OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE VANE, IN PARTICULAR FOR A NOZZLE OF THE SEVENTH STAGE OF A TURBINE

• US 20180230809A1
• Filed: 12/29/2016
• Published: 08/16/2018
• Est. Priority Date: 07/13/2016
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Safran Aircraft Engine Company
• Inventors: ROUTIER, Pascal Pierre, LEONARDON, Vincent Nicolas, MAN, Daniel Marius, SCHOLL, Guillaume Jochen
• Granted Patent: US 10,443,393 B2
• Time in Patent Office: Days
• 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 2220/3215 the last stage of the turbine
• 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 profile being, when cold and in a non-coated state, 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 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 seventh stage of the turbine.

6. The aerodynamic profile as claimed in claim 4, wherein the vane is a vane of the seventh stage nozzle of a turbine having seven 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 102 to 122 vanes that present aerodynamic profiles comprising:

when cold and in a non-coated state, 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 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.

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 102 to 122 vanes that present aerodynamic profiles comprising:

when cold and in a non-coated state, 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 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.