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

• US 10,458,246 B2
• Filed: 12/29/2016
• Issued: 10/29/2019
• Est. Priority Date: 07/13/2016
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Safran Aircraft Engine Company
• Inventors: Mervant, Thomas Michel, Botrel, Erwan Daniel, Delabriere, Maxime Didier, Destouches, Jean-Armand Marc
• Primary Examiner(s): Amick, Jacob M
• Assistant Examiner(s): Brauch, Charles
• Application Number:
  US15/393,470
• Publication Number:
  US 20180230807A1
• Time in Patent Office: 1,034 Days
• 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 5/142 of the blades of successive rotor or stator blade-rows
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F01D 9/047 Nozzle boxes
• CPC Class Codes: F05D 2220/3218 for an intermediate stage of a compressor
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2240/128 Nozzles
• 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 non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim 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 aerodynamic profile defining the turbine vane when cold and in a non-coated state, the aerodynamic profile being substantially identical to a nominal profile determined by Cartesian coordinates X,Y,Zadim given in Table 1, in which the coordinate Zadim is a quotient D/H, where D is a distance of a point under consideration from a reference X,Y plane situated at a base of the nominal profile, and H is a height of said profile measured from said reference plane out to an end of the turbine vane, the measurements D and H being taken radially relative to an axial direction of a 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 turbine vane is a nozzle vane forming a part of a stator of the turbine.

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

6. The aerodynamic profile as claimed in claim 4, wherein the turbine vane is a vane of a fifth stage nozzle of the turbine, wherein the turbine includes seven stages.

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

8. A turbine, including a plurality of 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 140 to 160 vanes that each present the aerodynamic profile.

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

11. A turbine nozzle as claimed in claim 10, including 140 to 160 vanes that each present the aerodynamic profile.