Gas turbine engine air intake in a nacelle

摘要

An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle.

主权项

1. An assembly of a gas turbine engine and of a nacelle in which the gas turbine engine is housed, the nacelle comprising an air inlet fairing forming an air inlet comprising:
a foreign-object deflection member positioned inside the air inlet fairing, the deflection member and an interior wall of the air inlet fairing delimiting an air intake duct; a secondary deflection passage disposed downstream of the deflection member and including an inlet and an outlet opening via opening in an exterior wall of the nacelle; a main engine air supply passage disposed downstream of the deflection member and leading to an inlet of a compressor of the gas turbine engine, the main engine air supply passage being concentric with and inside of the secondary deflection passage; said air intake duct being configured to deflect at least some foreign objects that have been aspirated by the air inlet toward the secondary deflection passage, wherein an upstream edge of a surface splits the air inlet between the secondary deflection passage and the main engine air supply passage, wherein the secondary deflection passage is delimited by first and second substantially radial walls extending longitudinally between the inlet and the outlet, a radially interior cylindrical wall, and a radially exterior cylindrical wall in continuation with the interior wall of the air inlet fairing, the walls delimiting the secondary deflection passage being fixed relative to each other, and wherein an area of a cross section of the secondary deflection passage, transverse to a direction in which the air flows, progressively decreases between the inlet and the outlet of the secondary deflection passage such that a speed at which the air passing through the secondary deflection passage flows is increased from upstream to downstream.