Turbine engine airfoil with a woven core
A gas turbine engine includes a fan section, a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. Sets of blades can be rotatably driven about the longitudinal axis in the fan section, the compressor section, and the turbine section. The airfoil structure defining one or more of the blades or vanes can include a structure which includes a woven or foam core, with a laminate skin, and an exterior coating.
1. A turbine engine comprising:
a fan section, a compressor section, a combustor section, and a turbine section in serial flow arrangement, and defining an engine centerline; and
an airfoil, provided in one of the fan section, the compressor section, or the turbine section, the airfoil including an outer wall having a pressure side and a suction side, and the airfoil rotatable about the engine centerline, the airfoil comprising:
a woven core having a first stiffness,
a laminate skin, having a second stiffness and located exteriorly of the woven core,
a first coating, having a third stiffness and located exteriorly of the laminate skin,
wherein the second stiffness is between the first stiffness and the third stiffness, providing a stiffness transition from the first stiffness to the third stiffness,
a second coating located exteriorly of the first coating, and
an adhesive layer provided between the first coating and the second coating.
2. The turbine engine of claim 1 wherein the woven core includes a three-dimensional weave pattern.
3. The turbine engine of claim 2 wherein the three-dimensional weave pattern includes a braided pattern.
4. The turbine engine of claim 1 wherein the first coating is an environmental barrier coating.
5. The turbine engine of claim 1 wherein the first coating partially covers the laminate skin.
6. The turbine engine of claim 1 further comprising a second adhesive layer located between the laminate skin and the first coating.
7. The turbine engine of claim 1 further comprising a woven layer located between the laminate skin and the first coating.
8. The turbine engine of claim 7 wherein the woven layer includes a braided pattern.
9. The turbine engine of claim 7 wherein the woven layer includes a different weave pattern than that of the woven core.
10. The turbine engine of claim 1 further comprising a foam core located within the woven core.
11. The turbine engine of claim 1 wherein the second coating includes a fourth stiffness, and wherein a fifth stiffness for the adhesive layer is between the third stiffness and the fourth stiffness.
12. The turbine engine of claim 1 , wherein the second coating is an ultraviolet radiation layer.
13. An airfoil having an outer wall defining an interior, the airfoil comprising:
a three-dimensional woven core having a first stiffness; and
a laminate skin having a second stiffness and located exteriorly of the three-dimensional woven core;
a first coating having a third stiffness and located exteriorly of the laminate skin;
a second coating having a fifth stiffness and located exteriorly of the first coating; and
an adhesive layer having a fourth stiffness and provided between the first coating and the second coating;
wherein the second stiffness of the laminate skin is between the first stiffness of the three-dimensional woven core and the third stiffness of the first coating; and
wherein the fourth stiffness of the adhesive layer is between the third stiffness of the first coating and the fifth stiffness of the second coating.
14. The airfoil of claim 13 further comprising a three-dimensional woven layer located exteriorly of the laminate skin, and wherein the three-dimensional woven layer includes an elasticity that is greater than an elasticity for the laminate skin.
15. The airfoil of claim 14 wherein the three-dimensional woven core includes a weave pattern that is different than another weave pattern defining the three-dimensional woven layer.
16. The airfoil of claim 13 further comprising a foam inner core located within the three-dimensional woven core.
17. A turbine engine comprising:
a fan section, a compressor section, a combustor section, and a turbine section in serial flow arrangement, and defining an engine longitudinal axis; and
an airfoil rotatable about the engine longitudinal axis, the airfoil comprising:
a woven core;
a laminate skin at least partially covering the woven core;
at least two coatings located exteriorly of the laminate skin including at least a first coating having a first stiffness and a second coating having a second stiffness; and
an adhesive layer provided between the first coating and the second coating;
wherein a third stiffness for the adhesive layer is between the first stiffness for the first coating and the second stiffness for the second coating.
18. The turbine engine of claim 17 further comprising a woven layer located exteriorly of the laminate skin.