Method of making an aerofoil cladding body

Patent metadata

Field	Value
Publication number	US-9956653-B2
Application number	US-201514592518-A
Country	US
Kind code	B2
Filing date	Jan 8, 2015
Priority date	Jan 20, 2014
Publication date	May 1, 2018
Grant date	May 1, 2018

Abstract

A method of manufacture of a cladding body for an edge of an aerofoil, the method including the step of providing a core member shaped to include an elongate recess portion for mounting on the edge of the aerofoil, the elongate recess portion being shaped across its width to define a smoothly curved concave surface. A support member is provided; the support member has a support portion for complementary engagement with the recess portion. Both the support member and the core member are arranged between a pair of opposing membranes. The core member is bonded to each of the pair of membranes to form an intermediate cladding body, wherein the recess portion of the core member is arranged to engage, at least during the bonding step, the support portion to be supported thereby. At least the membranes are shaped using a hot forming process.

First claim

The invention claimed is:

1. A method of manufacture of a cladding body for a leading edge of an aerofoil, the method including steps of:
providing a core member including an elongate recess, the elongate recess having a complementary shape that substantially mirrors a shape of the leading edge of the aerofoil and being configured to engage the leading edge of the aerofoil, the elongate recess extending along a width of the core member to define a smoothly curved concave surface of the core member;
engaging a support portion of a support member into the elongate recess of the core member forming complementary engagement with the elongate recess;
arranging both the support member and the core member between a pair of opposing membranes;
bonding the core member to each of the pair of membranes to form an intermediate cladding body, the elongate recess of the core member engaging and being supported by, at least during the bonding step, the support portion of the support member; and
shaping at least the pair of membranes using a hot forming process.

2. The method according to claim 1 , wherein the bonding step is performed before the shaping step.

3. The method according to claim 1 , wherein the bonding step includes a diffusion bonding process.

4. The method according to claim 1 , wherein the bonding step includes heating at least a portion of the core body and at least a portion of each membrane of the pair of membranes to above 750 degrees Celsius.

5. The method according to claim 1 , wherein the hot forming process includes:
arranging the intermediate cladding body in a cavity mould; and
inflating the intermediate cladding body to deform at least the pair of membranes to conform to constraints of the cavity mould.

6. The method according to claim 1 , wherein the hot forming process is a creep forming process or a superplastic forming process.

7. The method according to claim 1 , wherein the core member and the support member are arranged to be laterally adjacent to one another between the pair of membranes.

8. The method according to claim 1 , wherein a surface of the support member is configured to prevent bonding of the support member with the core member and with each of the pair of membranes during the bonding step.

9. The method according claim 1 , wherein:
a surface of the support member is provided with a coating that prevents bonding of the support member to the core member and to each of the pair of membranes during the bonding step; and
the method includes a step of coating the support member with the coating.

10. The method according to claim 1 , further comprising, after the steps of bonding and shaping, removing a portion of the intermediate cladding body to allow the support member to be removed.

11. The method according to claim 1 , further comprising:
providing a second core member shaped to include a second elongate recess for mounting on the, or another, leading edge of the, or another, aerofoil, the second elongate recess having a same shape as the shape of the elongate recess;
providing a second support member having a second support portion for complementary engagement with the second elongate recess;
arranging the support members and the core members between the pair of opposing membranes;
bonding each core member to each of the pair of membranes to form the intermediate cladding body, the respective elongate recess of each core member engaging and being supported by, at least during the bonding step, a respective support portion of the support members; and
shaping at least the pair of membranes using the hot forming process.

12. The method according to claim 11 , wherein the support member and the second support member are provided as an integral support body providing the respective support portions.

13. The method according to claim 12 , wherein the respective support portions are located on opposing faces of the integral support body.

14. The method according to claim 1 , wherein the aerofoil is a blade of a gas turbine engine.

15. A process of assembling a reinforced blade for a gas turbine engine, the process including:
the method according to claim 14 ; and
a step of mounting the resulting cladding body on to the blade.

16. A process of assembling a gas turbine engine, the process including:
the method according to claim 1 ; and
a step of incorporating the cladding body into the gas turbine engine.

17. A process of assembling a gas turbine engine, the process including:
the process of claim 15 ; and
a step of incorporating the reinforced blade of the gas turbine engine having the cladding body mounted thereon into the gas turbine engine.

Assignees

• Rolls Royce Plc

Inventors

• Wilson Craig
• Davey Michael John
• Cowherd David
• Wilkinson Stephen John

Classifications

• B23K2101/001

  Turbines · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• Y10T29/49337

  Composite blade · CPC title

• F01D5/288

  Protective coatings for blades · CPC title