Patent ID: 11878807
Assignee: RAYTHEON COMPANY
Field: Mechanical elements (Mechanical engineering)
Classification: CPC B  F | IPC B  F

Claim 5:
6. A sealed system comprising:
an annular seal comprising a flat annular portion extending circumferentially around a longitudinal axis of the flat annular portion and a plurality of independently flexible segments arranged circumferentially around the longitudinal axis and extending obliquely from the flat annular portion toward the longitudinal axis;
an engine nozzle having an outer circumferential surface;
an airframe having an inner circumferential surface that is arranged circumferentially around the outer circumferential surface of the engine nozzle with a space therebetween; and
an L-shape or J-shape insulating member arranged axially adjacent to and distinct from the annular seal in the space between the outer circumferential surface of the engine nozzle and the inner circumferential surface of the airframe and extending circumferentially around the longitudinal axis, the insulating member having an axially extending first leg mounted to the inner circumferential surface of the airframe and a radially extending second leg contacting the outer circumferential surface of the engine nozzle, the axially extending first leg and the radially extending second leg being configured to accommodate at least a part of the annular seal in a space between the axially extending first leg and the radially extending second leg, the insulating member being configured to cool airflow passing therethrough;
wherein the axially extending first leg is adjacent and contacting the flat annular portion of the annular seal, and the radially extending second leg is adjacent to the plurality of independently flexible segments of the annular seal;
wherein the annular seal is disposed in the space between the outer circumferential surface of the engine nozzle and the inner circumferential surface of the airframe and wherein the flat annular portion of the annular seal is mounted to the inner circumferential surface of the airframe;
wherein a distal end of each of the plurality of independently flexible segments from the flat annular portion contacts the outer circumferential surface of the engine nozzle; and
wherein the plurality of independently flexible segments exert a biased force on the outer circumferential surface of the engine nozzle such that contact of the distal end of each of the plurality of independently flexible segments with the outer circumferential surface of the engine nozzle is maintained upon radial and axial displacement of the outer circumferential surface of the engine nozzle.