Propeller ring comprising radial housings with an ovoid cross-section

Patent metadata

Field	Value
Publication number	US-10526067-B2
Application number	US-201515523295-A
Country	US
Kind code	B2
Filing date	Oct 30, 2015
Priority date	Oct 31, 2014
Publication date	Jan 7, 2020
Grant date	Jan 7, 2020

Abstract

The invention relates to a propeller ring (10) of a turbomachine (1), with variable-pitch blades (P), the propeller ring (10) comprising a substantially coaxial annular body (11) with a main axis (A) and a plurality of radial housings (12) uniformly distributed around the main axis (A), each radial housing (12) being designed to receive a bearing (13) for a root (14) of a blade (P) so as to allow the variable pitch of the blade (P), the radial housings (12) having a substantially ovoid cross-section in a plane (T) tangential to the annular body (11).

First claim

The invention claimed is:

1. Propeller ring of a turbomachine with variable pitch blades, the propeller ring comprising an annular body substantially coaxial with a main axis and a plurality of radial housings uniformly distributed around the main axis, each radial housing being designed to receive a bearing for a root of a blade so as to allow variable pitch of the blade, the propeller ring wherein the radial housings have, in a plane tangential to the annular body, a substantially ovoid cross-section, said substantially ovoid cross-section having a minor diameter and a major diameter with distinct dimensions, wherein the bearing has, in the plane tangential to the propeller ring a substantially circular cross-section.

2. The propeller ring according to claim 1 , wherein the section of the radial housings is elliptical.

3. The propeller ring according to claim 1 , wherein the major diameter is greater than the minor diameter, said major diameter extending substantially parallel to the main axis of the propeller ring.

4. The propeller ring according to claim 3 , wherein the bearing comprises an outer bearing ring and a difference between the major diameter and the minor diameter of the substantially ovoid cross-section is between 0.5 and 1% of a diameter of the outer bearing ring.

5. The propeller ring according to claim 4 , wherein the diameter of the outer bearing ring is on the order of 200 mm and the difference between the major diameter and the minor diameter is between 1 mm and 2 mm.

6. The propeller ring according to claim 1 , wherein the major diameter is greater than the minor diameter, said minor diameter extending substantially parallel to the main axis of the propeller ring.

7. The propeller ring according to claim 1 , wherein the annular body has a polygonal shape.

8. A turbomachine with variable pitch blades, comprising a propeller ring according to claim 1 .

9. The turbomachine according to claim 8 , wherein the propeller is unducted.

10. Propeller ring of a turbomachine with variable pitch blades, the propeller ring comprising an annular body substantially coaxial with a main axis and a plurality of radial housings uniformly distributed around the main axis, each radial housing being designed to receive a bearing for a root of a blade so as to allow variable pitch of the blade, the propeller ring wherein the radial housings have, in a plane tangential to the annular body, a substantially ovoid cross-section, said substantially ovoid cross-section having a minor diameter and a major diameter with distinct dimensions, wherein the major diameter is greater than the minor diameter and wherein one of the major diameter and the minor diameter extends substantially parallel to the main axis of the propeller ring.

11. The propeller ring according to claim 10 , wherein the section of the radial housings is elliptical.

12. The propeller ring according to claim 10 , wherein the major diameter extends substantially parallel to the main axis of the propeller ring, the bearing comprising an outer bearing ring and a difference between the major diameter and the minor diameter of the substantially ovoid cross-section is between 0.5 and 1% of a diameter of the outer bearing ring.

13. The propeller ring according to claim 12 , wherein the diameter of the outer bearing ring is on the order of 200 mm and the difference between the major diameter and the minor diameter is between 1 mm and 2 mm.

14. The propeller ring according to claim 10 , wherein the bearing has, in the plane tangential to the propeller ring a substantially circular cross-section.

15. The propeller ring according to claim 10 , wherein the annular body has a polygonal shape.

16. A turbomachine with variable pitch blades, comprising a propeller ring according to claim 10 .

17. The turbomachine according to claim 16 , wherein the propeller is unducted.

18. Propeller ring of a turbomachine with variable pitch blades, the propeller ring comprising an annular body substantially coaxial with a main axis and a plurality of radial housings uniformly distributed around the main axis, each radial housing being designed to receive a bearing for a root of a blade so as to allow variable pitch of the blade, the propeller ring wherein the radial housings have, in a plane tangential to the annular body, a substantially ovoid cross-section, said substantially ovoid cross-section having a minor diameter and a major diameter with distinct dimensions, wherein the section of the radial housings is elliptical.

19. The propeller ring of claim 18 , wherein the major diameter is greater than the minor diameter and wherein one of the major diameter and the minor diameter extends substantially parallel to the main axis of the propeller ring.

20. The propeller ring according to claim 19 , wherein the major diameter extends substantially parallel to the main axis of the propeller ring, the bearing comprising an outer bearing ring and a difference between the major diameter and the minor diameter of the substantially ovoid cross-section is comprises between 0.5 and 1% of a diameter of the outer bearing ring.

21. A turbomachine with variable pitch blades, comprising a propeller ring according to claim 18 .

Assignees

• Safran Aircraft Engines

Inventors

• Tajan Sebastien Emile Philippe
• Derrez Charles-Henri Michel Marie
• Lafitte Anthony
• Le Pecheur Cyril Roger Yves

Classifications

• B64D2027/005

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

• B64C11/48

  Units of two or more coaxial propellers · CPC title

• B64C11/06 Primary

  for variable-pitch blades · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• Y02T50/66

  Cross-Sectional Technologies · mapped topic