Fan blade made of a textile composite material
A gas-turbine engine fan blade made of a textile composite material includes short carbon fiber intermediate layers ( 8 ) for forming the blade root arranged between splayed carbon fiber layers ( 7 ) in the blade root ( 2 ). In a compressive stress-affected zone ( 11 ) of the blade root, the fiber layers extend parallel to the flanks ( 12 ) of the blade root. The diversion of the carbon fiber layers ( 7 ) up to the splayed area is effected in a transition area ( 13 ). A glass fiber outer layer ( 10 ) arranged on the flanks ( 12 ) of the blade root gradually runs out at a transition zone ( 15 ) of the transition area ( 13 ), this zone being diverted at a certain radius. Between the glass fiber outer layer and the outer carbon fiber layer there is a carbon fiber layer ( 9 ) oriented at +/−45°.
1. A gas-turbine engine fan blade made of a textile composite material, which turbine blade comprises an airfoil and a blade root for retention in a recess of a rotor disk, the turbine blade comprising:
a plurality of carbon fiber layers extending parallel to an airfoil axis in the airfoil and also forming:
a quasi unidirectionally reinforced carbon fiber-plastic carrying structure,
an airfoil root tapering in the blade root,
a transition area which extends from a start of the airfoil root on both sides, and in which the carbon fiber layers are diverted from a position parallel to the airfoil axis via an outer, load-adequate transition zone to a position splayed in accordance with a geometry of the blade root, and
a compressive stress-affected zone, in which the previously diverted carbon fiber layers extend parallel to flanks of the blade root positioned in the recess of the rotor disk, with
a plurality of carbon fiber intermediate layers individually arranged between the splayed carbon fiber layers,
a glass fiber outer layer positioned on each flank of the blade root; and
a further carbon fiber layer, haying a fiber orientation of +/−45° to a fiber orientation of the carbon fiber layers of the carrying structure, positioned between the carrying structure and each glass fiber outer layer.
2. The fan blade in accordance with claim 1 , wherein the glass fiber outer layer extends along the flanks of the blade root to the transition area.
3. The fan blade in accordance with claim 2 , wherein the glass fiber outer layer gradually tapers out into the load-adequate transition zone with decreasing layer thickness.
4. The fan blade in accordance with claim 3 , wherein a transition radius of the fiber layers in the transition zone corresponds to a curvature of an ellipse with an ellipse ratio of approximately 3:1.
5. The fan blade in accordance with claim 4 , wherein the transition radius of the fiber layers in the transition zone corresponds to a curvature of an ellipse with an ellipse ratio of 3:1.
6. The fan blade in accordance with claim 5 , wherein the carbon fiber intermediate layers extend with different length and with decreasing layer thickness into the transition area in accordance with the geometry of the compressive stress-affected zone.
7. The fan blade in accordance with claim 6 , wherein a plastic proportion between the fiber layers in the compressive stress-affected zone is lower than in blade areas not subjected to local pressure, because of increased compression in this area during plastic infiltration.
8. The fan blade in accordance with claim 7 , further comprising pointed glass or carbon fiber-plastic pins to reinforce the carbon fiber layers in the transition area in a thickness direction.
9. The fan blade in accordance with claim 1 , wherein the glass fiber outer layer extends along the flanks of the blade root to the transition area.
10. The fan blade in accordance with claim 9 , wherein the glass fiber outer layer gradually tapers out into the load-adequate transition zone with decreasing layer thickness.
11. The fan blade in accordance with claim 10 , wherein a transition radius of the fiber layers in the transition zone corresponds to a curvature of an ellipse with an ellipse ratio of approximately 3:1.
12. The fan blade in accordance with claim 11 , wherein the transition radius of the fiber layers in the transition zone corresponds to a curvature of an ellipse with an ellipse ratio of 3:1.
