Rotor blade airfoil
Rotor blades and turbomachines are provided. A rotor blade includes a platform and an airfoil extending radially from a root proximate the platform to a tip. The airfoil includes a leading edge and a trailing edge. The airfoil further includes a pressure side surface extending between the leading edge and the trailing edge. The airfoil also includes a suction side surface disposed opposite the pressure side surface and extending between the leading edge and the trailing edge. The leading edge, the trailing edge, the pressure side surface, and the suction side surface collectively define a first profile at the tip and a second profile radially inward from the tip. The first profile includes a suction side overhang, a pressure side overhang, and a pressure side underhang relative to the second profile.
1. A rotor blade for a turbomachine, the rotor blade comprising:
a platform;
an airfoil extending radially from a root proximate the platform to a tip, the airfoil comprising:
a leading edge;
a trailing edge;
a pressure side surface extending between the leading edge and the trailing edge;
a suction side surface disposed opposite the pressure side surface and extending between the leading edge and the trailing edge;
wherein the leading edge, the trailing edge, the pressure side surface, and the suction side surface collectively define a first profile at the tip and a second profile radially inward from the tip;
wherein the first profile includes a suction side overhang, a pressure side overhang, and a pressure side underhang relative to the second profile.
2. The rotor blade as in claim 1 , wherein the airfoil defines a radial span length between the root and the tip, and wherein the second profile is defined between about 90% and about 99% of the radial span length.
3. The rotor blade as in claim 1 , wherein the pressure side underhang is defined between the leading edge and the pressure side overhang.
4. The rotor blade as in claim 1 , wherein the pressure side overhang is defined between the pressure side underhang and the trailing edge.
5. The rotor blade as in claim 1 , wherein the first profile includes a pressure side arc length and a suction side arc length, the pressure side arc length measured from the leading edge along the pressure side surface to the trailing edge, the suction side arc length measured from the leading edge along the suction side surface to the trailing edge.
6. The rotor blade as in claim 5 , wherein the suction side overhang is defined along the entirety of the suction side arc length.
7. The rotor blade as in claim 5 , wherein the pressure side underhang transitions to the pressure side overhang at a transition point located between about 15% and about 35% of the pressure side arc length measured from the leading edge to the trailing edge.
8. The rotor blade as in claim 5 , wherein the first profile includes a maximum suction side overhang relative the second profile at between about 30% and about 60% of the suction side arc length.
9. The rotor blade as in claim 5 , wherein the first profile includes a maximum pressure side overhang relative the second profile between about 40% and about 70% of the pressure side arc length.
10. A turbomachine, comprising:
a compressor section;
a combustor section downstream from the compressor section;
a turbine section downstream from the combustor section;
a plurality of rotor blades provided in the turbine section, each of the plurality of rotor blades comprising:
a platform;
an airfoil extending radially from a root proximate the platform to a tip, the airfoil comprising:
a leading edge;
a trailing edge;
a pressure side surface extending between the leading edge and the trailing edge:
a suction side surface disposed opposite the pressure side surface and extending between the leading edge and the trailing edge;
wherein the leading edge, the trailing edge, the pressure side surface, and the suction side surface collectively define a first profile at the tip and a second profile radially inward from the first profile; and
wherein the first profile includes a suction side overhang, a pressure side overhang, and a pressure side underhang relative to the second profile.
11. The turbomachine as in claim 10 , wherein the airfoil defines a radial span length between the root and the tip, and wherein the second profile is defined between about 90% and about 99% of the radial span length.
12. The turbomachine as in claim 10 , wherein the pressure side underhang is defined between the leading edge and the pressure side overhang.
13. The turbomachine as in claim 10 , wherein the pressure side overhang is defined between the pressure side underhang and the trailing edge.
14. The turbomachine as in claim 10 , wherein the first profile includes a pressure side arc length and a suction side arc length, the pressure side arc length measured from the leading edge along the pressure side surface to the trailing edge, the suction side arc length measured from the leading edge along the suction side surface to the trailing edge.
15. The turbomachine as in claim 14 , wherein the suction side overhang is defined along the entirety of the suction side arc length.
16. The turbomachine as in claim 14 , wherein the pressure side underhang transitions to the pressure side overhang at a transition point located between about 15% and about 35% of the pressure side arc length measured from the leading edge to the trailing edge.
17. The turbomachine as in claim 14 , wherein the first profile includes a maximum suction side overhang relative the second profile at between about 30% and about 60% of the suction side arc length.
18. The turbomachine as in claim 14 , wherein the first profile includes a maximum pressure side overhang relative the second profile between about 40% and about 70% of the pressure side arc length.