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1. (WO2015175051) PROFIL AÉRODYNAMIQUE DE MOTEUR À TURBINE À GAZ
Note: Texte fondé sur des processus automatiques de reconnaissance optique de caractères. Seule la version PDF a une valeur juridique

CLAIMS

What is claimed is:

1. A compressor airfoil of a turbine engine having a geared architecture comprising:

pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span, where the negative slope leans forward relative to an engine axis.

2. The compressor airfoil according to claim 1 , wherein the curve has a negative slope from 80% span to 100% span.

3. The compressor airfoil according to claim 2, wherein the curve has a negative slope from 70% span to 100% span.

4. The compressor airfoil according to claim 1 , wherein the curve has a positive slope beginning at 0% span, where the positive slope leans aftward relative to the engine axis.

5. The compressor airfoil according to claim 4, wherein the positive slope extends from 0% span to 40% span.

6. The compressor airfoil according to claim 5, wherein the curve transitions from the positive slope to the negative slope in a range of 40% span to 75% span.

7. A gas turbine engine comprising:

a combustor section arranged between a compressor section and a turbine section; a fan section having an array of twenty-six or fewer fan blades, wherein the fan section has a fan pressure ratio of less than 1.55;

a geared architecture coupling the fan section to the turbine section or the compressor section; and

an airfoil arranged in the compressor section and including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span, where the negative slope leans forward relative to an engine axis.

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.

9. The gas turbine engine according to claim 8, wherein the airfoil is provided in a compressor outside the high pressure compressor.

10. The gas turbine engine according to claim 9, wherein the low pressure compressor is counter-rotating relative to the fan blades.

11. The gas turbine engine according to claim 9, wherein the gas turbine engine is a two-spool configuration.

12. The gas turbine engine according to claim 9, wherein the low pressure compressor is immediately downstream from the fan section.

13. The gas turbine engine according to claim 8, wherein the airfoil is rotatable relative to an engine static structure.

14. The gas turbine engine according to claim 7, wherein the curve has a negative slope from 80% span to 100% span.

15. The gas turbine engine according to claim 14, wherein the curve has a negative slope from 70% span to 100% span.

16. The gas turbine engine according to claim 7, wherein the curve has a positive slope beginning at 0% span, where the positive slope leans aftward relative to the engine axis.

17. The gas turbine engine according to claim 16, wherein the positive slope extends from 0% span to 40% span.

18. The gas turbine engine according to claim 17, wherein the curve transitions from the positive slope to the negative slope in a range of 40% span to 75% span.