An air duct interface for an aircraft engine is disclosed herein. The air duct interface includes a first air duct, a first outer wall, a mating interface disposed circumferentially around the first outer wall, a second air duct, a second outer wall, and a gasket interface disposed circumferentially around the second outer wall. The mating interface includes a first angled portion extending away from the first outer wall in a first direction and a second angled portion extending away from the first outer wall in a second direction opposite the first direction. The gasket interface includes a first portion extending away from the second outer wall in the first direction, wherein the first portion is configured to engage the first angled portion and a second portion extending away from the second outer wall in the second direction, wherein the second portion is configured to engage the second angled portion.
MECHANISM FOR CONNECTING HIGH TEMPERATURE AIR DUCTING FOR AIRCRAFT ENGINE
2025-04-17
Patent
Electronic Resource
English
NTRS | 1996
NTIS | 1996
Liquid Tight Insulation for High Temperature Aircraft Ducting
SAE Technical Papers | 1992
|Liquid tight insulation for high temperature aircraft ducting
Tema Archive | 1992
|