Thermo-pneumatic anti-icing systems include port and starboard anti-icing subsystems operatively interconnecting heated engine (1, 2) bleed air discharged from port side and starboard side turboprop engines with port and starboard airfoils, respectively, associated with an aircraft (10) to thereby provide in-flight anti-icing protection to the port and starboard airfoils, and an auxiliary power unit (APU) capable of discharging a supply of heated APU (40) bleed air to the port and starboard anti-icing subsystems during an abnormal single engine (1, 2) or a single pneumatic bleed air operational condition. A controller (25) may command respective port and starboard cross bleed valves to open and thereby allow the APU (40) bleed air to be supplied to the one port or starboard anti-icing subsystem that is incapable of delivering heated engine (1, 2) bleed air from the port side turboprop engine (1, 2) or the starboard side turboprop engine (1, 2), respectively. The port and starboard airfoils are thus each protected against inflight icing during the abnormal single engine (1, 2) or single pneumatic bleed air operational condition.
FAIL SAFE MULTI-ENGINE TURBOPROP AIRFRAME THERMOPNEUMATIC ANTI-ICING SYSTEMS
AUSFALLSICHERE THERMOPNEUMATISCHE ENTEISUNGSSYSTEME FÜR TURBOPROPFLUGTRIEBWERKE MIT MEHREREN MOTOREN
SYSTÈMES D'ANTIGIVRAGE THERMOPNEUMATIQUES DE CELLULE À TURBOPROPULSEUR À SÉCURITÉ INTÉGRÉE À MOTEURS MULTIPLES
2023-09-13
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
FAIL SAFE MULTI-ENGINE TURBOPROP AIRFRAME THERMO-PNEUMATIC ANTI-ICING SYSTEMS
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