Transition piece for a gas turbine engine, corresponding system and method

摘要

Disclosed herein are apparatus, method, and system for cross sectional area convergence reduction and selection of a transition piece (200) of a gas turbine engine. In an embodiment, an aft end cross sectional area (210) is determined for a transition piece and a forward end cross sectional area (205) is determined for the transition piece. The transition piece may be fabricated based on a constant slope of cross sectional area change between the aft end and the forward end.