ANNULAR WALL OF A COMBUSTION CHAMBER WITH IMPROVED COOLING AT THE LEVEL OF PRIMARY AND/OR DILUTION HOLES

• US 20140260257A1
• Filed: 10/25/2012
• Published: 09/18/2014
• Est. Priority Date: 10/26/2011
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA), Turbomeca
• Inventors: Rullaud, Matthieu Francois, Carrere, Bernard Joseph, Jean-Pierre, Verdier, Hurbert Pascal
• Granted Patent: US 10,551,064 B2
• Time in Patent Office: Days
• US Class Current: 60/722
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03042 Film cooled combustion chamber walls or domes
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube

Abstract

An annular wall of a combustion chamber of a turbine engine including: a cold side and a hot side; plural dilution holes to allow circulating air of the cold side to enter the hot side for dilution of an air/fuel mixture; plural cooling orifices to allow the circulating air of the cold side to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices distributed spaced axially from one another and with geometric axes inclined, in an axial direction of flow of combustion gases, by an inclination angle relative to a normal to the annular wall; plural additional cooling orifices arranged directly downstream of the dilution holes and distributed spaced axially from one another, with geometric axes arranged in a plane perpendicular to the axial direction and inclined by an angle of inclination relative to a normal to the annular wall.

Claims

1-12. -12. (canceled)

13. An annular wall of a turbine engine combustion chamber, including a cold side and a hot side, the annular wall comprising:

a plurality of primary holes distributed according to a circumferential row to allow circulating air of the cold side of the annular wall to enter the hot side to create an air/fuel mixture;

a plurality of dilution holes distributed according to a circumferential row to allow circulating air of the cold side of the annular wall to enter the hot side to ensure dilution of the air/fuel mixture; and

a plurality of cooling orifices to allow the circulating air of the cold side of the annular wall to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices being distributed according to a plurality of circumferential rows spaced axially from one another and geometric axes of each of the cooling orifices being inclined, in an axial direction D of flow of combustion gases, by an angle of inclination θ

1 relative to a normal N to the annular wall; and

a plurality of additional cooling orifices arranged directly downstream of the primary holes and directly downstream of the dilution holes and distributed according to a plurality of circumferential rows spaced axially from one another, geometric axes of each of additional cooling orifices being arranged in a plane perpendicular to the axial direction D and inclined by an angle of inclination θ

2 relative to a normal N to the annular wall.

14. The wall as claimed in claim 13, wherein the inclination θ

2 of the additional orifices relative to the normal N to the annular wall is identical to that θ

1 of the cooling orifices.

15. The wall as claimed in claim 13, wherein a diameter d2 of the additional orifices is identical to a diameter dl of the cooling orifices and a pitch p2 of the additional orifices is identical to a pitch p1 of the cooling orifices.

16. The wall as claimed in claim 13, wherein the additional orifices exhibit greater densification just downstream of the primary holes and the dilution holes.

17. The wall as claimed in claim 13, further comprising at a level of a transition zone, formed downstream of the plurality of rows of additional orifices, at least two rows of orifices whereof geometric axes of each of the orifices are inclined, relative to a plane perpendicular to the axial direction D, by an inclination determined as different for each of the two rows.

18. The wall as claimed in claim 17, wherein the wall comprises two rows of orifices and the inclinations are 30°

and 60°

respectively.

19. The wall as claimed in claim 18, wherein the two rows of orifices are two rows of additional orifices arranged immediately upstream of a row of cooling orifices, two rows of cooling orifices arranged immediately downstream of a row of additional orifices, or a row of additional orifices and an adjacent row of cooling orifices.

20. The wall as claimed in claim 17, wherein the wall comprises plural rows of orifices and the inclinations are distributed evenly between 0°

and 90°

.

21. The wall as claimed in claim 13, wherein the direction of inclination of the additional orifices is restricted by the direction of flow of the air/fuel mixture downstream of the combustion chamber.

23. A combustion chamber of a turbine engine, comprising at least one annular wall as claimed in claim 13.

24. A turbine engine comprising a combustion chamber including at least one annular wall as claimed in claim 13.

22. An annular wall of a turbine engine combustion chamber, including a cold side and a hot side, the annular wall comprising:

a plurality of primary holes or dilution holes distributed according to a circumferential row to allow circulating air of the cold side of the annular wall to enter the hot side to respectively create an air/fuel mixture or ensure dilution of the air/fuel mixture;

a plurality of cooling orifices to allow the circulating air of the cold side of the annular wall to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices being distributed according to a plurality of circumferential rows spaced axially from one another and geometric axes of each of the cooling orifices being inclined, in an axial direction D of flow of combustion gases, by an angle of inclination θ

1 relative to a normal N to the annular wall; and

a plurality of additional cooling orifices arranged directly downstream of the primary holes or dilution holes and distributed according to a plurality of circumferential rows spaced axially from one another, geometric axes of each of the additional cooling orifices being arranged in a plane perpendicular to the axial direction D and inclined by an angle of inclination θ

2 relative to a normal N to the annular wall,

a level of a transition zone formed downstream of the plurality of rows of additional orifices, at least two rows of orifices whereof the geometric axes of each of the orifices are inclined, relative to a plane perpendicular to the axial direction D, by an inclination determined as different for each of the two rows.