Anti-torque rotor for a helicopter

Patent metadata

Field	Value
Publication number	US-11577829-B2
Application number	US-202017059710-A
Country	US
Kind code	B2
Filing date	May 26, 2020
Priority date	Jun 17, 2019
Publication date	Feb 14, 2023
Grant date	Feb 14, 2023

Abstract

An anti-torque rotor is described for a helicopter, comprising: a mast rotatable about a first axis; a plurality of blades hinged on the mast, extending along respective second axes transversal to said first axis and rotatable about respective said second axes to alter the respective angles of attack; a control element sliding and rotating with respect to the mast, and operatively connected to said blades to cause the rotation of said blades about respective second axes following a translation of said element along the first axis; a control rod sliding axially along first axis with respect to the mast and angularly fixed with respect to the first axis; and a bearing interposed between the control rod and the control element, sliding along the first axis with respect to the mast and integrally with the control rod; the anti-torque rotor further comprises an interface made of an antifriction material interposed between said control rod and said bearing.

First claim

The invention claimed is:

1. An anti-torque rotor ( 4 , 4 ′) for a helicopter ( 1 ), comprising:
a mast ( 6 ), rotatable about a first axis (A);
a plurality of blades ( 8 ), hinged on said mast ( 6 ), extending along respective second axes (B) transversal to said first axis (A) and rotatable about respective said second axes (B) to alter the respective angles of attack;
a control element ( 16 ), sliding along said first axis (A) with respect to said mast ( 6 ), integrally rotating with said mast ( 6 ), and operatively connected to said blades ( 8 ) to cause the rotation of said blades ( 8 ) about respective said second axes (B) following a translation of said control element ( 16 ) along said axis (A);
a control rod ( 10 ), sliding axially along said first axis (A) with respect to said mast ( 6 ) and angularly fixed with respect to said first axis (A); and
a bearing ( 17 ), interposed between said control rod ( 10 ) and said control element ( 16 ), sliding along said first axis (A) with respect to said mast ( 6 ) and integrally with said control rod ( 10 ), and configured to enable the relative rotation of said control element ( 16 ) with respect to said control rod ( 10 ) about said first axis (A) in a correct operating condition;

said anti-torque rotor ( 4 , 4 ′) further comprising:
an interface ( 120 ) made of an antifriction material interposed between said control rod ( 10 ) and said bearing ( 17 ), so as to enable the rotation of said bearing ( 17 ) with respect to said control rod ( 10 ) about said first axis (A) in the event of failure of said bearing ( 17 ); and
a sleeve ( 90 ) radially interposed between said control rod ( 10 ) and said bearing ( 17 ), and axially sliding integrally with said control rod ( 10 ) and said bearing ( 17 );

said interface ( 120 ) comprising at least a first surface ( 94 ) of said sleeve ( 90 ), which is arranged is contact with said control rod ( 10 ), so as to enable the rotation of said sleeve ( 90 ) jointly with said bearing ( 17 ), with respect to said control rod ( 10 );
said anti-torque rotor ( 4 , 4 ′) further comprising at least a first sensor ( 53 ) adapted to detect the rotation of said sleeve ( 90 );
said bearing ( 17 ) comprising:
an outer ring ( 30 ) integrally rotating with said control element ( 16 ) about said first axis (A);
an inner ring ( 31 ) radially internal to said outer ring ( 30 ) with respect to said first axis (A) and integrally sliding with said control rod ( 10 ) along said first axis (A); and
a plurality of rolling bodies ( 32 ), which are interposed between said outer and inner rings ( 30 , 31 ) and adapted to roll on respective raceways ( 33 , 34 ) of said outer and inner rings ( 30 , 31 );

said inner ring ( 31 ) being in contact with said sleeve ( 90 ) on the side opposite to said rolling bodies ( 32 ) along a direction radial to said first axis (A);
said anti-torque rotor ( 4 , 4 ′) further comprising an anti-torque rotor transmission unit ( 45 ), which is operatively connected to said control rod ( 10 ) and to said control element ( 16 );
said anti-torque rotor transmission unit ( 45 ) being configured to operate:
in an active configuration, causing said control element ( 16 ) to slide, following the translation of said control rod ( 10 ), along said first axis (A); or
in an inactive configuration, wherein the anti-torque rotor transmission unit ( 45 ) is disengaged from said control element ( 16 );

