A locking tab washer (70) for rotatably locking a bolt (40) fastened to a component (50, 60) in an aircraft engine has a body with an opening (73) and at least four locking tabs (74) positioned about the opening (73) and circumferentially spaced apart from...

Provided is a gas turbine combustor having improved maintainability obtained by facilitating the mounting and removal of a base plate for supporting main burners and a pilot burner. A gas turbine combustor is provided with: a pilot burner (13) disposed at ...

A panel (208) for a nacelle structure that surrounds a jet engine core includes a longitudinally extending semicircular center region (302), an upper bifurcation region (304), a lower bifurcation region (312), a hinge beam region (306) extending from the u...

The enclosure (3) has a metal structure comprising lateral faces adapted to partially surround a thermal equipment. A circular chamber (5) comprises an inner face. The metal structure is mounted on a base of the thermal equipment. The chamber is mounted on...

To improve structural integrity of the exo-skeleton tile structure, each tile (18) is formed with at least one rib (40) extending circumferentially across the outer surface of the tile. An end (41) of each rib projects beyond one edge of the tile, like til...

An outer crossfire tube (10) for attachment between adjacent combustors (12, 14) in a land-based gas turbine includes a substantially cylindrical bellows portion (16) and a pair of uniform diameter free ends (20, 22) on opposite sides of the bellows portio...

A method enables a link connector (12) to be coupled to a clevis (14). The clevis includes a pair of arms (20, 22) and an opening (28, 30) that extends therethrough. The link connector includes a first end (40) that includes an elastomeric portion (44) tha...