Turbine engine blade with leading edge strip
A blade for the fan section of a turbine engine comprising a composite core defining a pressure side and a suction side extending axially between a core leading edge and a core trailing edge defining a chord-wise direction and extending radially between a core root and a core tip defining a span-wise direction and a leading edge strip made of materials with different elasticity and mounted to the core leading edge.
1. A leading edge strip for a blade comprising:
a u-shape having a solid nose region and at least one sidewall, the at least one sidewall extending radially from a root portion along a radial length of the blade defining a span-wise direction and extending axially from the solid nose region along a width of the blade defining a chord-wise direction less than the radial length;
a first portion made from a first material and extending radially from the root portion, and a second portion, made from a second material different than the first material and extending radially from the first portion, and having a modulus of elasticity less than the first material;
wherein the leading edge strip is mounted to an exterior portion of the blade.
2. The leading edge strip of claim 1 wherein a third portion made from a third material extends from the second portion in the span-wise direction to define at least a portion of a blade tip.
3. The leading edge strip of claim 2 wherein the third material has a different modulus of elasticity than the second material and the second material extends between the first material and the third material to define a fuse.
4. The leading edge strip of claim 1 wherein the second portion extends from the first portion in the span-wise direction to define at least a portion of a tip.
5. The leading edge strip of claim 1 wherein the second portion defines a strip width extending from the solid nose region in the chord-wise direction that is at least a same width as the first portion.
6. The leading edge strip of claim 1 wherein the second portion defines a strip width extending from the solid nose region in the chord-wise direction that is greater than the first portion.
7. The leading edge strip of claim 1 wherein where the first portion meets the second portion defines a fuse.
8. The leading edge strip of claim 7 wherein the fuse is a butt joint or a lap joint.
9. A blade for a turbine engine, the blade extending axially between a blade leading edge and a blade trailing edge defining a chord-wise direction and having an axial width, and extending radially between a blade root and a blade tip defining a span-wise direction, the blade comprising:
a composite core extending radially between a core root proximate the blade root and a core tip proximate the blade tip and extending axially between a core leading edge and a core trailing edge; and
a leading edge strip mounted to the core leading edge to define at least a portion of the blade leading edge, the leading edge strip having a first portion made from a first material joining a second portion made from a second material to form an interface where an area surrounding the interface defines at least a portion of a frangible zone of the blade.
10. The blade of claim 9 wherein the first material has a different modulus of elasticity than the second portion.
11. The blade of claim 9 wherein a third portion made from a third material extends from the second portion in the span-wise direction to define at least a portion of the blade tip.
12. The blade of claim 11 wherein the third material has a different modulus of elasticity than the second material and the second material extends between the first material and the third material to define a fuse.
13. The blade of claim 9 wherein the second portion defines at least a portion of the blade tip.
14. The blade of claim 13 wherein the second portion defines a strip width extending from the blade leading edge in the chord-wise direction that is at least 5% of the axial width.
15. The blade of claim 13 wherein the second portion defines a strip width extending from the blade leading edge in the chord-wise direction that is greater than 50% of the axial width.
16. The blade of claim 9 further comprising a trailing edge strip mounted to at least a portion of the core trailing edge.
17. The blade of claim 9 further comprising a blade tip cap mounted to at least a portion of the core tip.
18. The blade of claim 9 wherein where the first portion meets the second portion defines a fuse.
19. A method for forming a blade having a frangible zone, the method comprising:
forming a composite core extending axially between a core leading edge and a core trailing edge defining a chord-wise direction and extending radially between a core root and a core tip defining a span-wise direction;
forming a leading edge strip having a first portion made from a first material and a second portion made from a second material having a lower modulus of elasticity than the first material;
mounting the leading edge strip to the composite core; and
forming a fuse between the first and second portions to define at least a portion of the frangible zone.
20. The method of claim 19 further comprising forming a third portion of the leading edge strip from a third material extending from the second portion.
21. The method of claim 19 further comprising extending the second portion in the chord-wise direction to encase more than 50% of the core tip.
22. The method of claim 19 further comprising overlapping the first portion with the second portion.
23. The method of claim 19 wherein the mounting occurs prior to the forming of a fuse.
24. The method of claim 19 wherein the forming of a fuse occurs prior to the mounting of the leading edge strip.