An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a trailing ed
An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position, and the trailing edge sweep angle is positive from 0% span to at least 95% span. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning.
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1. An airfoil for a turbine engine comprising: an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a curve corresponding to a relationship between a trai
1. An airfoil for a turbine engine comprising: an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position, wherein the trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position, and the trailing edge sweep angle is positive from 0% span to at least 95% span, wherein the airfoil has a relationship between a leading edge dihedral and a span position, the leading edge dihedral negative from the 0% span position to the 100% span position, wherein a positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. 2. The airfoil according to claim 1, wherein the trailing edge sweep angle is in a range of 10° to 20° in a range of 50-70% span position. 3. The airfoil according to claim 2, wherein the trailing edge sweep angle is in a range of 10° to 20° in a range of 60-70% span position. 4. The airfoil according to claim 1, wherein the trailing edge sweep angle is positive from 0%-95% span. 5. The airfoil according to claim 4, wherein the trailing edge sweep angle transitions from less positive to more positive at greater than an 80% span position. 6. The airfoil according to claim 4, wherein a positive-most trailing edge sweep angle is at a greater than 50% span position. 7. The airfoil according to claim 1, wherein a positive-most trailing edge sweep angle is at about a 70% span position. 8. The airfoil according to claim 1, wherein a trailing edge sweep angle is within 5° along a portion of the curve from the 0% span position to a 60% span position. 9. The airfoil according to claim 8, wherein a positive-most trailing edge sweep angle lies along the portion. 10. The airfoil according to claim 1, wherein a positive-most trailing edge sweep angle is within the range of 10° to 20° in the range of 40-70% span position. 11. The airfoil according to claim 1, wherein the airfoil has a leading edge sweep angle curve corresponding to a relationship between a leading edge sweep angle and a span position, wherein a leading edge sweep angle at the 100% span position is less negative than a forward-most leading edge sweep angle along the curve, and wherein the curve has a decreasing leading edge sweep angle rate in a range of a 80-100% span position. 12. The airfoil according to claim 11, wherein the leading edge sweep angle curve has a portion extending span-wise toward the tip and from the forward-most leading edge sweep angle, the portion has a decreasing leading edge sweep angle that crosses a zero sweep angle in the range of a 30-40% span position. 13. The airfoil according to claim 12, wherein the forward-most leading edge sweep angle is in a range of −10° to −15°. 14. The airfoil according to claim 13, wherein the forward-most leading edge sweep angle is about −10°. 15. The airfoil according to claim 13, wherein a rearward-most leading edge sweep angle is in a range of 15° to 30°. 16. The airfoil according to claim 13, wherein a leading edge sweep angle at the 0% span position and a leading edge sweep angle at the 100% span position are within 5° of one another. 17. The airfoil according to claim 13, wherein a leading edge sweep angle at the 0% span position is negative, and a leading edge sweep angle at the 100% span position is positive. 18. The airfoil according to claim 13, wherein a leading edge sweep angle at the 0% span position is positive, and a leading edge sweep angle at the 100% span position is negative. 19. The airfoil according to claim 1, wherein the leading edge dihedral at the 0% span position is in the range of −3° to −12°. 20. The airfoil according to claim 19, wherein the leading edge dihedral at the 0% span position is about −4°. 21. The airfoil according to claim 2, wherein the leading edge dihedral at the 0% span position is about −10°. 22. The airfoil according to claim 19, wherein the leading edge dihedral extends from the 0% span position to a 20% span position having a leading edge dihedral in a range of −2° to −6°. 23. The airfoil according to claim 22, wherein the leading edge dihedral includes a first point at a 75% span position and extends generally linearly from the first point to a second point at the 85% span position. 24. The airfoil according to claim 19, wherein a maximum negative dihedral is in a range of 95-100% span position. 25. The airfoil according to claim 24, wherein a least negative dihedral is in a range of 5-15% span position. 26. The airfoil according to claim 19, wherein a maximum negative dihedral is in a range of 65-75% span position. 27. The airfoil according to claim 26, wherein a least negative dihedral is in a range of 0-10% span position. 28. The airfoil according to claim 19, wherein a maximum negative dihedral is in a range of 50-60% span position. 29. The airfoil according to claim 1, wherein the airfoil is a fan blade for a gas turbine engine. 30. The airfoil according to claim 1, wherein the airfoil has a relationship between a trailing edge dihedral and a span position, the trailing edge dihedral positive from the 0% span position to the 100% span position, wherein a positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning.
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