Blade arrangement of a jet engine or an aircraft propeller

Patent metadata

Field	Value
Publication number	US-10012105-B2
Application number	US-201514969769-A
Country	US
Kind code	B2
Filing date	Dec 15, 2015
Priority date	Dec 17, 2014
Publication date	Jul 3, 2018
Grant date	Jul 3, 2018

Abstract

A blade arrangement of a jet engine or an aircraft propeller including a blade with a root portion and an aerofoil portion, wherein the aerofoil portion includes a suction side and a pressure side. The blade arrangement further includes a retention structure that is configured to radially retain the blade in case of a structural blade failure, wherein the retention structure is secured to the root portion and/or to a structure adjacent to the root portion and extends in the radial direction along the suction side and along the pressure side of the aerofoil portion. The retention structure forms a loop that runs at least around the root portion, along the suction side and along the pressure side of the blade.

First claim

The invention claimed is:

1. A blade arrangement of a jet engine or an aircraft propeller, comprising:
a blade with a root portion and an airfoil portion, wherein the airfoil portion comprises a suction side, a pressure side and a blade tip,
a retention structure for radially retaining the blade in case of a structural blade failure, wherein the retention structure:
is secured to at least one chosen from the root portion and a structure adjacent to the root portion and extends in a radial direction along the suction side and along the pressure side of the airfoil portion,
forms a loop that runs at least around the root portion, along the suction side and along the pressure side of the blade, and
includes a textile band or ribbon that forms a full loop which runs around the root portion, along the suction side, along the pressure side and around the blade tip, wherein the band or ribbon runs around the blade tip by looping over the blade tip or by running through an opening formed in the blade tip.

2. The blade arrangement of claim 1 , wherein the band or ribbon is attached to the root portion with a fastening device.

3. The blade arrangement of claim 1 , wherein the band or ribbon is tapered towards the blade tip.

4. The blade arrangement of claim 1 , wherein the band or ribbon is made out of a material that is lower in weight than a material out of which the airfoil portion is made.

5. The blade arrangement of claim 1 , wherein the airfoil portion comprises on both the suction side and the pressure side at least one groove or indentation, wherein the band or ribbon is arranged in the at least one groove or indentation.

6. The blade arrangement of claim 5 , wherein the retention structure is formed integrally with the blade.

7. The blade arrangement of claim 5 , wherein the band or ribbon is pretensioned in the radial direction.

8. The blade arrangement of claim 1 , wherein the blade is a jet engine fan blade or a jet engine propeller blade.

9. A jet engine comprising the blade arrangement of claim 1 .

10. The blade arrangement of claim 1 , wherein a thickness of the band or ribbon decreases towards the blade tip.

11. The blade arrangement of claim 5 , and further comprising an adhesive joining the band or ribbon to the at least one groove or indentation.

12. The blade arrangement of claim 11 , wherein a final shape of the blade includes a smooth aerodynamic external profile achieved by the band or ribbon being joined to the at least one groove or indentation with the adhesive.

13. The blade arrangement of claim 11 , wherein the band or ribbon is tapered towards the blade tip.

14. The blade arrangement of claim 13 , wherein the band or ribbon is made out of a material that is lower in weight than the material out of which the airfoil portion is made.

15. The blade arrangement of claim 11 , wherein the band or ribbon is made out of a material that is lower in weight than the material out of which the airfoil portion is made.

16. The blade arrangement of claim 14 , wherein the retention structure is formed integrally with the blade.

17. The blade arrangement of claim 16 , wherein the band or ribbon is pretensioned in the radial direction.

18. The blade arrangement of claim 1 , wherein the retention structure is formed integrally with the blade.

19. The blade arrangement of claim 1 , wherein the band or ribbon is pretensioned in the radial direction.

20. The blade arrangement of claim 5 , wherein a thickness of the band or ribbon decreases towards the blade tip.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Webb Simon Paul

Classifications

• F05D2300/6012

  Woven fabrics · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F01D21/045 Primary

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• B64C11/26

  Fabricated blades · CPC title