_sort | Alessandro Coclite |
| collection | DOAJ |
| description | The present work deals with an analysis of the cooling system for a two-stroke aircraft engine with compression ignition. This analysis is carried out by means of a 3D finite-volume RANS equations solver with <i>k</i>-<inline-formula> <math display="inline"> <semantics> <mi>ϵ</mi> </semantics> </math> </inline-formula> closure. Three different cooling system geometries are critically compared with a discussion on the capabilities and limitations of each technical solution. A first configuration of such a system is considered and analyzed by evaluating the pressure loss across the system as a function of the inlet mass-flow rate. Moreover, the velocity and vorticity patterns are analyzed to highlight the features of the flow structure. Thermal effects on the engine structure are also taken into account and the cooling system performance is assessed as a function of both the inlet mass-flow rate and the cylinder jackets temperatures. Then, by considering the main thermo-fluid dynamics features obtained in the case of the first configuration, two geometrical modifications are proposed to improve the efficiency of the system. As regards the first modification, the fluid intake is split in two manifolds by keeping the same total mass-flow rate. As regards the second configuration, a new single-inlet geometry is designed by inserting restrictions and enlargements within the cooling system to constrain the coolant flow through the cylinder jackets and by moving downstream the outflow section. It is shown that the second geometry modification achieves the best performances by improving the overall transferred heat of about 20% with respect to the first one, while keeping the three cylinders only slightly unevenly cooled. However, an increase of the flow characteristic loads occurs due to the geometrical restrictions and enlargements of the cooling system. |
| first_indexed | 2024-03-10T19:51:43Z |
| format | Article |
| id | doaj.art-9818968106174cfab7ca7a6b725aeba2 |
| institution | Directory Open Access Journal |
| issn | 2311-5521 |
| language | English |
| last_indexed | 2024-03-10T19:51:43Z |
| publishDate | 2020-05-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Fluids |
| spelling | doaj.art-9818968106174cfab7ca7a6b725aeba22023-11-20T00:19:45ZengMDPI AGFluids2311-55212020-05-01527110.3390/fluids5020071Liquid-Cooling System of an Aircraft Compression Ignition Engine: A CFD AnalysisAlessandro Coclite0Maria Faruoli1Annarita Viggiano2Paolo Caso3Vinicio Magi4School of Engineering, University of Basilicata, 85100 Potenza, ItalySchool of Engineering, University of Basilicata, 85100 Potenza, ItalySchool of Engineering, University of Basilicata, 85100 Potenza, ItalyCostruzioni Motori Diesel CMD S.p.A., 81020 San Nicola La Strada (CE), ItalySchool of Engineering, University of Basilicata, 85100 Potenza, ItalyThe present work deals with an analysis of the cooling system for a two-stroke aircraft engine with compression ignition. This analysis is carried out by means of a 3D finite-volume RANS equations solver with <i>k</i>-<inline-formula> <math display="inline"> <semantics> <mi>ϵ</mi> </semantics> </math> </inline-formula> closure. Three different cooling system geometries are critically compared with a discussion on the capabilities and limitations of each technical solution. A first configuration of such a system is considered and analyzed by evaluating the pressure loss across the system as a function of the inlet mass-flow rate. Moreover, the velocity and vorticity patterns are analyzed to highlight the features of the flow structure. Thermal effects on the engine structure are also taken into account and the cooling system performance is assessed as a function of both the inlet mass-flow rate and the cylinder jackets temperatures. Then, by considering the main thermo-fluid dynamics features obtained in the case of the first configuration, two geometrical modifications are proposed to improve the efficiency of the system. As regards the first modification, the fluid intake is split in two manifolds by keeping the same total mass-flow rate. As regards the second configuration, a new single-inlet geometry is designed by inserting restrictions and enlargements within the cooling system to constrain the coolant flow through the cylinder jackets and by moving downstream the outflow section. It is shown that the second geometry modification achieves the best performances by improving the overall transferred heat of about 20% with respect to the first one, while keeping the three cylinders only slightly unevenly cooled. However, an increase of the flow characteristic loads occurs due to the geometrical restrictions and enlargements of the cooling system.https://www.mdpi.com/2311-5521/5/2/71internal combustion enginesliquid-cooling systemheat transfercomputational fluid dynamics |
| spellingShingle | Alessandro Coclite Maria Faruoli Annarita Viggiano Paolo Caso Vinicio Magi Liquid-Cooling System of an Aircraft Compression Ignition Engine: A CFD Analysis Fluids internal combustion engines liquid-cooling system heat transfer computational fluid dynamics |
| title | Liquid-Cooling System of an Aircraft Compression Ignition Engine: A CFD Analysis |
| title_full | Liquid-Cooling System of an Aircraft Compression Ignition Engine: A CFD Analysis |
| title_fullStr | Liquid-Cooling System of an Aircraft Compression Ignition Engine: A CFD Analysis |
| title_full_unstemmed | Liquid-Cooling System of an Aircraft Compression Ignition Engine: A CFD Analysis |
| title_short | Liquid-Cooling System of an Aircraft Compression Ignition Engine: A CFD Analysis |
| title_sort | liquid cooling system of an aircraft compression ignition engine a cfd analysis |
| topic | internal combustion engines liquid-cooling system heat transfer computational fluid dynamics |
| url | https://www.mdpi.com/2311-5521/5/2/71 |
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