Patent ID: 11905843
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 14:
15. An aircraft comprising:
an engine bay, the engine bay maintained substantially at atmospheric pressure; and
an aircraft engine housed within the engine bay, the aircraft engine including an exhaust system further comprising:
an exhaust duct mounted in the engine bay;
an exhaust liner spaced from the exhaust duct, the exhaust liner having a gas flow path boundary side and a back side opposite the gas flow path boundary side;
an annulus between the exhaust duct and the exhaust liner; and
a plurality of posts spacing the exhaust liner from the exhaust duct, wherein each post further comprises:
an interface region adjacent to the back side of the exhaust liner;
a periphery defining a perimeter of the interface region, the perimeter in contact with the back side of the exhaust liner and sealed to the back side of the exhaust liner;
a shank extending from the periphery and in fluid communication with a first pressure region; and
a hollow passageway internal to the shank, providing fluid communication between the interface region of the post and the first pressure region;

wherein the first pressure region results in a net positive outward pressure against the exhaust liner, urging the back side of the exhaust liner adjacent the interface region against the periphery while preventing fluid leakage across the perimeter.