A pressure relief assembly (24) includes an aircraft engine cowl (26) having radially outer and inner skins (28,30) having an opening. A door frame (32) is joined around the perimeter of the opening and defines a door seat (34) surrounding a central portal (36). A pressure relief door (38) is joined to the cowl (26) to cover the portal (36). The door (38) has inner and outer surfaces (40,42) terminating in a perimeter rim (44), with the inner surface (40) of the rim (44) overlapping the door seat (34) to define a primary seal (46) with the door stowed closed. A fireproof secondary seal (48) bridges the door inner surface (40) and frame (32) around the inner perimeter of the primary seal (46) to pre-seal flow to the primary seal (46).
FIREPROOF PRESSURE RELIEF ASSEMBLY
FEUERFESTE DRUCKENTLASTUNGSANORDNUNG
ENSEMBLE DE DÉCHARGE DE PRESSION IGNIFUGE
2021-06-16
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / E05B LOCKS , Schlösser / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS |