Local pressure side blade tip lean
A rotor blade of a gas turbine engine includes a pressure side, and a suction side opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from a blade root to a blade tip. The rotor blade defines a cross-sectional median line midway between the pressure side and the suction side. The cross-sectional median line extends in a generally radial direction from the blade root to a lean point between the blade root and the blade tip. The cross-sectional median line extends off of radial from the lean point to the blade tip, defining a lean of the rotor blade between the lean point and the blade tip.
1. A rotor blade of a gas turbine engine, comprising:
a pressure side; and
a suction side opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from a blade root to a blade tip;
wherein the rotor blade defines a cross-sectional median line midway between the pressure side and the suction side, the cross-sectional median line extending in a generally radial direction from the blade root to a lean point between the blade root and the blade tip, the cross-sectional median line extending off of radial from the lean point to the blade tip, defining a lean of the rotor blade between the lean point and the blade tip; and
wherein the lean point is disposed at a radial position defined relative to the blade tip by a distance equal to between 100% and 300% of a tip clearance, defined as the distance between the blade tip and an outer air seal.
2. The rotor blade of claim 1 , wherein the lean point is disposed at between 80% of a rotor blade radial span and 95% of the rotor blade radial span, measured from the blade root.
3. The rotor blade of claim 2 , wherein the lean point is disposed at 90% of the rotor blade radial span, measured from the blade root.
4. The rotor blade of claim 1 , wherein the cross-sectional median line extends off of radial toward the pressure side from the lean point to the blade tip.
5. The rotor blade of claim 1 , wherein the cross-sectional median line extends off radial by a magnitude equal to between 5% and 20% of the rotor blade radial span.
6. The rotor blade of claim 1 , wherein the cross-sectional medial line extends off radial by a magnitude equal to between 100% and 300% of the tip clearance, defined as the radial distance between the blade tip and an outer air seal.
7. The rotor blade of claim 1 , wherein the cross-sectional median line extends off radial in a curvilinear direction.
8. A rotor of a gas turbine engine, comprising:
a rotor hub; and
a plurality of rotor blades extending from the hub at a blade root outwardly to a blade tip, each rotor blade including:
a pressure side; and
a suction side opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from the blade root to the blade tip;
wherein the rotor blade defines a cross-sectional median line midway between the pressure side and the suction side, the cross-sectional median line extending in a general radial direction from the blade root to a lean point between the blade root and the blade tip, the cross-sectional median line extending off of radial from the lean point to the blade tip, defining a lean of the rotor blade between the lean point and the blade tip; and
wherein the lean point is disposed at a radial position defined relative to the blade tip by a distance equal to between 100% and 300% of a tip clearance, defined as the distance between the blade tip and an outer air seal.
9. The rotor of claim 8 , wherein the lean point is disposed at between 80% of a rotor blade radial span and 95% of the rotor blade radial span, measured from the blade root.
10. The rotor of claim 9 , wherein the lean point is disposed at 90% of the rotor blade radial span, measured from the blade root.
11. The rotor of claim 8 , wherein the cross-sectional median line extends off of radial toward the pressure side from the lean point to the blade tip.
12. The rotor of claim 8 , wherein the cross-sectional median line extends off radial by a magnitude equal to between 5% and 20% of the rotor blade radial span.
13. The rotor of claim 8 , wherein the cross-sectional medial line extends off radial by a magnitude equal to between 100% and 300% of the tip clearance, defined as the radial distance between the blade tip and an outer air seal.
14. The rotor of claim 8 , wherein the cross-sectional median line extends off radial in a curvilinear direction.
15. The rotor of claim 8 , wherein the rotor is a high pressure compressor rotor of the gas turbine engine.
16. A gas turbine engine, comprising:
a combustor; and
a compressor disposed upstream of the combustor to direct airflow to the combustor, the compressor including at least one rotor, the rotor including:
a rotor hub; and
a plurality of rotor blades extending from the hub at a blade root outwardly to a blade tip, each rotor blade including:
a pressure side; and
a suction side opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from the blade root to the blade tip;
wherein the rotor blade defines a cross-sectional median line midway between the pressure side and the suction side, the cross-sectional median line extending radially from the blade root to a lean point between the blade root and the blade tip, the cross-sectional median line extending off of radial from the lean point to the blade tip, defining a lean of the rotor blade between the lean point and the blade tip; and
wherein the lean point is disposed at a radial position defined relative to the blade tip by a distance equal to between 100% and 300% of a tip clearance, defined as the distance between the blade tip and an outer air seal.