Rotor for an aircraft capable of hovering

Patent metadata

Field	Value
Publication number	US-11111011-B2
Application number	US-201716474097-A
Country	US
Kind code	B2
Filing date	Dec 29, 2017
Priority date	Dec 30, 2016
Publication date	Sep 7, 2021
Grant date	Sep 7, 2021

Abstract

A rotor for an aircraft capable of hovering includes a stationary support structure and a rotative element which is rotatable about an axis with respect to the stationary support structure. The rotor has at least one blade, which is operatively connected with a rotative element. The rotor has a source of a magnetic field, which is either stationary or driven in rotation at a first rotational speed and an electric conductive element, which is operatively connected to the rotative element and can be driven in rotation at a second rotational speed different from first rotational speed. An electric conductive element is electromagnetically coupled so that an electromotive force is magnetically induced in electric conductive element itself Two rings extend radially inward from a tubular body of the rotor hub with the first ring connected to a plurality of thermally conductive rings of a flow deflector at an axial end of the rotor and the second ring supports the electric conductive element.

First claim

The invention claimed is:

1. An aircraft ( 1 ) capable of hovering comprising:
a fuselage ( 2 );
a main transmission group ( 7 ); and
a main rotor ( 3 , 3 ′, 3 ″, 3 ′″, which is connected to said main transmission group ( 6 ) and is adapted to provide said aircraft ( 1 ) with the lift to raise it;
said main rotor ( 3 , 3 ′, 3 ″, 3 ′″) comprising:
a stationary support structure ( 10 ) fixed to said fuselage ( 2 );
a rotative element ( 11 ), which is rotatable about a first axis (A) with respect to said stationary support structure ( 10 );
at least one blade ( 13 ) which is operatively connected with said rotative element ( 11 );
a source ( 30 ) of a magnetic field, which is either stationary or driven, in use, in rotation; and
an electric conductive element ( 32 ), which is operatively connected to said rotative element ( 11 ) and can be driven, in use, in rotation;
said electric conductive element ( 32 ) being electromagnetically coupled with said source ( 30 ), so that an electromotive force is magnetically induced, in use, in said electric conductive element ( 32 ) itself;
said rotor ( 3 , 3 ′, 3 ″, 3 ′″) further comprising:
a hub ( 12 ) operatively connected to said rotative element ( 11 ), rotatable with said second rotational speed (ω 2 ) about said first axis (A) and onto which said blade ( 13 ) is articulated; and
a support element ( 36 , 36 ′, 36 ″) to which said source ( 30 ) is fixed, and which is either stationary or rotatable with said first rotational speed (ω 1 ) about said first axis (A);
said electric conductive element ( 32 ) being fixed to said hub ( 12 );
characterized in that said rotor ( 3 , 3 ′, 3 ″, 3 ′″) comprises a flow deflector ( 85 ), which is arranged at an axial end of said rotor ( 3 , 3 ′, 3 ″, 3 ′″), is rotatable about said first axis (A) integrally with said hub ( 12 ) and defines a compartment housing at least in part said support element ( 36 , 36 ′);
said hub ( 12 ) comprising:
a tubular body ( 51 ) and a first and a second ring ( 52 , 53 ) which extend from said tubular body ( 51 ) towards said first axis (A) and orthogonally to said first axis (A);
said electric conductive element ( 32 ) being fitted to said second ring ( 53 );
said flow deflector ( 85 ) being made in metal and comprising a plurality of thermally conductive rings ( 90 ), which are connected to said first ring ( 52 , 52 ′).

2. The aircraft of claim 1 , characterized by comprising: a first epicyclic gear train ( 17 );
said first epicyclic gear train ( 17 ) comprising:
a sun gear ( 20 ) which is connectable to an output shaft of said main transmission group ( 7 ) of said aircraft ( 1 );
a crown gear ( 23 ) which is defined by and forms part of said support structure ( 10 );
a plurality of planetary gears ( 21 ) which simultaneously mesh with said sun gear ( 20 ) and said crown gear ( 23 ); and
a first carrier ( 22 ), which is connected to said planetary gears ( 21 ) and to said rotative element ( 11 , 151 );
said planetary gears ( 21 ) being rotatable about respective second axes (E) parallel and distinct from said first axis (A) and being mounted to revolute about said first axis (A).

