Compressor rotor blade airfoils
A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. 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. The 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 are joined smoothly with one another to form a complete airfoil shape.
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 II, 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 in accordance with one of Table XI, each stagger angle in the stagger angle distribution being measured between a chord line of the airfoil and a rotary axis of the airfoil.
3. The rotor blade of claim 1 , wherein the rotor blade forms part of a stage of a compressor section.
4. The rotor blade of claim 3 , wherein the stage of the compressor section is an early stage of the compressor section.
5. The rotor blade of claim 1 , wherein the rotor blade is a third stage compressor rotor blade.
6. 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.
7. The rotor blade of claim 1 , wherein the scaling factor is between about 0.01 inches and about 10 inches.
8. 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.
9. 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 II, 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.
10. The rotor blade of claim 9 , wherein the airfoil includes a stagger angle distribution in accordance with Table XI, each stagger angle in the stagger angle distribution being measured between a chord line of the airfoil and a rotary axis of the airfoil.
11. The rotor blade of claim 9 , wherein the rotor blade forms part of a stage of a compressor section.
12. The rotor blade of claim 11 , wherein the stage of the compressor section is an early stage of the compressor section.
13. The rotor blade of claim 9 , wherein the rotor blade is one of a third stage compressor rotor blade.
14. The rotor blade of claim 9 , 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.
15. The rotor blade of claim 9 , wherein the scaling factor is between about 0.01 inches and about 10 inches.
16. The rotor blade of claim 9 , 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.
17. A compressor section comprising:
a plurality of rotor blades arranged in a plurality of stages, each rotor blade of the plurality of rotor blades comprising an airfoil having an airfoil shape, the airfoil shapes of the plurality of rotor blades each having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX, 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;
wherein the plurality of stages comprises:
a third stage comprising the airfoil having the airfoil shape with the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in Table II;
a sixth stage comprising the airfoil having the airfoil shape with the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in Table III;
a seventh stage comprising the airfoil having the airfoil shape with the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in Table IV;
an eighth stage comprising the airfoil having the airfoil shape with the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in Table V;
a ninth stage comprising the airfoil having the airfoil shape with the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in Table VI;
an eleventh stage comprising the airfoil having the airfoil shape with the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in Table VII;
a twelfth stage comprising the airfoil having the airfoil shape with the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in Table VIII; and
a thirteenth stage comprising the airfoil having the airfoil shape with the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in Table IX.