Part of a turbomachine comprising a washer cooperating with a counterbore

Patent metadata

Field	Value
Publication number	US-11041393-B2
Application number	US-201916433984-A
Country	US
Kind code	B2
Filing date	Jun 6, 2019
Priority date	Jun 8, 2018
Publication date	Jun 22, 2021
Grant date	Jun 22, 2021

Abstract

The invention concerns a part of a turbomachine, including an element having a first aerodynamic surface including a counterbore at the bottom of which is provided a mounting hole of a fastening screw of the part, and a washer configured to be accommodate into the counterbore and intended to serve as a support for a head of the fastening screw, wherein the washer has an asymmetry of revolution about a screwing axis and is engaged by shape complementarity in the counterbore, and in that the washer includes a second aerodynamic surface extending in the continuity of the first surface.

First claim

The invention claimed is:

1. A part of a turbomachine comprising:
an element having a first aerodynamic surface and comprising a counterbore, said counterbore comprising an upper end and a bottom end, said upper end opening on said first aerodynamic surface and said bottom end forming a mounting hole,
a fastening screw having a head and a threaded rod, said head being received into said upper end and said threaded rod passing through said mounting hole, said fastening screw having a screwing axis which extends in a first direction, and
a washer accommodated into said upper end of said counterbore and forming a support for said head of said fastening screw, said washer having a first cross sectional oblong shape in a plane perpendicular to said screwing axis and said upper end of the counterbore having a second cross sectional oblong shape in a plane perpendicular to said screwing axis, said first and second cross sectional oblong shapes being complementary, and said washer having a second aerodynamic surface which is aligned with said first aerodynamic surface, and
wherein said washer is asymmetric about said screwing axis,
said washer forms a strut around the fastening screw separating, along a mounting axis of the fastening screw, a first end on the bottom end of the counterbore and a second end comprising said second aerodynamic surface,
the first and second ends of the washer are interconnected on a first side of the washer,
the first and second ends of the washer are separated from each other on a second side of the washer which is opposite to the first side, and
the first and second sides extend in the first direction.

2. The part according to claim 1 , wherein said first end is along a plane that is inclined with respect to said second aerodynamic surface.

3. The part according claim 1 , wherein said washer comprises a disc or fork configured to be tightened by said head against the bottom end of the counterbore and a cap for sealing the counterbore and to define said second aerodynamic surface.

4. The part according claim 3 , wherein said cap comprises a screwing hole for the fastening screw.

5. The part according to claim 4 , wherein a diameter of said screwing hole is smaller than a diameter of the mounting hole for the fastening screw.

6. The part according to claim 1 , wherein said second end of the strut comprises a supporting frustoconical inner surface for the head of the fastening screw.

7. The part according to claim 1 , wherein said washer is formed of a single part.

8. The part according to claim 1 , wherein said part is a vane which comprises a platform having said first aerodynamic surface.

9. The part according to claim 8 , wherein said part is a stator vane.

10. The part according to claim 1 , wherein the part is one of an air inlet cone, a cowl and a casing.

11. An aircraft turbomachine, comprising the part according to claim 1 .

12. The part according to claim 1 , wherein the mounting hole of said bottom end is eccentric such that the screwing axis of the mounting hole is closer to a first axial end of the washer than to a second opposite axial end of the washer.

13. The part according to claim 1 , wherein the first end is a planar plate of the washer conforming to a shape of the bottom of the counterbore, and the second end of the washer is a second plate that is shaped to correspond to the second aerodynamic surface.

14. The part according to claim 13 , wherein the planar plate forms a fork with a U-shaped notch extending longitudinally from a first axial end of the washer.

15. The part according to claim 14 , wherein the U-shaped notch comprises a bottom having a hole centered to correspond to the mounting hole of said bottom end.

16. The part according to claim 1 , wherein the second oblong shape of said upper end is elongated in a second direction, wherein the second direction is perpendicular to the first direction.

17. The part according to claim 1 , wherein the washer has an axis which is aligned with the screwing axis.

18. A part of a turbomachine comprising:
an element having a first aerodynamic surface and comprising a counterbore, said counterbore comprising an upper end and a bottom end, said upper end opening on said first aerodynamic surface and said bottom end forming a mounting hole,
a fastening screw having a head and a threaded rod, said head being received into said upper end and said threaded rod passing through said mounting hole, said fastening screw having a screwing axis which extends in a first direction, and
a washer accommodated into said upper end of said counterbore and forming a support for said head of said fastening screw, said washer having a first cross sectional oblong shape in a plane perpendicular to said screwing axis and said upper end of the counterbore having a second cross sectional oblong shape in a plane perpendicular to said screwing axis, said first and second cross sectional oblong shapes being complementary, and said washer having a second aerodynamic surface which is aligned with said first aerodynamic surface, and
wherein said washer is asymmetric about said screwing axis,
said washer forms a strut around the fastening screw separating, along a mounting axis of the fastening screw, a first end on the bottom end of the counterbore and a second end comprising said second aerodynamic surface, and
wherein said second end of the strut comprises a supporting frustoconical inner surface for the head of the fastening screw.

19. An aircraft turbomachine, comprising a part according to claim 18 .

Assignees

• Safran Aircraft Engines

Inventors

• Lagarde Romain Nicolas
• Charbonnier Marie-Charline Stephanie
• Perrollaz Jean-Marc Claude

Classifications

• F01D9/042 Primary

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F16B39/108

  with a locking washer under the nut or bolt head having at least one tongue or lug folded against the nut or bolt head, or against the object itself (F16B39/103 takes precedence) · CPC title