Hover-capable aircraft
A hover-capable aircraft having propulsion means; at least one rotor; transmission means for transmitting power from the propulsion means to the rotor and lubricated with a lubricant; a heat exchanger, which receives the heated lubricant from the transmission means and feeds the cooled lubricant back to the transmission means; and a fan for producing airflow through the heat exchanger to cool the lubricant, and which has an impeller with blades, and an exhaust pipe for expelling the hot air produced by cooling the lubricant; at least one portion of the wall of the exhaust pipe has dissipating means designed to selectively absorb pressure waves in a given frequency band related to the rotation speed of the impeller and to the number of blades of the impeller.
1. A hover-capable aircraft ( 1 ) comprising:
propulsion means ( 6 );
at least one rotor ( 3 );
transmission means ( 5 ) for transmitting power from said propulsion means ( 6 ) to said rotor ( 3 ) and lubricated with a lubricant;
a heat exchanger ( 9 ), which receives the heated lubricant from said transmission means ( 5 ) and feeds the cooled lubricant back to the transmission means ( 5 ); and
a fan ( 10 ) for producing airflow through said heat exchanger ( 9 ) to cool said lubricant, and which comprises an impeller ( 16 ) with blades ( 21 ), and an exhaust pipe ( 18 ) for expelling the hot air produced by cooling said lubricant;
wherein at least one portion ( 23 ) of an outer delimiting wall ( 22 ) of said exhaust pipe ( 18 ) incorporates dissipating means ( 25 ) designed to selectively absorb pressure waves in a given frequency band related to the rotation speed (V) of said impeller ( 16 ) and to the number (N) of blades ( 21 ) of the impeller ( 16 ), wherein said exhaust pipe defines an internal flow path for the hot air with said dissipating means ( 25 ) being disposed laterally with respect to said flow path and in a manner in which said dissipating means 25 encircles at least a portion of the flow path.
2. An aircraft as claimed in claim 1 , wherein said frequency band ranges between 90% and 110% of the frequency value (f 0 ) calculated by multiplying the rotation speed (V) of the impeller ( 16 ) by the number (N) of blades ( 21 ) of the impeller ( 16 ) by the number (N) of blades ( 21 ) of the impeller ( 16 ).
3. An aircraft as claimed in claim 1 , wherein said dissipating means ( 25 ) comprise a layer ( 27 ) of sound-absorbing material designed to absorb said pressure waves by porosity.
4. An aircraft as claimed in claim 3 , wherein said layer ( 27 ) of sound-absorbing material is a fibre.
5. An aircraft as claimed in claim 3 , wherein said layer ( 27 ) of sound-absorbing material is housed in a cavity ( 26 ) of said wall ( 22 ) of said exhaust pipe ( 18 ), and said cavity ( 26 ) is bounded internally by a perforated surface ( 29 ) designed to let said pressure waves through to said layer ( 27 ) of sound-absorbing material to produce a preliminary cavity-resonance sound-absorbing effect on the pressure waves.
6. An aircraft as claimed in claim 5 , wherein said cavity ( 26 ) is bounded externally by a rigid retaining shell ( 30 ).
7. An aircraft as claimed in claim 1 , wherein said impeller ( 16 ) of said fan ( 10 ) is powered by said transmission means ( 5 ).
8. A hover-capable aircraft ( 1 ) comprising:
propulsion means ( 6 );
at least one rotor ( 3 );
transmission means ( 5 ) for transmitting power from said propulsion means ( 6 ) to said rotor ( 3 ) and lubricated with a lubricant;
a heat exchanger ( 9 ), which receives the heated lubricant from said transmission means ( 5 ) and feeds the cooled lubricant back to the transmission means ( 5 ); and
a fan ( 10 ) for producing airflow through said heat exchanger ( 9 ) to cool said lubricant, and which comprises an impeller ( 16 ) with blades ( 21 ), and an exhaust pipe ( 18 ) for expelling the hot air produced by cooling said lubricant, wherein said exhaust pipe ( 18 ) comprises a hollow structure that defines a flow path for the hot air, whereby the hot air flows along a longitudinal axis of said exhaust pipe;
wherein at least one portion ( 23 ) of an outer delimiting wall ( 22 ) of said exhaust pipe ( 18 ) incorporates dissipating means ( 25 ) designed to selectively absorb pressure waves in a given frequency band related to the rotation speed (V) of said impeller ( 16 ) and to the number (N) of blades ( 21 ) of the impeller ( 16 ), wherein said dissipating means ( 25 ) is disposed radially outward from the flow path and said longitudinal axis does not intersect said dissipating means ( 25 ).
9. An aircraft as claimed in claim 8 , wherein said dissipating means ( 25 ) circumferentially surrounds the flow path.