Patent ID: 8726631
Filing Date: 2014-05-20
Classification: F02C,F05D,F23R,Y02T

Abstract:
1. A combustor for a gas turbine engine, comprising: an inner liner; an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner, the outer liner being a dual walled liner with a first wall and a second wall, the first and second walls defining a liner cavity; a fuel igniter comprising a tip portion configured to ignite an air and fuel mixture in the combustion chamber; and an igniter support assembly positioning the fuel igniter relative to the combustionchamber, the igniter support assembly defining a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter, the igniter support assembly comprising first and second floating seals that are configured to accommodate radial and axial relative movements, wherein the igniter support assembly further comprises a first boss configured to couple the igniter support assembly on the first wall and a second boss configured to couple the igniter support assembly on the second wall, the second boss attached to the second wall, wherein the second floating seal is retained by the first boss in a radial direction and is movable relative to the first boss in an axial direction, wherein the second floating seal is retained in the axial direction by the second boss and is movable relative to the second boss in the radial direction, wherein the first and second walls are continuous annular walls; and wherein the second boss includes a protrusion extending into the liner cavity to at least partially define a gap between the first boss and the second boss.