Abstract: Methods and apparatus for a mounting assembly for a liner of a gas turbine engine combustor are provided. The combustor includes a combustor liner and a radially outer annular flow sleeve. The mounting assembly includes an inner ring surrounding a radially outer surface of the liner and including a plurality of axially extending fingers. The mounting assembly also includes a radially outer ring coupled to the inner ring through a plurality of spacers that extend radially from a radially outer surface of the inner ring to the outer ring.

Abstract: Methods and apparatus for a mounting assembly for a liner of a gas turbine engine combustor are provided. The combustor includes a combustor liner and a radially outer annular flow sleeve. The mounting assembly includes an inner ring surrounding a radially outer surface of the liner and including a plurality of axially extending fingers. The mounting assembly also includes a radially outer ring coupled to the inner ring through a plurality of spacers that extend radially from a radially outer surface of the inner ring to the outer ring.

Abstract: A liner for a gas turbine engine combustor having a trapped vortex cavity formed therein, wherein a dome plate is positioned at an upstream end of the combustor, includes: a first portion positioned adjacent and connected to the dome plate, wherein the first liner portion extends downstream from and substantially perpendicular to the dome plate; a second portion extending substantially perpendicular to the first liner portion and substantially parallel to the dome plate; a first arcuate portion having a predetermined radius located between the first and second liner portions; a third portion extending downstream and substantially perpendicular to the second liner portion; and, a second arcuate portion located between the second and third liner portions; wherein the first liner portion, the second liner portion, the first arcuate liner portion and a portion of the dome plate form the trapped vortex cavity.

Abstract: A liner for a gas turbine engine combustor having a trapped vortex cavity formed therein, wherein a dome plate is positioned at an upstream end of the combustor, includes: a first portion positioned adjacent and connected to the dome plate, wherein the first liner portion extends downstream from and substantially perpendicular to the dome plate; a second portion extending substantially perpendicular to the first liner portion and substantially parallel to the dome plate; a first arcuate portion having a predetermined radius located between the first and second liner portions; a third portion extending downstream and substantially perpendicular to the second liner portion; and, a second arcuate portion located between the second and third liner portions; wherein the first liner portion, the second liner portion, the first arcuate liner portion and a portion of the dome plate form the trapped vortex cavity.