Vane assembly
A vane assembly includes an aerofoil having a leading edge, a trailing edge, and a pressure surface and a suction surface defined between the leading edge and the trailing edge. The aerofoil includes a blade member forming the trailing edge, at least a portion of the pressure surface and at least a portion of the suction surface. The blade member is formed of a first material. The aerofoil further includes a spar at least partly enclosed by the blade member and forming at least a portion of the leading edge. The spar further forms at least one cooling channel and supports at least a portion of an interior surface of the blade member. The spar is formed of a second material different from the first material. The second material has a greater impact resistance than the first material.
1. A vane assembly comprising:
an aerofoil having a leading edge, a trailing edge, and a pressure surface
and a suction surface defined between the leading edge and the trailing edge, the aerofoil comprising:
a blade member forming the trailing edge, at least a portion of the pressure surface and at least a portion of the suction surface, wherein the blade member is formed of a first material; and
a spar at least partly enclosed by the blade member and forming at least a portion of the leading edge and at least partially exposed to a hot gas path, the spar further forming at least one cooling channel and supporting at least a portion of an interior surface of the blade member, wherein the spar is formed of a second material different from the first material;
wherein the second material has a greater impact resistance than the first material; and
wherein the first material comprises a ceramic matrix composite.
2. The vane assembly of claim 1 , wherein the blade member further comprises:
a first section forming at least the portion of the pressure surface; and
a second section forming at least the portion of the suction surface;
wherein the first section and the second section together form the trailing edge; and wherein the spar supports at least a portion of an interior surface of the first section and at least a portion of an interior surface of the second section.
3. The vane assembly as claimed in claim 2 , wherein the spar and the first section together form the leading edge.
4. The vane assembly as claimed in claim 2 , wherein the spar and the first section together form the pressure surface.
5. The vane assembly as claimed in claim 2 , wherein the second section forms entirely the suction surface.
6. The vane assembly as claimed in claim 2 , wherein the first section and the second section are separate parts.
7. The vane assembly as claimed in claim 2 , wherein the first section and the second section are integrally formed.
8. The vane assembly as claimed in claim 2 , further comprising a fastener coupling the spar to at least one of the first section and the second section.
9. The vane assembly as claimed in claim 8 , wherein the fastener is a solid rivet or a hollow rivet.
10. The vane assembly as claimed in claim 1 , further comprising:
a first platform disposed proximate a top end of the aerofoil; and
a second platform disposed proximate a bottom end of the aerofoil;
wherein the spar further comprises at least one first locating feature coupling the spar to the first platform, at least one second locating feature coupling the spar to the second platform and at least one support feature supporting the spar on the second platform.
11. The vane assembly as claimed in claim 1 , wherein the second material comprises a metallic material.
12. The vane assembly as claimed in claim 1 , further comprising at least one inlet for supplying cooling fluid to the at least one cooling channel of the spar.
13. The vane assembly as claimed in claim 1 , wherein the blade member is joined to the spar by at least one of welding, brazing and bi-casting.
14. A gas turbine engine comprising the vane assembly as claimed in claim 1 .