3. The aircraft of claim 2 , characterized by comprising:
a connecting element ( 35 ), which is connected to said support structure ( 10 ) and stationary about said first axis (A); and
a second epicyclic gear train ( 37 , 37 ′), which is functionally interposed between said connecting element ( 35 ) and said support element ( 36 , 36 ′).

4. The aircraft of claim 3 , characterized in that said second epicyclic gear train ( 37 , 37 ′) comprises:
a first gear ( 45 ), which is defined by said support element ( 36 , 36 ′) and is rotatable about said first axis (A);
a second gear ( 48 ) rotationally integral with and driven in rotation, in use, by said hub ( 12 ) about said first axis (A);
at least one pair of third planetary gears ( 46 ); and
a second carrier ( 47 ) which is connected with said third planetary gears ( 46 );
said third planetary gears ( 46 ) simultaneously meshing with said first gear ( 45 ) and said second gear ( 48 ), being rotatable about respective third axes (F) parallel and distinct from said first axis (A) and being mounted to revolute about said first axis (A).

5. The aircraft of claim 4 , characterized in that said second carrier ( 47 ) is connected to said support structure ( 10 ) and is stationary about said first axis (A).

6. The aircraft of claim 4 , characterized in that said hub ( 12 ) further comprises a fourth ring ( 48 ), which extends from said body ( 10 ) towards said first axis (A) and orthogonally to said first axis (A); said fourth ring ( 48 ) being axially interposed between said second and third ring ( 53 , 52 , 52 ′);
said ring ( 48 ) comprising a radially inner toothing with respect to said first axis (A) meshing with radially outer toothing of said third planetary gears ( 46 ).

7. The aircraft of claim 4 , wherein the source ( 30 ) of the magnetic field is driven, in use, in rotation at a first rotational speed (ω 1 ); and the electric conductive element ( 32 ), is driven, in use, in rotation at a second rotational speed (ω 2 ) different from said first rotational speed (ω 1 ).

8. The aircraft of claim 7 , characterized in that said second carrier ( 47 ) is connected to said sun gear ( 20 ) of said first epicyclic gear ( 17 ) and is rotatable about said first axis (A) with a third rotational speed (ω 0 ) different from said first and second rotational speed (ω 1 , ω 2 ).

9. The aircraft of claim 3 , characterized in that said second epicyclic gear train ( 37 ′) and said support element ( 36 ′) are axially contained inside the axial size of said hub ( 12 ).

10. The aircraft of claim 1 , characterized in that said flow deflector ( 85 ) comprises at least one of: an electrical power storage means ( 89 ) electrically connected to said electrical conductive element ( 32 ) and heat dissipating means ( 90 ) for dissipating the heat generated, in use, by said source ( 30 ) and said electrical conductive element ( 32 ).

11. The aircraft of claim 1 , characterized in that said support element ( 36 , 36 ′, 36 ″) comprise a pair of thirds rings ( 39 , 40 ) which support respective sources ( 30 ) in a position in which they axially face with one another along said first axis (A);
said second ring ( 53 ) being axially interposed between said third rings ( 39 , 40 ) along said first axis (A).

12. The aircraft of claim 1 , characterized by comprising electrical connecting means ( 87 ), which are interposed between said electrical conductive element ( 32 , 169 ) and said at least one blade ( 13 , 154 );
said electrical connecting means ( 87 ) being connected to an anti-icing system embedded inside said at least one blade ( 13 ).

13. The aircraft of claim 1 , wherein the source ( 30 ) of the magnetic field is driven, in use, in rotation at a first rotational speed (ω 1 ); and the electric conductive element ( 32 ), is driven, in use, in rotation at a second rotational speed (ω 2 ) different from said first rotational speed (ω 1 ).

Assignees

• Leonardo Spa

Inventors

• Bottasso Luigi
• Zocchi Antonio
• Brunetti Massimo
• Medici Luca
• Wang James
• Lucchi Giorgio

Classifications

• B64D15/12

  by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• H02K11/00

  Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection (casings, enclosures or supports H02K5/00) · CPC title

• B64C27/82

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• B64C27/12

  Rotor drives · CPC title