OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE BLADE

• US 20070248465A1
• Filed: 04/18/2007
• Published: 10/25/2007
• Est. Priority Date: 04/20/2006
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: BOTREL, Erwan Daniel, Picot, Philippe, Lafarge, Gregory Pierre
• Granted Patent: US 7,785,075 B2
• Time in Patent Office: Days
• US Class Current: 416/223.A
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F05D 2250/71 curved
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10S 416/02 Formulas of curves
• CPC Class Codes: Y10S 416/05 Variable camber or chord length

Abstract

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 P0 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.

Claims

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 P0 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 blades that present aerodynamic profiles according to claim 1.