Epicyclic gear train for an aircraft capable of hovering
An epicyclic gear train, for an aircraft capable of hovering, having a sun gear rotating about a first axis; a fixed ring gear positioned coaxially with the first axis and radially outwards with respect to the sun gear; a number of planet gears, which are interposed between and mesh with the sun gear and the ring gear, and rotate about respective second axes, in turn revolving about the first axis; and lubricant feed means; the feed means having a number of nozzles arranged about the first axis and the sun gear to produce an annular flow of lubricant.
1. An epicyclic gear train ( 6 ), for an aircraft ( 1 ) capable of hovering, comprising:
a sun gear ( 7 ) rotating about a first axis (A) and having external teeth ( 8 );
a fixed ring gear ( 9 ) having internal teeth ( 10 ) and positioned coaxially with said first axis (A) and radially outwards with respect to said sun gear ( 7 );
a number of planet gears ( 11 ), which have respective external teeth ( 12 ), are interposed between and mesh with the teeth ( 8 , 10 ) of said sun gear ( 7 ) and said ring gear ( 9 ), and rotate about respective second axes (B), in turn revolving about said first axis (A); and
lubricant feed means ( 16 ) comprising a number of nozzles ( 17 ) arranged about said first axis (A) and said sun gear ( 7 ) to produce a flow (F) of said lubricant;
the gear train being characterized in that said flow is an annular flow; and
wherein said feed means ( 16 ) comprises a distributor ( 18 ) extending about said first axis (A) and having said nozzles ( 17 ), said distributor ( 18 ) comprising two substantially C-shaped conduits ( 19 ) located on diametrically-opposite sides of said first axis (A) with their respective concavities facing.
2. A gear train as claimed in claim 1 , wherein said conduits ( 19 ) form two halves of said distributor ( 18 ).
3. A gear train as claimed in claim 1 , wherein each said conduit ( 19 ) has a jagged profile and is formed in one piece.
4. A gear train as claimed in claim 3 , wherein each said conduit ( 19 ) comprises a number of straight portions ( 20 ), each forming an angle of less than 180° with the adjacent straight portion/s ( 20 ).
5. A gear train as claimed in claim 4 , wherein each said straight portion ( 20 ) has a longitudinal hole ( 21 ) communicating with the longitudinal hole/s ( 21 ) of the adjacent straight portion's ( 20 ) to permit throughflow of said lubricant.
6. A gear train as claimed in claim 5 , wherein each said straight portion ( 20 ) has one end ( 22 ) connected to the longitudinal hole ( 21 ) of an adjacent straight portion ( 20 ); and an opposite, outwardly-open end ( 23 ) accessible from the outside and sealed, in use, by a respective plug ( 24 ).
7. A gear train as claimed in claim 5 , wherein said nozzles ( 17 ) are defined by transverse holes formed in said straight portions ( 20 ) of said conduits ( 19 ) and communicating with said longitudinal holes ( 21 ).
8. A gear train as claimed in claim 1 , wherein, for each said conduit ( 19 ), said distributor ( 18 ) comprises a branch ( 25 ) projecting from the conduit ( 19 ), in the opposite direction to the other said conduit ( 19 ), and having a feed inlet ( 26 ) for said lubricant.
9. A gear train as claimed in claim 1 , wherein said ring gear ( 9 ) is fixed to a supporting plate ( 15 ) supporting said feed means ( 16 ).
10. An aircraft ( 1 ) capable of hovering comprising:
a rotor ( 3 );
a drive member; and
a transmission ( 5 ) interposed between said rotor ( 3 ) and said drive member, and comprising an epicyclic gear train ( 6 ) as claimed in claim 1 ;
said epicyclic gear train ( 6 ) comprising a planet carrier ( 13 ) connected to said planet gears ( 11 );
either one ( 7 ) of said sun gear ( 7 ) and said planet carrier ( 13 ) receiving a torque from said drive member;
and the other ( 13 ) of said sun gear ( 7 ) and said planet carrier ( 13 ) being connected to a drive shaft of said rotor ( 3 ).