Within gas turbine engines 10 it is necessary to provide fixed vanes which comprise an aerofoil in the gas flow through the gas turbine engine 10. These vanes are subject to significant stressing. Therefore it is generally necessary to secure the vane at one end 103 through an appropriate bond such as brazing whilst at another end a friction damping response is achieved. By providing an anti-bonding layer it is possible to prevent a mechanical bond being formed at the friction damping end 105. Furthermore, a tight fit can be emphasised by residual bonding material remaining after an attempted bonding process upon the anti-bonding layer.
Description
BRIEF DESCRIPTION OF THE DRAWINGS
The invention will be described with reference to the following drawings, wherein:
FIG. 1 illustrates a three shaft engine; and
FIG. 2 illustrates a schematic illustration of a vane arrangement in accordance with the invention.
Claims
1. A vane arrangement for a gas turbine engine, the arrangement comprises a vane confined at an end by a platform with an anti bonding layer between the end of the vane and the platform to prevent a bond forming between them.
2. An arrangement as claimed in claim 1 wherein the vane is secured by a bond at a bond end of the vane to a further platform.
3. An arrangement as claimed in claim 2 wherein the bond is a braze between the bond end of the vane and the further platform.
4. An arrangement as claimed in claim 1 where the anti bonding layer is an anti brazing compound.
5. An arrangement as claimed in claim 1 wherein the end is located in a slot or aperture in the platform.
6. An arrangement as claimed in claim 1 wherein the anti bonding layer is applied to the platform against which the vane is confined.
7. An arrangement as claimed in claim 1 wherein the end is located in a slot or aperture in the platform.
8. An arrangement as claimed in claim 1 wherein the vane is further confined by residual bonding compound upon the anti bonding layer between the end and the platform.
9. An arrangement as claimed in claim 1 wherein the end and the platform form a friction damping combination.
10. A method of forming a vane arrangement for a gas turbine engine, the method comprising:—
a) Presenting an end of a vane to a platform with an anti bonding layer between them; and,b) Retaining the end in a confined association with the platform whilst the anti bonding layer prevents a bond forming between the end and the platform.
11. A method as claimed in claim 10 wherein retaining of the end is achieved by bonding the other end of the vane to a further platform with the vane confined between the platform and the further platform.
12. A method as claimed in claim 11 wherein the bonding is by a brazing process.
13. A method as claimed in claim 10 wherein the anti bonding layer is applied to the end of the vane.
14. A method as claimed in claim 10 wherein the anti bonding layer is applied to the platform.
15. A method as claimed in claim 10 wherein a slot is formed in the platform to receive the end.
16. A method as claimed in claim 10 wherein the vane is further confined by residual bonding compound remaining after attempting to bond a bonding compound with the anti bonding layer.
17. A vane assembly comprising a plurality of vane arrangements as claimed in claim 1.
18. A gas turbine engine incorporating a vane assembly as claimed in claim 17.
Patent Application
20070140854
