Patent ID: 8056346
Filing Date: 2011-11-15
Classification: F23R

Abstract:
1. A combustor for a gas turbine engine comprising: a plurality of liners to define a substantially enclosed space where combustion of a fuel-air mixture takes place, the liners defining an open aft end where hot gases from the combustion escape the combustor at high speeds and, are directed toward a turbine; the plurality of liners including at least a first dome and a second dome one of the first dome or the second dome having a plurality of impingement-holes to allow cooling air to pass through and impinge on the other of the first dome or the second dome; a connection assembly positioned between the first dome and the second dome the connection assembly defining an opening in which a fuel injector may be positioned to inject a fuel-air mixture into the substantially enclosed space for combustion, the second dome being directly fixed to the connection assembly, the first dome being retained in a groove formed in the connection assembly, the groove and the first dome defining a non-uniform gap therebetween so that the first dome through thermal expansion is permitted to move relative to the second dome in an aligned radial direction, but is not permitted to move relative to the second dome in any other direction.