Double paroi pour chambre de combustion de turbine à gaz d'aéronef et procédé de fabrication d'une telle double paroi

• Main Authors: SAVARY, Nicolas Roland Guy, AUTRET, Jean-Paul Didier, GRESY, Thomas Sebastien Alexandre
• Format: Patent
• Language: French
• Published: 26.01.2024
• Subjects: ADDITIVE MANUFACTURING TECHNOLOGY; ADDITIVE MANUFACTURING, i.e. MANUFACTURING OFTHREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVEAGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING,STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING; BLASTING; CASTING; COMBUSTION APPARATUS; COMBUSTION PROCESSES; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS; HEATING; LIGHTING; MAKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MECHANICAL ENGINEERING; PERFORMING OPERATIONS; POWDER METALLURGY; TRANSPORTING; WEAPONS; WORKING METALLIC POWDER

Une double paroi (2) pour chambre de combustion de turbine à gaz d'aéronef comportant une paroi interne (21) configurée pour être en contact avec la réaction de combustion et une paroi externe (22), écartée de la paroi interne (21), comportant une pluralité d'orifices (3) de manière à permettre la circulation de flux d'air de refroidissement (F), extérieurs à la paroi externe (22), qui viennent refroidir la paroi interne (21), la paroi interne (21) étant exempte de perforation de manière à interdire toute circulation d'un flux d'air de refroidissement (F) vers le centre de la chambre de combustion, la paroi interne (21) comportant une pluralité d'organes en saillie (4) vers la paroi externe (22), chaque organe en saillie (4) s'étendant dans un orifice (3) de manière à définir une section de passage calibrée entre l'organe en saillie (4) et l'orifice (3) pour le passage d'un flux d'air de refroidissement (F). Figure de l'abrégé : Figure 4 A double wall (2) for an aircraft gas turbine combustion chamber (1) comprising an internal wall (21) which is configured to be in contact with the combustion reaction, and an external wall (22) which is at a distance from the internal wall (21), comprising a plurality of openings (3) so as to allow the circulation of cooling air streams (F), outside the external wall (22), which cool the internal wall (21), the internal wall (21) being free of perforations so as to prevent any circulation of a cooling air stream (F) towards the centre of the combustion chamber (1). The double wall (2) is characterised in that the internal wall (21) comprises a plurality of members (4) projecting towards the external wall (22), each projecting member (4) comprising a foot portion (4a) and a cylindrical head portion (4b) with a circular cross-section, the head portion (4b) extending into an opening (3) with a circular cross-section so as to define a calibrated cross-sectional area between the projecting member (4) and the opening (3), through which area a cooling air stream (F) can flow.