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, or Table IV. 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 one of Table I, Table II, Table III, or Table IV, 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 V, Table VI, Table VII, or Table VIII, 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 mid stage of a compressor section of a turbomachine.
4. The rotor blade of claim 1 , wherein the rotor blade is disposed in one of an early stage of a compressor section of a turbomachine or a late stage of the compressor section of the turbomachine.
5. The rotor blade of claim 1 , wherein the rotor blade is one of a fourth stage compressor rotor blade, a filth stage compressor rotor blade, a tenth stage compressor rotor blade, or a fourteenth 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 same constant or number 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 one of Table I, Table II, Table III, or Table IV, 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 one of Table V, Table VI, Table VII, or Table VIII, 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 mid stage of a compressor section of a turbomachine.
12. The rotor blade of claim 9 , wherein the rotor blade is disposed in one of an early stage of a compressor section of a turbomachine or a late stage of the compressor section of the turbomachine.
13. The rotor blade of claim 9 , wherein the rotor blade is one of a fourth stage compressor rotor blade, a fifth stage compressor rotor blade, a tenth stage compressor rotor blade, or a fourteenth 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 same constant or number to provide a scaled-up or scaled-down airfoil.
17. 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 one of Table I, Table II, Table III, or Table IV, 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.
18. The turbomachine of claim 17 , wherein the airfoil includes a stagger angle distribution in accordance with one of Table V, Table VI, Table VII, or Table VIII, each stagger angle in the stagger angle distribution being measured between a chord line of the airfoil and a rotary axis of the airfoil.
19. The turbomachine of claim 17 , wherein the two or more rotor blades each form part of a mid stage of the compressor section.
20. The turbomachine of claim 17 , wherein each rotor blade of the two or more rotor blades is disposed in one of an early stage of the compressor section or a late stage of the compressor section.