Compressor stator vane airfoils
A stator vane 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, or TABLE III. The Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at a base of the airfoil. The Cartesian coordinate values of X, Y, and Z are non-dimensional values that are 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 are connected by smooth continuing arcs to 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 stator vane 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, or TABLE III, 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 that are 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 are connected by smooth continuing arcs to 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 stator vane 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, when the airfoil is 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 IV; wherein, when the airfoil is defined by the Cartesian coordinate values of X, Y, and Z set forth in TABLE II, the stagger angle distribution is defined in accordance with TABLE V; and wherein, when the airfoil is defined by the Cartesian coordinate values of X, Y, and Z set forth in TABLE III, the stagger angle distribution is defined in accordance with TABLE VI.
3. The stator vane of claim 1 , wherein the stator vane is a fifth stage compressor stator vane.
4. The stator vane of claim 1 , wherein the stator vane is a sixth stage compressor stator vane.
5. The stator vane of claim 1 , wherein the stator vane is seventh stage compressor stator vane.
6. The stator vane 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 stator vane of claim 1 , wherein the scaling factor is between about 0.01 inches and about 10 inches.
8. The stator vane 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 stator vane 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, or TABLE III, 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 that are 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 are connected by smooth continuing arcs to 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 stator vane of claim 9 , 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, when the airfoil has 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 IV; wherein, when the airfoil is defined by the Cartesian coordinate values of X, Y, and Z set forth in TABLE II, the stagger angle distribution is defined in accordance with TABLE V; and wherein, when the airfoil is defined by the Cartesian coordinate values of X, Y, and Z set forth in TABLE III, the stagger angle distribution is defined in accordance with TABLE VI.
11. The stator vane of claim 9 , wherein the stator vane is a fifth stage compressor stator vane.
12. The stator vane of claim 9 , wherein the stator vane is a sixth stage compressor stator vane.
13. The stator vane of claim 9 , wherein the stator vane is a seventh stage compressor stator vane.
14. The stator vane 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 stator vane of claim 9 , wherein the scaling factor is between about 0.01 inches and about 10 inches.
16. The stator vane 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
a stator vane disposed within the compressor section, the stator vane 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, or TABLE III, 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 that are 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 are connected by smooth continuing arcs to 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, 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, when the airfoil has 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 IV; wherein, when the airfoil is defined by the Cartesian coordinate values of X, Y, and Z set forth in TABLE II, the stagger angle distribution is defined in accordance with TABLE V; and wherein, when the airfoil is defined by the Cartesian coordinate values of X, Y, and Z set forth in TABLE III, the stagger angle distribution is defined in accordance with TABLE VI.
19. The turbomachine of claim 17 , wherein a fifth stage of the compressor section includes a plurality of stator vanes defined according to TABLE I, a sixth stage of the compressor section includes a plurality of stator vanes defined according to TABLE II, and a seventh stage of the compressor section includes a plurality of stator vanes defined according to TABLE III.