Exhaust centerbody for a turbine engine
View Patent ↗An exhaust centerbody for a turbine engine is provided. The centerbody includes a truncated downstream part, which is connected to an upstream part by an annular ridge marking a discontinuity between the outer surfaces of the upstream and downstream parts. The outer surface of the downstream part has a substantially conical general shape, of which the tip is oriented downstream and is positioned in the region of the axis A, the axial half-section of this outer surface defining a line of which the upstream end part is substantially tangential to a straight line passing through the ridge and forming a non-zero angle α with a tangent to the outer surface of the upstream part, in the region of the ridge, and of which the downstream end part is substantially tangential to a straight line passing through the tip and forming a non-zero angle β with the axis A.
1. An exhaust centerbody for a turbine engine, having rotational symmetry about a longitudinal axis A, comprising:
an upstream annular part; and
a downstream annular part, said downstream annular part being connected to the upstream annular part by an annular ridge marking a discontinuity in curvature between outer surfaces of the upstream and downstream annular parts, the outer surface of the downstream annular part having a substantially conical general shape, of which a tip is oriented downstream and is positioned substantially in a region of the axis A,
an axial half-section of the outer surface of the downstream annular part defining a line of which an upstream end part is substantially tangential to a first straight line passing through the annular ridge and forming a non-zero angle α with a tangent to the outer surface of the upstream annular part, in a region of the annular ridge, a downstream end part of said line being substantially tangential to a second straight line passing through the tip and forming a substantially non-zero angle β with the axis A,
wherein the upstream end part of the line has a concavity oriented downstream and the downstream end part of said line has a convexity oriented downstream; and
wherein the tangent to the outer surface of the upstream annular part intersects the axis A at a location downstream of the tip.
2. The centerbody according to claim 1 , wherein the line has a substantially undulating shape.
3. The centerbody according to claim 1 , wherein at least one of the angle α is between 20 and 90° and the angle β is between 10 and 90°.
4. A turbine engine comprising a centerbody according to claim 1 .
5. A method for producing an exhaust centerbody for a turbine engine, said centerbody having rotational symmetry about a longitudinal axis A, the method comprising:
a) determining a position on the axis A, upstream of which the centerbody will comprise an upstream annular part, downstream of which the centerbody will comprise a downstream annular part and in a region of which the centerbody will have an annular ridge marking a discontinuity in curvature between outer surfaces of the upstream and downstream annular parts of the centerbody;
b) designing the downstream annular part of the body, the outer surface of the downstream annular part having a substantially conical general shape, of which a tip is oriented downstream and is positioned substantially in a region of the axis A, an axial half-section of the outer surface of the downstream annular part defining a line of which an upstream end part is substantially tangential to a first straight line passing through the annular ridge and forming a non-zero angle α with a tangent to the outer surface of the upstream annular part, in a region of the ridge, and of which a downstream end part is substantially tangential to a second straight line passing through the tip and forming a substantially non-zero angle β with the axis A, the upstream end part of the line having a concavity oriented downstream and the downstream end part of said line having a convexity oriented downstream, the tangent to the outer surface of the upstream annular part intersecting the axis A at a location downstream of the tip; and
c) producing the centerbody.
6. The method according to claim 5 , wherein step a) comprises sub-steps including determining an annular region of separation of a flow of a gas stream acting on the exhaust centerbody by calculation, and selecting the position on the axis A to be an axial position which is furthest upstream in the region of separation.
7. The method according to claim 5 , wherein the line is obtained by polynomial interpolation.