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

Claim 2:
3. An exhaust system for an aircraft engine, comprising:
an exhaust duct;
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;
core gas flowing along the gas flow path boundary side producing a first pressure on the gas flow path boundary side of the exhaust liner;
an annulus between the exhaust duct and the exhaust liner;
cooling air flowing in the annulus producing a second pressure on the back side of the exhaust liner, the second pressure being opposed to the first pressure, producing a first net pressure; 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 to a low pressure region, the pressure in the low pressure region being less than the first pressure and the second pressure; and
a hollow passageway internal to the shank, providing fluid communication between the interface region of the post and the low pressure region;

wherein the low pressure region results in a second net 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 between the exhaust liner and the interface region; and
wherein the second net pressure is not equal to the first net pressure.