A combustor assembly for a gas turbine engine defining an axial direction, the combustor assembly comprising: a liner (102, 108) at least partially defining a combustion chamber extending between an aft end and a forward end generally along the axial direction, the liner (102, 108) including an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber, and the liner (102, 108) comprising an inner liner and an outer liner; an inner annular dome attached to the forward end of the inner liner and an outer annular dome attached to the forward end of the outer liner, wherein the inner and outer annular domes (116, 118) each includes an attachment extension (134, 138) configured to assist in mounting the combustor assembly within the gas turbine engine; a first damper assembly extending from the outer surface of the outer liner, the first damper assembly including a first selectively separable support and a first damper spring, the first damper spring (145,) being disposed between the first support and the outer liner, wherein the first support includes the attachment extension of the outer liner; and a second damper assembly extending from an outer surface of the inner liner, the second damper assembly including a second selectively separable support and a second damper spring, the second damper spring being disposed between the inner annular dome and the inner liner, wherein the second support includes the attachment extension of the inner annular dome; wherein the first damper spring is a first front damper spring attached to the outer annular dome and is in operable connection with the attachment extension of the outer annular dome to damp radial oscillation of the outer liner and that attachment extension; and wherein the second damper spring is a second front damper spring attached to the inner annular dome and is in operable connection with the attachment extension of the inner annular dome to damp radial oscillation of the inner liner and the attachment extension. a liner (102, 108) at least partially defining a combustion chamber extending between an aft end and a forward end generally along the axial direction, the liner (102, 108) including an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber, and the liner (102, 108) comprising an inner liner and an outer liner; an inner annular dome attached to the forward end of the inner liner and an outer annular dome attached to the forward end of the outer liner, wherein the inner and outer annular domes (116, 118) each includes an attachment extension (134, 138) configured to assist in mounting the combustor assembly within the gas turbine engine; a first damper assembly extending from the outer surface of the outer liner, the first damper assembly including a first selectively separable support and a first damper spring, the first damper spring (145,) being disposed between the first support and the outer liner, wherein the first support includes the attachment extension of the outer liner; and a second damper assembly extending from an outer surface of the inner liner, the second damper assembly including a second selectively separable support and a second damper spring, the second damper spring being disposed between the inner annular dome and the inner liner, wherein the second support includes the attachment extension of the inner annular dome; wherein the first damper spring is a first front damper spring attached to the outer annular dome and is in operable connection with the attachment extension of the outer annular dome to damp radial oscillation of the outer liner and that attachment extension; and wherein the second damper spring is a second front damper spring attached to the inner annular dome and is in operable connection with the attachment extension of the inner annular dome to damp radial oscillation of the inner liner and the attachment extension.