Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the fourth stage of a turbine

• US 8,734,113 B2
• Filed: 06/29/2011
• Issued: 05/27/2014
• Est. Priority Date: 07/26/2010
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Girard, Patrick, Kueny, Olivier, Martet, Renaud, Royan, Renaud
• Primary Examiner(s): Wiehe, Nathaniel
• Assistant Examiner(s): YOUNGER, SEAN JERRARD
• Application Number:
  US13/171,561
• Publication Number:
  US 20120020806A1
• Time in Patent Office: 1,063 Days
• Field of Search: 415/191, 416/143, 416/191, 416/223.A, 416/223.R, 416/DIG.2, 416/DIG.5
• 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: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2220/321 for a special turbine stage
• CPC Class Codes: F05D 2220/3215 the last stage of the turbine
• CPC Class Codes: F05D 2240/121 related to the leading edge of a stator vane
• CPC Class Codes: F05D 2240/303 related to the leading edge of a rotor blade
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

When cold and in the non-coated 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 of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Claims

1. An aerodynamic profile for a turbine vane, the profile being, when cold and in a non-coated state, 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 of the point under consideration from a reference X,Y plane situated at the base of the nominal profile, and H is the height of said profile measured from said reference plane out to the end of the vane, 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.

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

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

3. The aerodynamic profile as claimed in claim 1, wherein the coordinates X,Y of said profile lie within a range of ±

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

4. The aerodynamic profile as claimed in claim 1, wherein the vane is a nozzle vane forming a part of a stator of a turbine.

5. The aerodynamic profile as claimed in claim 4, wherein the vane is a nozzle vane of the fourth stage of the turbine.

6. The aerodynamic profile as claimed in claim 4, wherein the vane is a vane of the fourth stage nozzle of a turbine having four stages.

7. A turbine vane, presenting an aerodynamic profile as claimed in claim 1.

8. A turbine, including turbine vanes presenting aerodynamic profiles as claimed in claim 1.

9. A turbine as claimed in claim 8, including a nozzle that is stationary in rotation, having 100 to 120 vanes.

10. A turbine nozzle forming a portion of a turbine stator, wherein all the vanes of the nozzle present an aerodynamic profile as claimed in claim 1.

11. A turbine nozzle as claimed in claim 10, including 100 to 120 vanes.