Abstract:
A combustor liner assembly of a gas turbine engine comprises a dome having a central axis aligned with an engine axis, the dome arranged at an inlet end of a combustor, a first spring disposed at a radially outward position of the dome, an outer liner retainer engaging a radially outer cowl 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 having an outer liner sealing surface 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 having an inner liner sealing surface and engaging a radially inward surface of the dome, a second spring engaging the radially extending surface of the inner combustor liner, acting in an axial direction.
Abstract:
A system of integrating baffles for enhanced cooling of CMC liners is comprised of a combustor assembly having a dome mount assembly, outer liner and inner liner. Liners include those manufactured from and in a process for CMC (Ceramic Matrix Composite). One or more liner baffles such as outer baffle and inner baffle, are provided to reduce the pressure drop across the liner, allowing the addition of more cooling holes and thereby reducing the cooling hole spacing while not increasing the required amount of cooling air. CMC liners are incorporated, as desired, to take advantage of shapes and hole dispositions made possible by use of CMC over past designs.