Annular combustion chamber for a turbine engine including improved dilution openings

Patent metadata

Field	Value
Publication number	US-9599342-B2
Application number	US-201214001429-A
Country	US
Kind code	B2
Filing date	Feb 20, 2012
Priority date	Feb 25, 2011
Publication date	Mar 21, 2017
Grant date	Mar 21, 2017

Abstract

An annular wall for an annular turbine engine combustion chamber, including one annular row of dilution orifices including larger area orifices and smaller area orifices, and a multi-perforation formed from micro-perforations distributed as an upstream row, a downstream row, and at least one intermediate row interrupted by the orifices, a geometric ratio being defined as the quotient obtained by dividing the maximum spacing L between any two points on the edge of the orifice measured along a direction parallel to an axis of the wall by the maximum spacing l between any two points on the edge of this orifice measured along a direction perpendicular to the axis, the geometric ratio of the larger area orifices being greater than or equal to 1, and the geometric ratio of the smaller area orifices being greater than the geometric ratio of the larger area orifices.

First claim

The invention claimed is:

1. An annular wall for an annular turbine engine combustion chamber, comprising:
at least one annular row of dilution air inlet orifices comprising two types of orifices differentiated by their cross-sectional area of orifices with a larger area and orifices with a smaller area; and
a multi-perforation for cooling the wall, the multi-perforation including micro-perforations that have a cross-sectional area less than an area of each of the dilution air inlet orifices and that are distributed as an upstream annular row and a downstream annular row formed on an upstream side and downstream side respectively of the row of dilution air inlet orifices, and as at least one intermediate annular row interrupted by the dilution air inlet orifices, a geometric ratio being defined for each of the dilution air inlet orifices as the quotient obtained by dividing a maximum spacing between any two points on an edge of the orifice measured along a direction parallel to an axis of revolution of the wall by a maximum spacing between any two points on an edge of the orifice measured along a direction perpendicular to the axis of revolution;
wherein the geometric ratio of the dilution air inlet orifices with the larger area is greater than or equal to 1, and
wherein the geometric ratio of the dilution air inlet orifices with the smaller area is greater than the geometric ratio of the dilution air inlet orifices with the larger area.

2. A wall according to claim 1 , wherein the dilution air inlet orifices with the larger area are circular in shape and the dilution air inlet orifices with the smaller area are oval in shape.

3. A wall according to claim 1 , wherein the edges of the two types of the dilution air inlet orifices have respective upstream and downstream ends that are circumferentially in line with each other.

4. A wall according to claim 1 , wherein each intermediate annular row of the multi-perforation is interrupted by the two types of dilution air inlet orifices.

5. A wall according to claim 1 , wherein an axial spacing between each pair of consecutive rows among the upstream, downstream, and intermediate annular rows of the multi-perforation is equal to a constant predetermined value.

6. An annular combustion chamber for a turbine engine, comprising:
two coaxial annular walls, of an inner wall and an outer wall, connected to each other by an annular chamber bottom wall,
wherein at least one of the coaxial annular walls is a wall according to claim 1 .

7. A turbine engine, comprising an annular combustion chamber according to claim 6 .

8. A wall according to claim 1 , wherein the edges of the two types of the dilution air inlet orifices have respective upstream or downstream ends that are circumferentially in line with each other.

9. A wall according to claim 1 , wherein a plurality of the dilution air inlet orifices with the smaller area are positioned between an adjacent pair of the dilution air inlet orifices with the larger area.

Assignees

• Leblond Nicolas Christian Raymond
• Bunel Jacques Marcel Arthur
• Lains Dominique Maurice Jacques
• Snecma

Inventors

• Leblond Nicolas Christian Raymond
• Bunel Jacques Marcel Arthur
• Lains Dominique Maurice Jacques

Classifications

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title