| 摘要 |
<p>A nozzle cooling system (2) for selectively cooling longitudinally extending and circumferentially adjacent divergent exhaust flow confining elements (54 & 55) bounding a hot exhaust gas flowpath (4) in a divergent section (48) of an aircraft gas turbine engine exhaust nozzle (14) and providing pivoting capability for divergent flaps (54) and seals (55) in an axisymmetric vectoring nozzle (14). The apparatus includes axially adjacent foward and aft sections (49F & 49A) of at least one of the exhaust flow confining elements (typically referred to as flaps and seals), the adjacent forward and aft sections have forward and aft interior hot surfaces (47F & 47A) respectively, and mounting apparatus (56) for mounting the aft section to the forward section in one of at least two positions. A first one of these two positions spaces apart the sections to form a gap (106) between the sections which allows cooling air (102) to flow onto the aft interior hot surface and a second one of these two positions places the sections in close abutting relationship so as to essentially prevent cooling air from flowing onto the aft interior hot surface.</p> |
