OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE BLADE

• US 20100040475A1
• Filed: 08/13/2009
• Published: 02/18/2010
• Est. Priority Date: 08/13/2008
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: BOQUET, Michel, BOTREL, Erwan
• Granted Patent: US 8,496,441 B2
• Time in Patent Office: Days
• US Class Current: 416/223.R
• 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 2220/321 for a special turbine stage
• CPC Class Codes: F05D 2240/301 Cross-sectional characteristics
• 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

Abstract

When cold and in the uncoated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance from the point in question to a reference plane P0 situated at the base of the nominal profile and H is the height of this profile, measured from the reference plane to the tip of the blade. The measurements D and H are taken radially relative to the axis of the turbine, while the coordinate X is measured in the axial direction of the turbine.

Claims

1. An aerodynamic profile of a turbine blade, wherein, when cold and in the uncoated state, said profile is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Z′

given in Table 1, in which the coordinate Z′

is the quotient D/H where D is the distance from the point in question to a reference plane P0, situated at the base of the nominal profile and H is the height of this 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, while the coordinate X is measured in the axial direction of the turbine and the height H being 43 mm±

30%.

2. The aerodynamic profile as claimed in claim 1, wherein the relationship between the coordinate Z′

and the axial chord CA of the nominal profile complies with the curve of FIG. 3.

3. The aerodynamic profile as claimed in claim 1, wherein the relationship between the coordinate Z′

and the internal area defined by the external contour of the nominal profile in a plane X, Y complies with the curve of FIG. 4.

4. The aerodynamic profile as claimed in claim 1, wherein the relationship between the coordinate Z′

and the maximum thickness Emax of the nominal profile measured in a plane X, Y complies with the curve of FIG. 5.

5. The aerodynamic profile as claimed in claim 1, wherein said profile is defined in an envelope of ±

1 mm in a direction normal to the surface of the nominal profile.

6. The aerodynamic profile as claimed in claim 1, wherein the coordinates X, Y of said profile are in the range of ±

5% relative to the coordinates X, Y of the nominal profile.

7. A turbine blade, which has an aerodynamic profile as claimed in claim 1.

8. A turbine, which comprises turbine blades having aerodynamic profiles as claimed in claim 1.

9. The turbine as claimed in claim 8, which comprises a movable rotor having between 70 and 78 blades which have aerodynamic profiles as claimed in claim 1.

10. A turbomachine, comprising a turbine having at least one blade the aerodynamic profile of which complies with claim 1.