Turbine blade with airfoil tip vortex control
A rotor blade for a gas turbine engine is provided. The rotor blade having: an attachment; an airfoil extending from the attachment to a tip; and a tip shelf located in a surface of the tip proximate to a pressure side of the airfoil, wherein the tip shelf has a ledge portion extending from the pressure side to a wall portion extending upwardly from the ledge portion to the tip and wherein the wall portion is configured to have a convex portion with respect to the pressure side of the airfoil as it extends from a leading edge to a trailing edge of the airfoil.
1. A rotor blade for a gas turbine engine, comprising:
an attachment;
an airfoil extending from the attachment to a tip, wherein the airfoil has a stagger angle that changes as the airfoil extends between the attachment and the tip, the airfoil further comprising a base region disposed adjacent to the attachment, a tip region, and a transition region located between the base region and the tip region; wherein a rate of the change of the stagger angle in the transition region is greater than a rate of the change of the stagger angle in the base region; wherein the rate of the change of the stagger angle in the transition region is greater than a rate of change of the stagger angle in the tip region; and wherein the airfoil has a chord that increases as the airfoil extends from the base region to the tip; and
a tip shelf located in a surface of the tip proximate to a pressure side of the airfoil, wherein the tip shelf has a ledge portion extending from the pressure side to a wall portion extending upwardly from the ledge portion to the tip and wherein the wall portion is configured to have a convex portion with respect to the pressure side of the airfoil as it extends from a leading edge to a trailing edge of the airfoil.
2. The rotor blade of claim 1 , wherein the ledge portion has a concave portion that results in the wall portion having varying heights as it extends upwardly from the ledge portion.
3. The rotor blade of claim 1 , wherein the ledge portion has a convex portion that results in the wall portion having varying heights as it extends upwardly from the ledge portion.
4. The rotor blade of claim 2 , wherein the ledge portion also has a convex portion that results in the wall portion having varying heights as it extends upwardly from the ledge portion, wherein the convex portion of the ledge portion is located proximate to the trailing edge of the airfoil and wherein the concave portion of the ledge comprises greater than 50% of the ledge portion.
5. The rotor blade of claim 1 , wherein the convex portion of the wall portion comprises at least 50% of the wall portion that extends from the leading edge to the trailing edge of the airfoil.
6. The rotor blade of claim 1 , further comprising a squealer pocket located in a surface of the tip.
7. The rotor blade of claim 2 , further comprising a squealer pocket located in a surface of the tip.
8. The rotor blade of claim 3 , further comprising a squealer pocket located in a surface of the tip.
9. The rotor blade of claim 4 , further comprising a squealer pocket located in a surface of the tip.
10. The rotor blade of claim 1 , wherein another portion of the wall portion is concave with respect to pressure side of the airfoil and the another portion is located proximate to the trailing edge of the airfoil.
11. The rotor blade of claim 6 , wherein the squealer pocket is at least partially surrounded by a first surface of a wall located between the squealer pocket and the pressure side of the airfoil, wherein the first surface of the wall has a convex configuration with respect to the pressure side of the airfoil as it extends from a leading edge to a trailing edge of the airfoil.
12. The rotor blade of claim 11 , wherein the squealer pocket is at least partially surrounded by a second surface of a wall located between the squealer pocket and a suction side of the airfoil, wherein the second surface of the wall has a convex configuration with respect to the suction side of the airfoil as it extends from the leading edge to the trailing edge of the airfoil.
13. The rotor blade of claim 12 , wherein the first surface and the second surface are in a facing spaced relationship with respect to each other and the squealer pocket is located between the first surface and the second surface.
14. A gas turbine engine, comprising:
a compressor section;
a combustor section; and
a turbine section; wherein at least one of the turbine section and compressor section includes a plurality of rotors having a plurality of radially disposed rotor blades at least some of the plurality of radially disposed rotor blades having:
an attachment;
an airfoil extending from the attachment to a tip, wherein the airfoil has a stagger angle that changes as the airfoil extends between the attachment and the tip, the airfoil further comprising a base region disposed adjacent to the attachment, a tip region, and a transition region located between the base region and the tip region; wherein a rate of the change of the stagger angle in the transition region is greater than a rate of the change of the stagger angle in the base region; wherein the rate of the change of the stagger angle in the transition region is greater than a rate of change of the stagger angle in the tip region; and wherein the airfoil has a chord that increases as the airfoil extends from the base region to the tip;
a tip shelf located in a surface of the tip proximate to a pressure side of the airfoil, wherein the tip shelf has a ledge portion extending from the pressure side to a wall portion extending upwardly from the ledge portion to the tip and wherein the wall portion is configured to have a convex portion with respect to the pressure side of the airfoil as it extends from a leading edge to a trailing edge of the airfoil.
15. The gas turbine engine as in claim 14 , wherein the wall portion further comprises a concave portion that is located proximate to the trailing edge of the airfoil.
16. The gas turbine engine of claim 15 , further comprising a squealer pocket located in a surface of the tip.
17. A rotor blade for a gas turbine engine, comprising:
an attachment;
an airfoil extending from the attachment to a tip;
a tip shelf located in a surface of the tip proximate to a pressure side of the airfoil; and
wherein the airfoil has a stagger angle that changes as the airfoil extends between the attachment and the tip, the airfoil further comprising a base region disposed adjacent to the attachment, a tip region, and a transition region located between the base region and the tip region; wherein a rate of the change of the stagger angle in the transition region is greater than a rate of the change of the stagger angle in the base region; wherein the rate of the change of the stagger angle in the transition region is greater than a rate of change of the stagger angle in the tip region; and wherein the airfoil has a chord that increases as the airfoil extends from the base region to the tip, wherein the tip shelf has a ledge portion extending from the pressure side to a wall portion extending upwardly from the ledge portion to the tip.
18. The rotor blade of claim 17 , wherein the wall portion is generally flat and straight and is parallel to the pressure side proximate to the tip shelf.
19. The rotor blade of claim 17 , further comprising a squealer pocket located in a surface of the tip and wherein the wall portion is configured to have a convex portion with respect to the pressure side of the airfoil as it extends from a leading edge to a trailing edge of the airfoil and wherein the wall portion further comprises a concave portion that is located proximate to the trailing edge of the airfoil.
20. The rotor blade of claim 18 , further comprising a squealer pocket located in a surface of the tip.