A system is provided for an aircraft propulsion system. This system includes an inlet lip, a bulkhead and a piccolo tube for a thermal anti-icing system. The inlet lip extends circumferentially about an axial centerline. The bulkhead extends circumferentially about the axial centerline. The bulkhead is configured with the inlet lip to form a cavity axially between the inlet lip and the bulkhead. The piccolo tube extends circumferentially about the axial centerline within the cavity. The piccolo tube is configured with an elliptical cross-sectional geometry.
Thermal anti-icing system with non-circular piccolo tube
14.02.2023
Patent
Elektronische Ressource
Englisch
THERMAL ANTI-ICING SYSTEM WITH NON-CIRCULAR PICCOLO TUBE
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