An airfoil of a turbine engine according to an example of the present disclosure includes, among other things, pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a gap/chord ratio and span position that d
An airfoil of a turbine engine according to an example of the present disclosure includes, among other things, pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope.
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1. An airfoil arrangement of a turbine engine comprising: adjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoils have a relationship between a gap/chord ratio and span position that defines a curve
1. An airfoil arrangement of a turbine engine comprising: adjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoils have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope, the adjacent airfoils are rotating blades, the gap/chord ratio is less than 1.0 at 100% span, and the gap/chord ratio is less than 1.0 at each span position. 2. The airfoil arrangement according to claim 1, wherein the gap/chord ratio is less than 0.9 at 0% span. 3. The airfoil arrangement according to claim 2, wherein the gap/chord ratio is less than 0.8 at 0% span. 4. The airfoil arrangement according to claim 3, wherein the gap/chord ratio is less than 0.7 at 0% span. 5. The airfoil arrangement according to claim 1, wherein the portion is from 80% span to 100% span. 6. A gas turbine engine comprising: a combustor section arranged between a compressor section and a turbine section;a fan section having a fan pressure ratio of less than 1.55; andadjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoils have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope, the adjacent airfoils are rotating blades, the gap/chord ratio is less than 1.0 at 100% span, the fan section has an array of twenty-six or fewer fan blades, and the gap/chord ratio is less than 1.0 at each span position. 7. The gas turbine engine according to claim 6, wherein the airfoils are arranged in the compressor section. 8. The gas turbine engine according to claim 7, wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged immediately upstream of the combustor section, the airfoils provided in a compressor outside the high pressure compressor section. 9. The gas turbine engine according to claim 8, wherein the low pressure compressor is counter-rotating relative to the array of fan blades. 10. The gas turbine engine according to claim 8, wherein the gas turbine engine is a two-spool configuration. 11. The gas turbine engine according to claim 8, wherein the low pressure compressor is immediately downstream from the fan section. 12. The gas turbine engine according to claim 8, wherein the airfoils are rotatable relative to an engine static structure. 13. The gas turbine engine according to claim 6, wherein the gap/chord ratio is less than 0.9 at 0% span. 14. The gas turbine engine according to claim 13, wherein the gap/chord ratio is less than 0.8 at 0% span. 15. The gas turbine engine according to claim 14, wherein the gap/chord ratio is less than 0.7 at 0% span. 16. The gas turbine engine according to claim 6, wherein the portion is from 80% span to 100% span. 17. The gas turbine engine according to claim 6, wherein the gap/chord ratio is greater than 0.6 at each span position. 18. The gas turbine engine according to claim 6, wherein the adjacent airfoils are fan blades arranged in the fan section. 19. The gas turbine engine according to claim 18, wherein the curve has another portion with a positive slope. 20. A gas turbine engine comprising: a fan section including a fan;a gear arrangement configured to drive the fan section;a compressor section;a turbine section configured to drive the compressor section and the gear arrangement; andadjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the adjacent airfoils have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope from 80% span to 100% span and another portion with a positive slope, and the gap/chord ratio is less than 1.0 at each span position. 21. The gas turbine engine according to claim 20, wherein the adjacent airfoils are blades arranged in the compressor section. 22. The airfoil according to claim 21, wherein the gap/chord ratio is greater than 0.6 at each span position. 23. The gas turbine engine according to claim 20, wherein the adjacent airfoils are fan blades arranged in the fan section.
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