Patent ID: 9709276
Date: 2017-07-18
CPC Classifications: B23P,F01D,F02C,F05D,F23R

Claim:
1. A method for installation of a transition duct in a gas turbine engine, comprising: positioning a guide structure extending in an inclined direction with respect to a gas turbine axis, wherein at least a portion of the guide structure is disposed between a turbine section and a combustor section of the gas turbine engine, engaging the transition duct with the guide structure such that the transition duct is movable along the guide structure, and imparting a motion to the transition duct along the guide structure in a forward-to-aft direction, to move the transition duct to an installed position in which an aft end portion of the transition duct is aligned for attachment to a forward face of a stator component of the turbine section, wherein an aft frame of the transition duct comprises attachment structures, each attachments structure having a link with a tangential pin that engages in a respective slot on the forward face of the stator, wherein each pin is rotatable about a tangential axis, such that said motion transitions from the inclined direction in relation to the turbine axis to an axial direction in relation to the turbine axis facilitated by the rotation of the pins about the tangential axis.