Multi-material vane for a gas turbine engine
A multi-material vane includes an airfoil extending longitudinally between a leading edge and a trailing edge. The airfoil extends spanwise between an inner end and an outer end. The airfoil extends laterally between a first side and a second side. The airfoil includes a base section, a first side section, a second side section and a sheath. The base section extends along the span line between the inner end and the outer end. The base section is laterally between the first side section and the second side section. The first side section is connected to the base section and partially forms the first side of the airfoil. The second side section is connected to the base section and partially forms the second side of the airfoil. The sheath at least partially forming an edge of the airfoil. The edge is the leading edge or the trailing edge of the airfoil.
1. A vane for a gas turbine engine, comprising:
an airfoil extending longitudinally between a first edge and a second edge, the airfoil extending spanwise between an inner end and an outer end, the airfoil extending laterally between a first side and a second side, and the airfoil including a base section, a first side section, a second side section and a sheath;
the base section laterally between the first side section and the second side section, and the base section comprising a metal material;
the first side section connected to the base section and partially forming the first side of the airfoil, and the first side section comprising a first non-metal material;
the second side section connected to the base section and partially forming the second side of the airfoil, and the second side section comprising a second non-metal material;
the sheath partially forming an exterior surface of the airfoil and attached to the base section;
the base section including a first section and a second section extending spanwise to the first section;
the first section partially forming the first side and the second side, and the first section abutted spanwise against an end of the first side section and an end of the second side section;
the second section spanwise and longitudinally covered by the first side section and the second side section, the second section including a first portion and a second portion;
the first portion extending spanwise from the first section to the second portion, and the first portion having a first portion lateral thickness that is greater than a second portion lateral thickness of the second portion and that is less than a first section lateral thickness of the first section; and
the base section configured with a stepped transition at a spanwise intersection between the first portion and the first section.
2. The vane of claim 1 , wherein both the first side section and the second side section
overlap the first portion and the second portion; and
are connected to the first portion and the second portion.
3. The vane of claim 1 , wherein the base section laterally tapers as the first portion extends along a span line between the inner end and the outer end to the second portion.
4. The vane of claim 1 , wherein the first portion and the second portion are laterally spaced from the first side and the second side at a spanwise intersection between the first portion and the second portion.
5. A gas turbine engine, comprising:
a fan section, a compressor section, a combustor section and a turbine section;
an inner structure housing the compressor section, the combustor section and the turbine section;
an outer structure housing the fan section; and
a structural exit guide vane extending between and structurally tied to the inner structure and the outer structure, the structural exit guide vane configured to transfer loads between the inner structure and the outer structure, the structural exit guide vane comprising the vane of claim 1 .
6. The vane of claim 1 , wherein
the sheath at least partially forms an edge of the airfoil; and
the edge of the airfoil comprises one of the first edge or the second edge.
7. The vane of claim 6 , wherein the sheath completely forms the edge of the airfoil.
8. The vane of claim 6 , wherein the edge of the airfoil comprises a leading edge of the airfoil.
9. The vane of claim 6 , wherein the edge of the airfoil comprises a trailing edge of the airfoil.
10. The vane of claim 1 , wherein
the sheath at least partially forms the first edge; and
the airfoil further includes a second sheath at least partially forming the second edge.
11. The vane of claim 1 , wherein the sheath is bonded to the base section, the first side section and the second side section.
12. The vane of claim 1 , wherein
the airfoil has a span length extending spanwise along a span line between the inner end and the outer end; and
an end-to-end length of the first side section along the span line is less than the span length.
13. The vane of claim 1 , wherein
the airfoil includes an inner end portion at the inner end, an outer end portion at the outer end and an intermediate portion extending spanwise between the inner end portion and the outer end portion;
at least the base section, the first side section, the second side section and the sheath collectively form the intermediate portion; and
at least the base section and the sheath collectively form at least one of the inner end portion or the outer end portion.
14. The vane of claim 13 , wherein neither the first side section nor the second side section forms at least one of the inner end portion or the outer end portion.
15. The vane of claim 1 , wherein the base section extends longitudinally through a channel which is laterally between the first side section and the second side section.
16. The vane of claim 1 , further comprising:
a platform;
the base section extending spanwise to and formed integral with the platform.
17. The vane of claim 1 , wherein the base section is configured as an aperture free body at least between the first side section and the second side section.
18. The vane of claim 1 , wherein at least one of the first non-metal material or the second non-metal material comprises a fiber-reinforced composite material.
19. The vane of claim 1 , wherein the vane is configured as a structural guide vane of the gas turbine engine.
20. A vane for a gas turbine engine, comprising:
an airfoil extending longitudinally between a first edge and a second edge, the airfoil extending spanwise between an inner end and an outer end, the airfoil extending laterally between a first side and a second side, and the airfoil including a base section, a first side section and a second side section;
the base section laterally between the first side section and the second side section, and the base section comprising a metal;
the first side section connected to the base section and partially forming the first side of the airfoil, and the first side section comprising a first non-metal;
the second side section connected to the base section and partially forming the second side of the airfoil, and the second side section comprising a second non-metal;
the base section including a first section and a second section extending spanwise to the first section;
the first section partially forming the first side and the second side, and the first section abutted spanwise against an end of the first side section and an end of the second side section;
the second section spanwise and longitudinally covered by the first side section and the second side section, and the second section including a first portion and a second portion;
the first portion extending spanwise from the first section to the second portion, and the first portion having a first portion lateral thickness that is greater than a second portion lateral thickness of the second portion and that is less than a first section lateral thickness of the first section; and
the base section configured with a stepped transition at a spanwise intersection between the first portion and the first section.