THERMAL ANTI-ICING SYSTEM
THERMAL ANTI-ICING SYSTEM
- New search for: GREGORY KARL
- New search for: SHEPPARD MICHAEL JAMES
- New search for: ATTRILL SCOTT
- New search for: GREGORY KARL
- New search for: SHEPPARD MICHAEL JAMES
- New search for: ATTRILL SCOTT
An air intake duct of an aircraft engine or other component is provided with a thermal anti-icing system. The front of the air intake duct comprises a toroidal outer skin (16) which forms, with a toroidal, internal bulkhead (18), a toroidal plenum (8) about the centre line (26). The bulkhead has an inner edge nearest the centre line. Within the plenum there is a toroidal inner skin (9) defining with the outer skin a substantially continuous toroidal channel (19). Hot air is supplied via an inlet (7) to the plenum (8). The air flows into an inlet (14) at an end of channel (19) and out of an outlet (11) through the bulkhead (18). This provide more heat to the leading edge of the duct, and to the surface of the duct facing the centre line, than to other parts of the duct to prevent build up of ice which may enter, and damage, the engine. This reduces the mass flow of hot air needed for de-icing.
Document information
THERMAL ANTI-ICING SYSTEM
SYSTEME THERMIQUE DE PREVENTION DU GIVRAGE D'UN AVION
2015-10-27
Patent
Electronic Resource
English
| IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |