Patent ID: 9593853
Date: 2017-03-14
CPC Classifications: F01D,F23R

Claim:
1. In a can annular gas turbine engine having a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades, a gas flow path formed by a duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades, the duct arrangement comprising: at least one straight section having a centerline that is misaligned with a centerline of the combustor; and an integrated exit piece (IEP) having an inlet section associated with the annular chamber, and a cone section having an inlet end receiving the gas flow and an outlet end connected to an inlet end of the inlet section, and wherein an end of the at least one straight section includes a joint formed by a band clamp permitting a misalignment between centerlines along the duct arrangement, wherein the end of the at least one straight section includes a flange cooperating with a flange on an adjacent element of the duct arrangement, and adjoining surfaces of the flanges are formed by spherical surfaces engaged against each other.