An airfoil for use in a rotor assembly is disclosed, the airfoil having a tip-cutter located on a sidewall near a tip portion, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-grinder located on the tip por
An airfoil for use in a rotor assembly is disclosed, the airfoil having a tip-cutter located on a sidewall near a tip portion, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-grinder located on the tip portion, wherein the tip-grinder capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-rake that facilitates reducing loading induced to said airfoil during tip rubs.
대표청구항▼
1. An airfoil comprising: a first sidewall;a second sidewall coupled to the first sidewall at a leading edge and at a trailing edge;a tip portion extending between the first and second sidewalls and defining an airfoil tip of the airfoil; anda tip-cutter located on the first sidewall at the leading
1. An airfoil comprising: a first sidewall;a second sidewall coupled to the first sidewall at a leading edge and at a trailing edge;a tip portion extending between the first and second sidewalls and defining an airfoil tip of the airfoil; anda tip-cutter located on the first sidewall at the leading edge and near the tip portion, the tip-cutter defining a tip-cutter profile comprising an arcuate portion on the leading edge and a flat portion on the leading edge between the arcuate portion and the tip portion of the airfoil, the arcuate portion defining a recess in the leading edge that extends in the chord-wise direction toward the trailing edge of the airfoil, the flat portion defining a cutter-angle with the leading edge that extends in the chord-wise direction toward the trailing edge of the airfoil, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. 2. An airfoil according to claim 1 wherein the arcuate and flat portions are contiguous with each other. 3. An airfoil according to claim 2 wherein the recess of the arcuate portion extends into the airfoil to a depth of up to 0.050 inch. 4. An airfoil according to claim 1, wherein the cutter-angle has a value between two degrees and five degrees. 5. An airfoil according to claim 1 wherein the cutter-angle gradually reduces to zero toward the trailing edge so as to blend with the first sidewall of the airfoil. 6. An airfoil according to claim 1 wherein the recess gradually reduces to zero toward the trailing edge so as to blend with the first sidewall of the airfoil. 7. An airfoil according to claim 1 further comprising a tip-grinder located on the tip portion, the tip-grinder being capable of removing a portion of an abradable material during a tip rub. 8. An airfoil according to claim 1 further comprising a concave edge and a convex edge that are separated from each other at the tip portion, the tip portion having a tip-rake profile so that the concave edge is closer to the static structure than the convex edge during a tip rub to facilitate reducing loading induced to the airfoil during tip rubs. 9. A rotor assembly comprising: a rotor hub; anda plurality of rotor blades coupled to the rotor hub such that each rotor blade comprises an airfoil portion comprising a first sidewall, a second sidewall coupled to the first sidewall at a leading edge and at a trailing edge, a root portion, a tip portion extending between the first and second sidewalls and defining an airfoil tip of the airfoil; anda tip-cutter located on the first sidewall at the leading edge and near the tip portion, the tip-cutter defining a tip-cutter profile comprising an arcuate portion on the leading edge and a flat portion on the leading edge between the arcuate portion and the tip portion of the airfoil, the arcuate portion defining a recess in the leading edge that extends in the chord-wise direction toward the trailing edge of the airfoil, the flat portion defining a cutter-angle with the leading edge that extends in the chord-wise direction toward the trailing edge of the airfoil, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. 10. A rotor assembly in accordance with claim 9, wherein an abradable casing extends circumferentially about the rotor assembly, and the tip-cutter profile facilitates reducing loading induced to the airfoil during a tip rub. 11. A blade assembly comprising: an airfoil having a leading edge, a trailing edge, and an airfoil tip extending therebetween; anda metal leading edge (MLE) coupled to at least a portion of the leading edge, the MLE having a tip-cutter capable of removing a portion of an abradable material during a tip rub, the tip-cutter defining a tip-cutter profile comprising an arcuate portion in the MLE and a flat portion on the MLE between the arcuate portion and the airfoil tip, the arcuate portion defining a recess in the MLE that extends in a chord-wise direction of the airfoil toward the trailing edge of the airfoil, the flat portion defining a cutter-angle with the MLE that extends in the chord-wise direction toward the trailing edge of the airfoil, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. 12. A blade assembly according to claim 11 further comprising a tip-grinder located on the airfoil tip, the tip-grinder being capable of removing a portion of an abradable material during a tip rub. 13. A blade assembly according to claim 11 wherein the airfoil tip has a tip-rake profile that facilitates reducing loading induced in the blade assembly during a tip rub. 14. A blisk comprising a plurality of airfoils extending from a hub, each airfoil comprising a first sidewall, a second sidewall coupled to the first sidewall at a leading edge and at a trailing edge, a root portion, a tip portion extending between the first and second sidewalls and a tip-cutter located on the first sidewall at the leading edge of at least one airfoil near the tip portion thereof, the tip-cutter defining a tip-cutter profile comprising an arcuate portion on the leading edge and a flat portion on the leading edge between the arcuate portion and the tip portion of the airfoil, the arcuate portion defining a recess in the leading edge that extends in the chord-wise direction toward the trailing edge of the airfoil, the flat portion defining a cutter-angle with the leading edge that extends in the chord-wise direction toward the trailing edge of the airfoil, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub.
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이 특허에 인용된 특허 (18)
Langenbrunner Leslie L. (Cincinnati OH) Proffitt Paul F. (Cincinnati OH), Abradable shroud assembly for turbomachinery.
Benoit Roland (Lake Park FL) Beverly Eugene M. (Palm Beach Gardens FL) Love Charles M. (Jupiter FL) Mack Gregory J. (Palm Beach Gardens FL), Abrasive blade tip.
Schaefer Robert P. (East Hartford CT) Rutz David A. (Glastonbury CT) Lee Edward (Higganum CT) Johnson Edward J. (Middletown CT), Abrasive material, especially for turbine blade tips.
Freling Melvin (West Hartford CT) Gruver Gary A. (South Windsor CT) Parkos ; Jr. Joseph J. (East Haddam CT) Welch Douglas A. (Portland CT), Method and apparatus for reducing stress on the tips of turbine or compressor blades.
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