| 摘要 |
A combustor liner assembly of a gas turbine engine comprises a dome (42) having a central axis aligned with an engine axis, the dome arranged at an inlet end (32) of a combustor (16), a first spring (70) disposed at a radially outward position of the dome, an outer liner retainer engaging a radially outer cowl (40) and, the outer liner retainer having a sealing surface disposed in a radial plane for receiving an axial force, a ceramic matrix composite outer combustor liner (60) having an outer liner sealing surface (62) which is seated against the outer liner retainer, the first spring forcing the outer liner in an axial direction against the liner outer liner retainer, a ceramic matrix composite inner combustor liner (64) having an inner liner sealing surface and engaging a radially inward surface (56) of the dome, a second spring (76) engaging the radially extending surface of the inner combustor liner, the second spring acting in an axial direction to capture the inner combustor liner against the dome. |
