TRANSITION WITH A LINEAR FLOW PATH FOR USE IN A GAS TURBINE ENGINE

摘要

A transition duct (94) for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct (94) may have an internal passage (102) extending between an inlet (98) to an outlet (100). An axis (130) of the transition duct body (96) may be generally linear such that gases expelled from the transition duct body (96) flow in a proper direction into the downstream turbine blades.