Exhaust centerbody for a turbine engine

Patent metadata

Field	Value
Publication number	US-9816461-B2
Application number	US-201414339846-A
Country	US
Kind code	B2
Filing date	Jul 24, 2014
Priority date	Jul 24, 2013
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

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.

First claim

The invention claimed is:

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.

Assignees

• Snecma

Inventors

• Pouyau Guillaume
• Sirvin Nicolas

Classifications

• F01D17/10

  Final actuators (valves in general F16K {; blades with variable camber F01D5/148}) · CPC title

• Y10T29/49323

  Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles · CPC title

• F02K1/04 Primary

  Mounting of an exhaust cone in the jet pipe · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• B23P23/00

  Machines or arrangements of machines for performing specified combinations of different metal-working operations not covered by a single other subclass (if the particular kinds of operation are not essential B23Q37/00 - B23Q41/00; {working by laser beam combined with other working of metal B23K26/0093}) · CPC title