A component (30) of an aircraft engine (10) includes an annular flange (32) disposed about a radially outer surface (31b) of the component (30). The annular flange (32) includes an annular wall extending radially outwardly from the radially outer surface (31b) of the component (30). The annular wall includes radially-extending supports (38) circumferentially spaced apart and extending radially between the radially outer surface (31b) of the component (30) and a circumferentially uninterrupted radially outer rim (32a) of the annular wall. The annular wall includes one or more arcuate cutouts (37) defined circumferentially between adjacent radially-extending supports (38) and radially inwards of the radially outer rim (32a) of the annular wall. The radially-extending supports (38) include fastener openings (36) defined axially therethrough. A spigot (35) extends axially from the radially outer rim (32a) of the annular wall and circumferentially about an entire circumference of the radially outer rim (32a) of the annular wall.
OUTSIDE FIT FLANGE FOR AIRCRAFT ENGINE
AUSSENDECKFLANSCH FÜR FLUGZEUGTRIEBWERK
BRIDE EXTÉRIEUR POUR MOTEUR D'AÉRONEF
2023-01-04
Patent
Electronic Resource
English
AIRCRAFT ENGINE AND ACCESSORY DRIVES AND FLANGE STANDARDS
SAE Technical Papers | 1973
Aircraft Engine and Accessory Drives and Flange Standards
SAE Technical Papers | 2004