Compressor rotor blade airfoils

1. A rotor blade comprising:

an airfoil having an airfoil shape, the airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at a base of the airfoil, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance; and wherein X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value, the airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.

2. The rotor blade of claim 1 , wherein the airfoil includes a stagger angle distribution, each stagger angle in the stagger angle distribution being measured between a chord line of the airfoil and a rotary axis of the airfoil; wherein, for the airfoil having the nominal profile defined by the Cartesian coordinate values of X, Y and Z set forth in Table I, the stagger angle distribution is defined in accordance with Table X.

3. The rotor blade of claim 1 , wherein the rotor blade forms part of an early stage of a compressor section of a turbomachine.

4. The rotor blade of claim 1 , wherein the rotor blade is a second stage compressor rotor blade.

5. The rotor blade of claim 1 , wherein the airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to any airfoil surface location.

6. The rotor blade of claim 1 , wherein the scaling factor is between about 0.01 inches and about 10 inches.

7. The rotor blade of claim 1 , wherein the X, Y and Z values are scalable as a function of the scaling factor to provide a scaled-up or scaled-down airfoil.

8. A rotor blade comprising:

an airfoil having a nominal suction-side profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in Table I, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at a base of the airfoil, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance; and wherein X and Y values, when connected by smooth continuing arcs, define suction-side profile sections at each Z value, the suction-side profile sections at the Z values being joined smoothly with one another to form a complete airfoil suction-side shape.

9. The rotor blade of claim 8 , wherein the airfoil includes a stagger angle distribution each stagger angle in the stagger angle distribution being measured between a chord line of the airfoil and a rotary axis of the airfoil; wherein, for the airfoil having the nominal suction-side profile defined by the Cartesian coordinate values of X, Y and Z set forth in Table I, the stagger angle distribution is defined in accordance with Table X.

10. The rotor blade of claim 8 , wherein the rotor blade forms part of an early stage of a compressor section of a turbomachine.

11. The rotor blade of claim 8 , wherein the rotor blade is a second stage compressor rotor blade.

12. The rotor blade of claim 8 , wherein the nominal suction-side profile lies in an envelope within +/−5% of a chord length in a direction normal to any airfoil surface location.

13. The rotor blade of claim 8 , wherein the scaling factor is between about 0.01 inches and about 10 inches.

14. The rotor blade of claim 8 , wherein the X, Y and Z values are scalable as a function of the scaling factor to provide a scaled-up or scaled-down airfoil.

15. A turbomachine comprising:

a compressor section;

a turbine section downstream from the compressor section;

a combustion section downstream from the compressor section and upstream from the turbine section; and

two or more rotor blades disposed within the compressor section of the turbomachine, each rotor blade of the two or more rotor blades comprising:

an airfoil having an airfoil shape, the airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at a base of the airfoil, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance; and wherein X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value, the airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.

16. The turbomachine of claim 15 , wherein the airfoil includes a stagger angle distribution, each stagger angle in the stagger angle distribution being measured between a chord line of the airfoil and a rotary axis of the airfoil; wherein, for the airfoil having the nominal profile defined by the Cartesian coordinate values of X, Y and Z set forth in Table I, the stagger angle distribution is defined in accordance with Table X.

17. The turbomachine of claim 15 , wherein the two or more rotor blades each form part of an early stage of the compressor section.