Gas turbine engine hollow fan blade rib orientation
A fan blade includes first and second portions that are secured to one another and provide a cavity. The first and second portions form an exterior airfoil surface that extends in a radial direction from a root to a tip and in a chord-wise direction from a leading edge to a trailing edge. Radial ribs extend in a radial direction from the root toward the tip and are spaced apart from one another in the chord-wise direction. First and second angled ribs intersect one another at a first apex. The radial ribs intersect at least one of the first and second angled ribs. The first and second angled ribs are at an angle relative to one of the radial ribs. The angle is in a range of 45°+/−30°.
1. A fan blade comprising:
first and second portions secured to one another and providing a cavity, the first and second portions forming an exterior airfoil surface extending in a radial direction from a root to a tip and in a chord-wise direction from a leading edge to a trailing edge, radial ribs extending in a radial direction from the root toward the tip and spaced apart from one another in the chord-wise direction, first and second angled ribs intersecting one another at a first apex, the radial ribs intersecting at least one of the first and second angled ribs, the first and second angled ribs at an angle relative to one of the radial ribs, the angle is in range of 45°+/−15°.
2. The fan blade of claim 1 , wherein the angle is in a range of 45°+/−5°.
3. A fan blade comprising:
first and second portions secured to one another and providing a cavity, the first and second portions forming an exterior airfoil surface extending in a radial direction from a root to a tip and in a chord-wise direction from a leading edge to a trailing edge, radial ribs extending in a radial direction from the root toward the tip and spaced apart from one another in the chord-wise direction, first and second angled ribs intersecting one another at a first apex, the radial ribs intersecting at least one of the first and second angled ribs, the first and second angled ribs at an angle relative to one of the radial ribs, the angle is in range of 45°+/−30°, wherein multiple first and second angled ribs are arranged in a waffle pattern forming multiple polygons each having first and second radial apexes and first and second lateral apexes, the second radial apex nearer the tip than the first radial apex, and the first lateral apex nearer the leading edge than the second lateral apex.
4. The fan blade of claim 3 , wherein the radial ribs are parallel to one another within 15°.
5. The fan blade of claim 4 , wherein the number of radial ribs is at least three.
6. The fan blade of claim 4 , wherein the radial ribs extend to at least a 50% span position.
7. The fan blade of claim 3 , wherein at least one of the radial ribs is joined at one of the first apexes.
8. The fan blade of claim 3 , wherein the waffle pattern is provided in a span region extending from a 50% span position to a 100% span position.
9. The fan blade of claim 3 , wherein the waffle pattern extends to a tip wall at the 100% span position.
10. The fan blade of claim 9 , wherein at least one of the first and second portions provides leading and trailing edge walls that respectively provide the leading and trailing edges, the waffle pattern extends to at least one of the leading and trailing edge walls.
11. The fan blade of claim 3 , wherein at least one of the first and second portions provides leading and trailing edge walls that respectively provide the leading and trailing edges, comprising at least one chord-wise rib that extends from the waffle pattern to one of the leading and trailing edge walls.
12. The fan blade of claim 3 , wherein the first and second portions are one of a titanium alloy or an aluminum alloy.
13. A method of designing a fan blade, comprising:
modeling a fan blade configuration with internal reinforcing ribs;
identifying stresses for various modes of the fan blade configuration;
identifying common stress areas between the various modes; and
varying an orientation of the internal reinforcing ribs in the common stress areas to provide a revised fan blade configuration with increased separation between some of the various modes that generate the stresses compared to the modeled fan blade configuration, wherein multiple first and second angled ribs are arranged in a waffle pattern forming multiple polygons each having first and second radial apexes and first and second lateral apexes, the second radial apex nearer the tip than the first radial apex, and the first lateral apex nearer the leading edge than the second lateral apex.
14. The method of claim 13 , wherein the revised fan blade configuration includes first and second portions secured to one another and providing a cavity, the first and second portions forming an exterior airfoil surface extending in a radial direction from a root to a tip and in a chord-wise direction from a leading edge to a trailing edge, radial ribs extending in a radial direction from the root toward the tip and spaced apart from one another in the chord-wise direction, first and second angled ribs intersecting one another at a first apex, the radial ribs intersecting at least one of the first and second angled ribs, the first and second angled ribs at an angle relative to one of the radial ribs, the angle is in range of 45°+/−30°.
15. The method of claim 14 , wherein the angle is in a range of 45°+/−15°.
16. The method of claim 15 , wherein the angle is in a range of 45°+/−5°.
17. The method of claim 14 , wherein the waffle pattern is provided in a span region extending from a 50% span position to a 100% span position.
18. The method of claim 14 , wherein at least one of the first and second portions provides leading and trailing edge walls that respectively provide the leading and trailing edges, comprising at least one chord-wise rib that extends from the waffle pattern to one of the leading and trailing edge walls.