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

Patent metadata

Field	Value
Publication number	US-10458246-B2
Application number	US-201615393470-A
Country	US
Kind code	B2
Filing date	Dec 29, 2016
Priority date	Jul 13, 2016
Publication date	Oct 29, 2019
Grant date	Oct 29, 2019

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 P 0 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 P 1 . 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.

First claim

We claim:

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.

Assignees

• Safran Aircraft Engines

Inventors

• Mervant Thomas Michel
• Botrel Erwan Daniel
• Delabriere Maxime Didier
• DESTOUCHES Jean-Armand Marc

Classifications

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D9/047

  Nozzle boxes · CPC title

• F05D2250/74

  given by a set or table of xyz-coordinates · CPC title

• F05D2220/3218

  for an intermediate stage of a compressor · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title