THERMALLY FREE LINER RETENTION MECHANISM

摘要

The present invention discloses a novel and improved device and method for securing a combustion liner within a gas turbine combustor. The improved configuration comprises a plurality of equally spaced support tab assemblies (712) secured about the combustion liner and positioned radially outward of the combustion zone. The support tab assemblies (712) comprise parallel liner tabs (714) which provide increased flexibility, greater structural support, and lower operating stresses.