METHODS AND APPARATUS FOR RADIALLY COMPLIANT COMPONENT MOUNTING

摘要

A mounting assembly for a liner of a gas turbine engine combustor and a gas turbine engine are provided to reduce in the combustor pressure drop and increase net power output of a gas turbine. A mounting assembly(200) for a liner of a gas turbine engine combustor includes an inner ring(208) and a radially outer ring(226). The inner ring surrounds the radial outer surface of a liner(9), and includes a plurality of fingers(210) extended in the axial direction. The radially outer ring is joined to the inner ring via a plurality of spacers. The spacers are extended from the radially outer surface of the inner ring to the radially outer ring in a radial direction.