Unducted-fan aircraft engine including a propeller comprising vanes with roots outside the nacelle and covered by detachable covers
The invention relates to an unducted-fan aircraft engine comprising a generally cylindrical nacelle through which a primary jet flows, the nacelle bearing a fan rotor comprising variable-pitch vanes ( 33 ) located radially outside the nacelle in order to be traversed by a secondary jet ( 31 ) flowing longitudinally around the nacelle. The rotor comprises a hub bearing variable-pitch vane supports each carrying one vane ( 33 ), each vane ( 33 ) comprising a blade extending from a root that is used to removably attach same to a base of the associated support ( 34 ). Each base ( 36 ) is located radially outside the nacelle so that it is in the secondary jet, and each assembly formed by a base ( 36 ) and the vane root supported by the base ( 36 ) is surrounded and covered by a detachable aerodynamic cover ( 37 ).
1. Unducted-fan aircraft engine, said engine comprising a generally cylindrical nacelle through which a primary jet flows, said nacelle bearing a fan rotor comprising variable-pitch vanes located radially outside the nacelle in order to be traversed by a secondary jet flowing longitudinally around said nacelle, said rotor comprising a hub bearing variable-pitch vane supports each carrying one of said variable-pitch vanes, each of said variable-pitch vanes comprising a blade extending from a root that is used to removably attach said blade to a base of the support bearing said blade, wherein each of said bases is located radially outside the nacelle so that each of said bases is in the secondary jet, and in that each assembly, formed by one of said bases and the respective root supported by said one of said bases, is surrounded and covered by a detachable aerodynamic cover.
2. The engine according to claim 1 , wherein at least one of the aerodynamic covers comprises an upstream half-cover and a downstream half-cover that respectively surround an upstream portion and a downstream portion of the respective assembly, formed by one of said bases and the respective root supported by said one of said bases.
3. The engine according to claim 1 , wherein at least one of the aerodynamic covers is movable while being rigidly secured to the respective assembly, formed by one of said bases and the respective root supported by said one of said bases.
4. The engine according to claim 1 , wherein at least one of the aerodynamic covers is stationary while being secured to a collar of the hub in order to be stationary relative to the hub.
5. The engine according to claim 4 , wherein the at least one of the aerodynamic covers comprises an air intake opening in the secondary jet in order to cool the vane support and an opening for discharging said cooling air.
6. The engine according to claim 5 , wherein the air intake opening and the opening for discharging said cooling air are plugged by the vane when said vane is in a reference position.
7. The engine according to claim 4 , wherein the at least one of the aerodynamic covers comprises a protuberance in the form of a flap located downstream of the vane and extending in an extension of a trailing edge of said vane.