Turboprop air intake
View Patent ↗A turboprop includes a rotary propeller upstream from an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, the bypass having an outlet oriented substantially axially towards the downstream of the engine. The turboprop further includes a nacelle surrounding the engine and the air intake, wherein the air intake is secured to a housing of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle. The outlet is connected by a flexible link to an intake of an air circuit carried by the nacelle.
1. A turboprop engine comprising a rotary propeller upstream of an engine having an engine housing with an air intake that is not coaxial to the propeller, said air intake defining a main conduit for supplying air to the engine and further defining a bypass to said main conduit, said bypass comprising an outlet that is oriented axially in a downstream direction of the engine, the turboprop engine further comprising a nacelle surrounding the engine and the air intake, wherein the air intake comprises, at an end of the main conduit, a peripheral flange for fixing to a corresponding flange of the air intake and wherein the air intake is not rigidly connected to the nacelle so as to allow relative movements between the air intake and the nacelle during operation, said outlet being connected by means of a flexible link to an intake of an air system borne by the nacelle, wherein the turboprop engine comprises means for suspending the air intake from a housing of a gearbox.
2. The turboprop engine according to claim 1 , wherein the air intake is fixed to said engine housing via a downstream end of the air intake, the main conduit that is defined by the air intake opening via the downstream end of the air intake into a duct that is defined by said engine housing.
3. The turboprop engine according to claim 1 , wherein the flange of the air intake is configured for bolt-fixing to the engine housing.
4. The turboprop engine according to claim 1 , wherein the air intake comprises a lip at an upstream end of the air intake, a seal being mounted between the lip and the nacelle.
5. The turboprop engine according to claim 1 , wherein the means for suspending comprise connecting rods that are hinged at two ends thereof.
6. The turboprop engine according to claim 1 , wherein the means for suspending is a torque-absorbing bar.
7. The turboprop engine according to claim 1 , wherein the air system that is borne by the nacelle comprises a heat exchanger that is cooled by the air from the bypass.
8. A turboprop engine comprising a rotary propeller upstream of an engine having an engine housing with an air intake that is not coaxial to the propeller, said air intake defining a main conduit for supplying air to the engine and further defining a bypass to said main conduit, said bypass comprising an outlet that is oriented axially in a downstream direction of the engine, the turboprop engine further comprising a nacelle surrounding the engine and the air intake,
the air intake comprising, at an end of the main conduit, a peripheral flange for fixing to a corresponding flange of the air intake of an engine housing and being not rigidly connected to the nacelle so as to allow relative movements between the air intake and the nacelle during operation, said outlet being connected by means of a flexible link to an intake of an air system borne by the nacelle, wherein said air intake comprises, at a downstream end thereof, said flange for fixing to the engine housing of the turboprop engine and comprises means for attaching to means for suspending from a housing of a gearbox of the turboprop engine.
9. The air intake according to claim 8 , wherein said turboprop engine comprises, at an upstream end of the air intake, a lip having a seal that forms a flexible link that engages with the nacelle of the turboprop engine.
10. The turboprop engine according to claim 8 , wherein the means for attaching comprises at least one clevis.