Abstract:
A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.
Abstract:
The tube (60) includes first and second portions (66, 58) that each have mating spherical sections (82, 84) at adjacent ends (72, 74) of each portion (66, 68). The second portion (68) includes a spring sleeve (92) configured to surround an outlet end (72) of the first portion (66). A spring (102) is captured inside the spring sleeve (92) and secured between a retaining clip (100) and a shoulder (88) protruding from the exterior surface of an outlet end (72) of the first portion (66) to maintain fluid seals between the spherical sections (82, 84). The spherical sections (82, 84) permit slidable motion relative to each other thereby facilitating rotational and angular motion between the tube portions (66, 68). One of the two portions (66, 68) may include a telescope mount (110) to permit limited axial motion of the tube (60).