| DOI | Trouver le DOI : https://doi.org/10.2514/6.2021-0512 |
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| Auteur | Rechercher : Paitich, Leo C.; Rechercher : Richer, Patrick; Rechercher : Jodoin, Bertrand; Rechercher : Yun, Sean1; Rechercher : Hong, Zekai1 |
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| Affiliation | - Conseil national de recherches du Canada. Aérospatiale
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| Format | Texte, Article |
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| Conférence | AIAA Scitech 2021 Forum, January 11-15, 2021, Virtual Event |
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| Sujet | combustors; coolants; mass transfer; paint; supersonic aerodynamics; swirling flow; wind tunnels |
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| Résumé | Effusion cooling is a method found in modern aeroengine combustors which produces a protective cooling film over the inner surface of combustor liners combined with heat removal from the metal liner as cooling air passes effusion holes. A complication to effusion cooling in gas turbine combustors is that swirling flows are usually utilized for anchoring flame whereas miniature effusion cooling jets emanating from effusion cooling holes are highly directional. A direct consequence of swirling flow pattern is varying angles between the main flow and cooling jets. This work aims at understanding the directional effects of effusion cooling by studying the effectiveness of cooling film as a function of the offset flow angle (β) between the main flow and effusion cooling jets. The cooling film effectiveness is investigated with the effusion cooling miniature jets at a range of angles between parallel and perpendicular to the main flow at 30° intervals, namely at offset angles of 0°, 30°, 60° and 90°. The cooling film effectiveness is determined by invoking the heat/mass transfer analogy using Pressure Sensitive Paint (PSP) that is sensitive to the oxygen partial pressure at the paint surface. An experimental setup is designed and fabricated based on a low-speed wind tunnel at the National Research Council Canada’s Aerospace Research Center. Experimental results indicate that offset angles (β) have a strong effect on the cooling film effectiveness. At lower coolant mass flow rates an offset angle increases the uniformness of the cooling film, as the flow from each individual hole coalesces together to form the protective film. At higher coolant mass flow rates the cooling film effectiveness is less sensitive to the offset angles (β). This is believed to be caused by the coolant flow lifting off the surface and dissipating more easily in the mainstream flow. |
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| Date de publication | 2021-01-11 |
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| Maison d’édition | American Institute of Aeronautics and Astronautics |
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| Dans | |
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| Langue | anglais |
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| Publications évaluées par des pairs | Oui |
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| Exporter la notice | Exporter en format RIS |
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| Signaler une correction | Signaler une correction (s'ouvre dans un nouvel onglet) |
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| Identificateur de l’enregistrement | 6a4e8b5c-17cf-45ac-ad16-7d23e86e5215 |
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| Enregistrement créé | 2023-06-16 |
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| Enregistrement modifié | 2023-06-16 |
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