wherein said anti-torque rotor transmission unit ( 45 ) being arranged in said active configuration in case of failure of the bearing ( 17 ), wherein said bearing ( 17 ) is no longer able to transmit an axial load from said control rod ( 10 ) to said control element ( 16 ), causing the axial translation in both directions of said control element ( 16 ), following the axial translation of said control rod ( 10 );
and said anti-torque rotor transmission unit ( 45 ) being arranged in said inactive configuration when said bearing ( 17 ) correctly allows relative rotation of said control element ( 16 ) with respect to said control rod ( 10 ) and prevents any relative translation between said control element ( 16 ) and said control rod ( 10 );
wherein said anti-torque rotor ( 4 , 4 ′) further comprises a second sensor ( 52 ) adapted to generate a signal associated with the fact of said anti-torque rotor transmission unit ( 45 ) being in said active configuration.

2. A rotor according to claim 1 , characterized in that said interface ( 120 ) comprises the entire said sleeve ( 90 ).

3. A rotor according to claim 1 , characterized in that said interface ( 120 ) comprises a second surface ( 18 ) of said control rod ( 10 ) having an axial extension and arranged in contact with said first surface ( 94 ).

4. A rotor according to claim 1 , characterized in that said sleeve ( 90 ), in turn, comprises:
a first main body ( 91 ) radially interposed between said bearing ( 17 ) and said control rod ( 10 ); and
an axial end ridge ( 92 ), which radially projects from said first main body ( 91 ) towards said bearing ( 17 ).

5. A rotor according to claim 4 , characterized in that said interface ( 120 ) further comprises a third surface ( 122 ) of said axial end ridge ( 92 ) arranged in abutment against a shoulder ( 121 ) of said control rod ( 10 ).

6. A rotor according to claim 5 , characterized in that said interface ( 120 ) further comprises said shoulder ( 121 ) of said control rod ( 10 ) in contact with said third surface ( 122 ).

7. A rotor according to claim 1 , characterized in that said anti-torque rotor transmission unit ( 45 ), in turn, comprises:
an annular ridge ( 61 ), axially integral with said control rod ( 10 ) and radially projecting from said control rod ( 10 ); and
a seat ( 64 ) engaged by said annular ridge ( 61 ) and angularly integral with said control element ( 16 ).

8. A rotor according to claim 7 , characterized in that said anti-torque rotor transmission unit ( 45 ) comprises a cylindrical body sleeve ( 60 ) mounted coaxially on said control rod ( 10 ) and from which said annular ridge ( 61 ) projects from the side radially opposite to said control rod ( 10 );
said inner ring ( 31 ) being axially blocked between said cylindrical body ( 60 ) and said radially projecting axial end ridge ( 92 ) of said sleeve ( 90 );
said interface ( 120 ) comprising a fourth surface ( 140 ) of said cylindrical body ( 60 ) arranged in contact with said inner ring ( 31 ).

9. An anti-torque rotor ( 4 , 4 ′) for a helicopter ( 1 ), comprising:
a mast ( 6 ), rotatable about a first axis (A);
a plurality of blades ( 8 ), hinged on said mast ( 6 ), extending along respective second axes (B) transversal to said first axis (A) and rotatable about respective said second axes (B) to alter the respective angles of attack;
a control element ( 16 ), sliding along said first axis (A) with respect to said mast ( 6 ), integrally rotating with said mast ( 6 ), and operatively connected to said blades ( 8 ) to cause the rotation of said blades ( 8 ) about respective said second axes (B) following a translation of said control element ( 16 ) along said axis (A);
a control rod ( 10 ), sliding axially along said first axis (A) with respect to said mast ( 6 ) and angularly fixed with respect to said first axis (A); and
a bearing ( 17 ), interposed between said control rod ( 10 ) and said control element ( 16 ), sliding along said first axis (A) with respect to said mast ( 6 ) and integrally with said control rod ( 10 ), and configured to enable the relative rotation of said control element ( 16 ) with respect to said control rod ( 10 ) about said first axis (A) in a correct operating condition;
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Assignees

• Leonardo Spa

Inventors

• Delli Paoli Michele
• Nannoni Fabio
• Vanni Roberto

Classifications

• B64C27/605

  including swash plate, spider or cam mechanisms · CPC title

• F16C39/02

  using mechanical means · CPC title

• F16C2326/43

  Aeroplanes; Helicopters · CPC title

• B64C27/82 Primary

  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

• B64C27/78

  in association with pitch adjustment of blades of anti-torque rotor · CPC title