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.