PROPELLER BLADE ROOT COUPLING

• US 20190309639A1
• Filed: 03/25/2019
• Published: 10/10/2019
• Est. Priority Date: 04/10/2018
• Status: Active Grant

• Current Assignee: Ratier Figeac (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Ratier Figeac (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: FAGES, Christian
• Granted Patent: US 10,968,757 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 11/04 Blade mountings
• CPC Class Codes: B64C 11/16 Blades
• CPC Class Codes: B64C 27/48 Root attachment to rotor head
• CPC Class Codes: F01D 5/3023 of radial insertion type, e.g. in individual recesses
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A method of mounting a metal blade root to a composite propeller blade body includes inserting a connection portion of the blade body into a bore formed in the blade root, wherein the connection portion comprises at least one depression formed in an outer surface thereof, and applying pressure to the outer surface of the blade root to cause it to deform and engage with the depressions, thereby mechanically coupling the blade root to the propeller blade body.

Claims

1. A method of mounting an airfoil component body to a blade root, comprising:

providing an airfoil component body having a connection portion, the connection portion comprising an elongate member with at least one depression formed on an outer surface thereof;

inserting the connection portion into a bore formed in a metal blade root; and

deforming the blade root such that a portion of the inner surface of the bore engages with at least one of the depressions in the connection portion to mechanically couple the blade root to the airfoil component body.

2. A method according to claim 1, wherein the at least one depression comprises a groove.

3. A method according to claim 1, wherein the bore and the connection portion each have a non-circular cross-sectional shape.

4. A method according to claim 1, wherein the airfoil component is formed from a fibre-reinforced polymer material.

5. A method according to claim 4, wherein a plurality of fibres extend continuously from a body portion of the airfoil component body into the connection portion.

6. A method according to claim 1, further comprising:

applying an adhesive to at least one of an outer surface of the connection portion and an inner surface of the bore before deforming the blade root, and curing the adhesive after deforming the blade root.

7. A method according to claim 1, further comprising:

fitting one or more brace members within a bore of the connection portion prior to deforming the blade root.

8. A method according to claim 1, wherein the blade root is deformed by a magnetic-pulse system.

9. A method according to claim 1, wherein the airfoil component body comprises a propeller blade body or a spar body for a propeller blade.

10. An airfoil component comprising:

an airfoil component body defining a connection portion with at least one depression formed on an outer surface thereof; and

a metal blade root defining a bore;

wherein;

the connection portion is received within the bore; and

an outer surface of the blade root is deformed such that a portion of the inner surface of the bore engages with at least one of the depressions in the connection portion to mechanically couple the blade root to the airfoil component body.

11. An airfoil component according to claim 10, wherein the at least one depression comprises a groove.

12. An airfoil component according to claim 10, wherein the bore and the connection portion each have a non-circular cross-sectional shape.

13. An airfoil component according to claim 10, wherein:

the airfoil component body is formed from a fibre-reinforced polymer material; and

a plurality of the reinforcement fibres extend continuously through both the connection portion and a body portion of the airfoil component body.

14. An airfoil component according to claim 10, further comprising:

an adhesive bonding an outer surface of the connection portion to an inner surface of the bore.

15. A propeller comprising a propeller hub and at least two propeller blades, wherein each of the propeller blades is an airfoil component according to claim 10.