Gas turbine engine air intake in a nacelle
View Patent ↗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.
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.
2. The assembly of a gas turbine engine and of a nacelle as claimed in claim 1 , wherein the foreign-object deflection member blocks any ballistic trajectory passing through the air inlet from entering the main engine air supply passage.
3. The assembly of a gas turbine engine and of a nacelle as claimed in claim 1 , wherein the deflection member is in a shape of an axisymmetric bullet which forms an annular air intake passage with the air inlet fairing which is of annular shape.
4. The assembly of a gas turbine engine and of a nacelle as claimed in claim 1 , the decrease of the area of the cross section of the secondary passage, transverse to the direction in which the air flows, between the inlet and the outlet of the secondary passage is achieved by azimuthal reduction.
5. The assembly of a gas turbine engine and of a nacelle as claimed in claim 1 , wherein the secondary deflection passage is formed of at least two separate ducts with an annular inlet that is common and outlets with openings distributed around the periphery of the nacelle.
6. The assembly of a gas turbine engine and of a nacelle as claimed in claim 1 , wherein an air discharge opening in the wall of the nacelle is configured such that the airflow is directed along the axis of the engine.
7. The assembly of a gas turbine engine and of a nacelle as claimed in claim 1 , wherein the nacelle comprises a removable cowling element in the continuation of said air inlet fairing, and
wherein the secondary deflection passage comprises at least one portion of the secondary deflection passage that forms a deflection scoop and is secured to said removable cowling element.
8. The assembly of a gas turbine engine and of a nacelle as claimed in claim 7 , further comprising a removable cowling element articulated about an axis parallel to the axis of the engine so as to uncover the engine.
9. The assembly of a gas turbine engine and of a nacelle as claimed in claim 1 , wherein the object deflection member is in a shape of an axisymmetric bullet which forms an annular air intake passage with the air inlet fairing which is of annular shape, the deflection member being supported at least in part by a first hub casing including an internal hub, by being engaged in said internal hub.
10. The assembly of a gas turbine engine and of a nacelle as claimed in claim 9 , wherein said first hub casing is fixed to the engine by a second hub casing that forms a plane for suspending the engine from an aircraft.
11. The assembly of a gas turbine engine and of a nacelle as claimed in claim 10 , further comprising a cowling element articulated about an axis parallel to the axis of the engine so as to uncover the engine, a portion of the secondary deflection passage secured to the articulated cowling element having upstream surfaces that press in a fluidtight manner against bearing surfaces forming the secondary deflection passage inside the air inlet fairing.
12. The assembly of a gas turbine engine and of a nacelle as claimed in claim 11 , wherein said bearing surfaces are formed on the second hub casing.
13. The assembly of a gas turbine engine and of a nacelle as claimed in claim 11 , wherein fan blades of the gas turbine engine are disposed downstream of the outlet of the secondary deflection passage.