Optimized aerodynamic profile for a turbine blade
View Patent ↗When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the rectangular coordinates X,Y,Z′ given in Table 1, in which the X coordinate is measured in the axial direction of the turbine, and the Z′ coordinate is the quotient D/H, where D is the distance of the point in question from a reference plane P 0 situated at the base of the nominal profile and H is the height of the profile measured from said reference plane to the tip of the blade, the measurements D and H being taken radially relative to the axis of the turbine.
1. An aerodynamic profile for a turbine blade, said profile, when cold and in a non-coated state, being substantially identical to a nominal profile determined by the rectangular coordinates X,Y,Z′ given in Table 1, in which the X coordinate is measured in the axial direction of the turbine, and the Z′ coordinate is the quotient D/H, where D is the distance of the point in question from a reference plane P 0 situated at the base of the nominal profile and H is the height of the profile measured from said reference plane to the tip of the blade, the measurements D and H being taken radially relative to the axis of the turbine.
2. An aerodynamic profile according to claim 1 , wherein the relationship between the Z′ coordinate and the axial chord CA of the nominal profile complies with the curve of FIG. 3 .
3. An aerodynamic profile according to claim 1 , wherein the relationship between the Z′ coordinate and the inside area defined by the outline of the nominal profile in an X,Y plane complies with the curve of FIG. 4 .
4. An aerodynamic profile according to claim 1 , wherein the relationship between the Z′ coordinate and the maximum thickness Emax of the nominal profile measured in an X,Y plane complies with the curve of FIG. 5 .
5. An aerodynamic profile according to claim 1 , said profile being defined in an envelope of ±1 mm in a direction normal to the surface of the nominal profile.
6. An aerodynamic profile according to claim 1 , wherein the X,Y coordinates of said profile lie within ±5% relative to the X,Y coordinates of the nominal profile.
7. A turbine blade, presenting an aerodynamic profile according to claim 1 .
8. A turbine, including turbine blades presenting aerodynamic profiles according to claim 1 .
9. A turbine according to claim 8 , including a moving wheel having 60 to 68 of said turbine blades.