BLEED DUCT FOR LAMINAR FAN DUCT FLOW

摘要

A disclosed gas turbine engine includes a fan including a plurality of fan blades rotatable about an engine axis and core engine disposed within a core nacelle for driving the fan. A bypass passage is defined between the core nacelle and an outer or fan nacelle. A duct mounted within the core nacelle defines a bleed air flow path for directing bleed air from the core engine into the bypass passage. The bleed air duct includes a plurality of airfoils disposed at a defined chord angle for directing bleed airflow into the bypass passage to minimize disruption to bypass airflow.

主权项

1. A gas turbine engine comprising:
a fan including a plurality of fan blades rotatable about an engine axis; a core engine disposed within a core nacelle for driving the fan; a fan nacelle circumscribing the fan; a bypass passage defined between the core nacelle and the fan nacelle; and a duct mounted within the core nacelle defining a bleed air flow path for directing bleed air from the core engine into the bypass passage, wherein the duct includes a plurality of airfoils that define a corresponding plurality of passages through the core nacelle bounded on one side by a suction side of one airfoil and a pressure side of an adjacent airfoil, wherein the duct includes a forward side and an aft side wherein each of the forward side and the aft side include a partial airfoil shape corresponding to the shape of the plurality of airfoils.