Blade

Patent metadata

Field	Value
Publication number	US-10174625-B2
Application number	US-201514954355-A
Country	US
Kind code	B2
Filing date	Nov 30, 2015
Priority date	Dec 19, 2014
Publication date	Jan 8, 2019
Grant date	Jan 8, 2019

Abstract

A turbomachine blade comprising a metallic leading edge having a region having varying fracture resistance in a spanwise direction so as to increase energy absorption by the leading edge in the event of the blade being released from a turbomachine and impacting a casing of the turbomachine.

First claim

The invention claimed is:

1. A turbomachine blade comprising:
a root and a tip of the turbomachine blade; and
a metallic leading edge having a region with varying fracture resistance in a spanwise direction that increases energy absorption by the metallic leading edge in the event of the turbomachine blade being released from a turbomachine and impacting a casing of the turbomachine, the region of varying fracture resistance of the metallic leading edge including a sequence of bonded regions and non-bonded regions, wherein:
a ratio of bonded area to non-bonded area of the sequence is greater at the tip of the turbomachine blade than at the root of the turbomachine blade, and
the fracture resistance of the metallic leading edge progressively increases from the root of the turbomachine blade to the tip of the turbomachine blade.

2. The turbomachine blade according to claim 1 , wherein the metallic leading edge includes two wings and a fore portion provided between the two wings.

3. The turbomachine blade according to claim 2 , wherein the fore portion is configured to have a different fracture resistance in a region towards the root of the turbomachine than in a region towards the tip of the turbomachine.

4. The turbomachine blade according to claim 2 , wherein the leading edge is formed from two parts, the two parts being connected together in a region of the fore portion.

5. The turbomachine blade according to claim 4 , wherein the two parts are bonded together and a bondline connecting the two parts has a different strength in a region towards the root of the turbomachine than in a region towards the tip of the turbomachine.

6. The turbomachine blade according to claim 5 , wherein the bondline includes the bonded regions and the non-bonded regions.

7. The turbomachine blade according to claim 5 , wherein the two parts are connected together using welding or diffusion bonding.

8. The turbomachine blade according to claim 1 , wherein the fracture resistance in a region towards the root of the turbomachine blade is reduced compared to the fracture resistance towards the tip of the turbomachine blade.

9. The turbomachine blade according to claim 1 , wherein the leading edge is made by additive manufacture.

10. A gas turbine engine comprising a fan having a plurality of turbomachine blades according to claim 1 .

11. A method of manufacturing a blade including:
manufacturing a metallic leading edge, and varying the manufacturing process or including weakening features in the metallic leading edge such that the metallic leading edge is configured to have varying fracture resistance in a spanwise direction, the weakening features increasing energy absorption by the metallic leading edge in the event of the blade being released from a turbomachine and impacting a casing of the turbomachine, the metallic leading edge including a sequence of bonded regions and non-bonded regions, wherein:
a ratio of bonded area to non-bonded area of the sequence is greater at a tip of the blade than at a root of the blade, and
the fracture resistance of the metallic leading edge progressively increases from the root of the blade to the tip of the blade.

12. The method according to claim 11 , wherein the metallic leading edge is made using additive manufacturing.

13. The method according to claim 12 , wherein the metallic leading edge is made in two portions that are connected together.

Assignees

• Rolls Royce Plc

Inventors

• Benson Christopher

Classifications

• F02C7/05

  having provisions for obviating the penetration of damaging objects or particles · 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

• F01D21/045

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

• F01D5/282 Primary

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F05D2220/32

  in gas turbines · CPC title