13. The fan blade in accordance with claim 12 , wherein the carbon fiber intermediate layers extend with different length and with decreasing layer thickness into the transition area in accordance with the geometry of the compressive stress-affected zone.
14. The fan blade in accordance with claim 13 , wherein a plastic proportion between the fiber layers in the compressive stress-affected zone is lower than in blade areas not subjected to local pressure, because of increased compression in this area during plastic infiltration.
15. The fan blade in accordance with claim 1 , wherein the carbon fiber intermediate layers extend with different length and with decreasing layer thickness into the transition area in accordance with the geometry of the compressive stress-affected zone.
16. A gas-turbine engine fan blade made of a textile composite material, which turbine blade comprises an airfoil and a blade root for retention in a recess of a rotor disk, the turbine blade comprising:
a plurality of carbon fiber layers extending parallel to an airfoil axis in the airfoil and also forming:
a quasi unidirectionally reinforced carbon fiber-plastic carrying structure,
an airfoil root tapering in the blade root,
a transition area which extends from a start of the airfoil root on both sides, and in which the carbon fiber layers are diverted from a position parallel to the airfoil axis via an outer, load-adequate transition zone to a position splayed in accordance with a geometry of the blade root, and
a compressive stress-affected zone, in which the previously diverted carbon fiber layers extend parallel to flanks of the blade root positioned in the recess of the rotor disk, with
a plurality of carbon fiber intermediate layers individually arranged between the splayed carbon fiber layers, and
a glass fiber outer layer positioned on each flank of the blade root,
wherein a transition radius of the fiber layers in the transition zone corresponds to a curvature of an ellipse with an ellipse ratio of approximately 3:1.
17. The fan blade in accordance with claim 16 , wherein the transition radius of the fiber layers in the transition zone corresponds to a curvature of an ellipse with an ellipse ratio of 3:1.
18. A gas-turbine engine fan blade made of a textile composite material, which turbine blade comprises an airfoil and a blade root for retention in a recess of a rotor disk, the turbine blade comprising:
a plurality of carbon fiber layers extending parallel to an airfoil axis in the airfoil anc also forming:
a quasi unidirectionally reinforced carbon fiber-plastic carrying structure,
an airfoil root tapering in the blade root,
a transition area which extends from a start of the airfoil root on both sides, and in which the carbon fiber layers are diverted from a position parallel to the airfoil axis via an outer, load-adequate transition zone to a position splayed in accordance with a geometry of the blade root, and
a compressive stress-affected zone, in which the previously diverted carbor fiber layers extend parallel to flanks of the blade root positioned in the recess of the rotor disk, with
a plurality of carbon fiber intermediate layers individually arranged between the splayed carbon fiber layers, and
a glass fiber outer layer positioned on each flank of the blade root,
wherein a plastic proportion between the fiber layers in the compressive stress-affected zone is lower than in blade areas not subjected to local pressure, because of increased compression in this area during plastic infiltration.
19. A gas-turbine engine fan blade made of a textile composite material, which turbine blade comprises an airfoil and a blade root for retention in a recess of a rotor disk, the turbine blade comprising:
a plurality of carbon fiber layers extending parallel to an airfoil axis in the airfoil and also forming:
a quasi unidirectionally reinforced carbon fiber-plastic carrying structure,
an airfoil root tapering in the blade root,
a transition area which extends from a start of the airfoil root on both sides, and in which the carbon fiber layers are diverted from a position parallel to the airfoil axis via an outer, load-adequate transition zone to a position splayed in accordance with a geometry of the blade root, and
a compressive stress-affected zone, in which the previously diverted carbon fiber layers extend parallel to flanks of the blade root positioned in the recess of the rotor disk, with
a plurality of carbon fiber intermediate layers individually arranged between the splayed carbon fiber layers,
a glass fiber outer layer positioned on each flank of the blade root, and
pointed glass or carbon fiber-plastic pins to reinforce the carbon fiber layers in the transition area in a thickness direction.