发明申请
US20080138197A1 Transition duct for a gas turbine engine 审中-公开
燃气轮机的过渡管

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. These fairings disturb the air flow through the duct, leading to flow separation and aerodynamic inefficiency. The invention proposes non-axisymmetric perturbations 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.
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