Control device for the pitch of blades, and propeller

Patent metadata

Field	Value
Publication number	US-9816385-B2
Application number	US-201414340111-A
Country	US
Kind code	B2
Filing date	Jul 24, 2014
Priority date	Jul 24, 2013
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

A control device of the pitch of blades of a rotor of a propeller is provided. The control device includes: a radial shaft; a pivot connected to the blade, the rotation of the radial shaft driving the rotation of the pivot for the modification of the pitch of the blade; an insert fixed rigidly to the pivot so as to block their relative displacement, the radial shaft being configured to drive in rotation the insert; at least one peg passing through the insert and the pivot for transmission of the rotation of the insert to the pivot; and a heat insulation element arranged between the insert and the pivot, whereof the thermal conductivity is less than the thermal conductivity of the pivot and of the radial shaft.

First claim

The invention claimed is:

1. A control device of the pitch of blades of a rotor of a propeller, comprising:
a radial shaft;
a pivot connected to the blade, a foot of the blade being mounted in the pivot, rotation of the radial shaft driving rotation of the pivot for modifying the pitch of the blade;
an insert fixed rigidly to the pivot so as to block a relative displacement of the insert with respect to the pivot, the insert being in direct contact with the radial shaft, the radial shaft being configured to drive in rotation the insert via rotation transmission elements borne respectively on an external surface of the radial shaft and an inner surface of the insert, the insert comprising a fixing flange;
at least one peg passing through the fixing flange of the insert and the pivot for transmission of the rotation of the insert to the pivot; and
a heat insulation element interposed between the fixing flange of the insert and the pivot, a thermal conductivity of the heat insulation element is less than a thermal conductivity of the pivot and a thermal conductivity of the radial shaft.

2. The device according to claim 1 , wherein the insert is fixed to the pivot by at least one screw.

3. The device according to claim 2 , wherein the heat insulation element encloses a circumference of at least one part of the peg or of the at least one screw.

4. The device according to claim 1 , wherein the heat insulation element consists in an air gap.

5. The device according to claim 4 , wherein the air gap has a height of less than or equal to 1 mm.

6. The device according to claim 1 , wherein the heat insulation element includes a material in which the thermal conductivity is less than the thermal conductivity of the pivot and the thermal conductivity of the radial shaft.

7. The device according to claim 6 , wherein the heat insulation element comprises an annular piece comprising:
a central opening, for passage of the radial shaft, and
one or more circumferential openings.

8. The device according to claim 6 , wherein the heat insulation element comprises one or more separate annular pieces enclosing at least one part of the peg or a screw linking the radial shaft to the pivot.

9. The device according to claim 6 , wherein the thermal conductivity of the material of the heat insulation element is between 0.01 and 10 W/m/K at 20° C.

10. A propeller comprising a rotor and blades, and a control device of the pitch of the blades according to claim 1 .

11. A control device of the pitch of blades of a rotor of a propeller, comprising:
a radial shaft;
a pivot connected to the blade, rotation of the radial shaft driving rotation of the pivot for modifying the pitch of the blade;
an insert fixed rigidly to the pivot so as to block a relative displacement of the insert with respect to the pivot, the radial shaft being configured to drive in rotation the insert;
at least one peg passing through the insert and the pivot for transmission of the rotation of the insert to the pivot; and
a heat insulation element arranged between the insert and the pivot, a thermal conductivity of the heat insulation element is less than a thermal conductivity of the pivot and a thermal conductivity of the radial shaft,
wherein the heat insulation element includes a material in which the thermal conductivity is less than the thermal conductivity of the pivot and the thermal conductivity of the radial shaft, and
wherein the thermal conductivity of the material of the heat insulation element is between 0.01 and 10 W/m/K at 20° C.

Assignees

• Snecma

Inventors

• Fabre Adrien Jacques Philippe
• Tajan Sebastien Emile Philippe
• Jacquemard Christophe Paul
• Chartier Sarah

Classifications

• B64D2027/005

  Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR] · CPC title

• Y02T50/66

  Cross-Sectional Technologies · mapped topic

• B64C11/06 Primary

  for variable-pitch blades · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F01D7/00 Primary

  Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30) · CPC title