A seal assembly for a gas turbine engine (10) having a rotor (23) arranged to rotate about an axis (9) in use. The seal assembly has a static support structure (50, 51) for the gas turbine engine (10) and a casing structure (21, 56) of the engine (10). Rotation of the engine rotor (23) causes a deflection of the casing (21, 56) relative to the static support structure (50) in a first direction (70). A seal (54) is provided at an interface (47, 52, 53) between the static support structure (50, 51) and the casing structure (21, 56), and comprising a first seal portion (62) and a second seal portion (64) spaced from one another in the first direction (70). The first seal portion (62) is provided against a first surface (58) of the casing and the second seal portion (64) is provided against a second surface (60) of the casing opposing the first surface (58). In an at-rest state in which the engine (10) is not operational, the first (58) and second (60) surfaces are offset from an equilibrium position with respect to the static support structure (50, 51) such that there is a difference in compression of the first seal portion (62) and the second seal portion (64) between the static support structure (50, 51) and the casing (21, 56). The offset is in a direction opposite to the first direction (70).
Seal assembly
2019-05-22
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |