A transition duct for a gas turbine engine

摘要

A transition duct for a gas turbine engine typically contains one or more non-turning fairings (12). These fairings (12) disturb the air flow through the duct, leading to flow separation and aerodynamic inefficiency. The invention proposes non-axisymmetric perturbations (36,38) in the duct end walls to minimise these undesirable aerodynamic effects. This permits the construction of shorter and lighter transition ducts, with more pronounced curvature.