Patent ID: 8875518

Claim:
A nacelle for a turbojet comprising: an inner fixed structure; a combustion chamber that generates a primary flow; an exhaust nozzle that exhausts the primary flow; an aft end of the inner fixed structure partially overlaps a forward end of the exhaust nozzle, the inner fixed structure having a larger diameter than the exhaust nozzle; wherein an outer surface of the exhaust nozzle and an inner surface of the inner fixed structure define an outlet section of an engine compartment therebetween; and wherein the outlet section ventilates an engine compartment airflow; the outlet section of the engine compartment comprising: a plurality of rigid spacers fixed to a periphery of a first surface of the outlet section, and wherein the plurality of rigid spacers define first and second sets of passages that each ventilate the engine compartment airflow at the outlet section; wherein the first set of passages are formed between adjacent rigid spacers; and wherein the second set of passages are formed in spaces within the plurality of rigid spacers; a plurality of longitudinal fingers, wherein each of the plurality of longitudinal fingers is attached to the plurality of rigid spacers at a first end and pressed against a second surface of the outlet section at a second end; a plurality of longitudinal slots formed between adjacent longitudinal fingers; and wherein each of the plurality of longitudinal fingers flex in response to relative movements of the turbojet with respect to the nacelle.