Turbine vane comprising a blade with a tub including a curved pressure side in a blade apex region

Patent metadata

Field	Value
Publication number	US-2018371925-A1
Application number	US-201615775034-A
Country	US
Kind code	A1
Filing date	Nov 14, 2016
Priority date	Nov 16, 2015
Publication date	Dec 27, 2018
Grant date	—

Abstract

A turbine vane of a turbine engine such as a turbojet. The vane includes a base supporting a blade that extends in a spanwise direction and ends in an apex. The blade includes a pressure-side wall and a suction-side wall, each ending at an end edge at the apex of the blade. The blade includes, at the apex thereof, a closed wall extending from the pressure-side wall to the suction-side wall so as to define, with the end edges, a tub shape. The pressure-side wall is curved inward so as to deviate from the spanwise direction in the region of the blade apex preceding the tub, between the base and the pressure-side end edge.

First claim

1 - 9 . (canceled)

10 . A turbine vane of a turbomachine such as a turbofan engine, this vane comprising a root carrying a blade which extends along a span direction terminating with an apex, said blade comprising a pressure-side wall and a suction-side wall each terminating with a terminal edge at the apex of the blade, the blade including at its apex a closing wall extending from the pressure side to the suction side, the terminal edge of the pressure-side wall and the terminal edge of the suction-side wall projecting from this wall for this wall to delimit with these terminal edges a tub shape, wherein: the pressure-side wall is curved so as to deviate from the span direction in the region of the blade apex, from a region located between the blade root and the tub, the pressure-side wall having a curvature determined by the relationship:

Δ


(
R
)

=

Δmax
*

(

R
-
Rmin

)

n

(

Rmax
-
Rmin

)

n

wherein:
Δ(R) designates an offset value of the pressure-side wall, for a section located at a radius R from the axis of rotation of the blade;
Rmax designates a maximum radius of the blade from the end of the blade apex to the axis of rotation;
Rmin designates the radius of the blade where the curvature of the pressure-side wall starts;
Δmax designates the maximum offset at the end of the blade apex;
n designates a smoothing power between 2 and 6.

11 . The vane according to claim 10 , wherein the terminal edge of the suction-side wall is curved so as to get closer to the span direction.

12 . The vane according to claim 10 , wherein the suction-side wall is curved so as to get closer to the span direction in the region of the blade apex preceding the tub.

13 . The vane according to claim 10 , wherein the terminal edge of the pressure side is also curved to deviate from the span direction.

14 . The vane according to claim 10 , wherein the terminal edge of the suction-side wall is oriented in parallel to the span direction.

15 . The vane according to claim 10 , wherein the terminal edge of the suction-side wall is cursed so as to deviate from the span direction.

16 . A turbine of a turbomachine comprising a vane according to claim 10 .

17 . A turbomachine comprising a turbine according to claim 16 .

Assignees

• Safran Aircraft Engines

Inventors

• Coudert Laurent Patrick Robert
• Botrel Erwan Daniel

Classifications

• F05D2200/10

  Basic functions · CPC title

• F05D2200/22

  Power · CPC title

• F01D9/041 Primary

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

• F05D2240/125

  related to the tip of a stator vane · CPC title

• F05D2220/323

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