Annular wall of a combustion chamber with improved cooling at the level of primary and/or dilution holes
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.
1. 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 first 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 second circumferential row to allow the 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 first 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 first cooling orifices being distributed according to a plurality of circumferential rows spaced axially from one another and geometric axes of each of the first cooling orifices being inclined, in an axial direction of a flow of combustion gases, by an angle of inclination θ1 relative to a normal N to the annular wall; and
a plurality of second cooling orifices distributed according to a plurality of circumferential rows spaced axially from one another, including a first row of the second cooling orifices arranged immediately downstream of the primary holes, and including a second row of the second cooling orifices arranged immediately downstream of the dilution holes, geometric axes of each of the second cooling orifices being arranged in a plane perpendicular to the axial direction and inclined by an angle of inclination θ2 relative to a normal N to the annular wall,
wherein ones of the second cooling orifices in the first row that overlap the primary holes in the axial direction have a greater densification than all of the second cooling orifices in the first row that do not overlap the primary holes in the axial direction,
wherein ones of the second cooling orifices in the second row that overlap the dilution holes in the axial direction have a greater densification than all of the second cooling orifices in the second row that do not overlap the dilution holes in the axial direction, and
wherein the ones of the second cooling orifices in the first row that overlap the primary holes in the axial direction have a greater densification than ones of the second cooling orifices in a third row of the plurality of circumferential rows of second cooling orifices that overlap the primary holes in the axial direction, the third row being directly downstream from the first row of the second cooling orifices.
2. The wall as claimed in claim 1 , wherein the inclination θ2 of the second cooling orifices relative to the normal N to the annular wall is identical to that θ1 of the first cooling orifices.
3. The wall as claimed in claim 1 , wherein a diameter d 2 of the second cooling orifices is identical to a diameter d 1 of the first cooling orifices.
4. The wall as claimed in claim 1 , further comprising, at a level of a transition zone formed downstream of a row of the plurality of circumferential rows of second cooling orifices and upstream of a row of the plurality of circumferential rows of first cooling orifices, at least two rows of third cooling orifices that have geometric axes that are inclined, relative to a plane perpendicular to the axial direction, by an inclination determined as different for each of the two rows of the third cooling orifices.
5. The wall as claimed in claim 4 , wherein the inclination of the third cooling orifices in a first row of the at least two rows is 30° and the inclination of the third cooling orifices in a second row of the at least two rows is 60°.
6. The wall as claimed in claim 4 , wherein the at least two rows of the third cooling orifices are a plurality of rows having the inclinations distributed evenly between 0° and 90°.
7. A combustion chamber of a turbine engine, comprising at least one annular wall as claimed in claim 1 .
8. A turbine engine comprising a combustion chamber including at least one annular wall as claimed in claim 1 .
9. The wall as claimed in claim 1 , wherein at least one row of the plurality of circumferential rows of first cooling orifices overlaps with the first circumferential row of the plurality of primary holes at a same position in the axial direction.
10. The wall as claimed in claim 1 , wherein at least one row of the plurality of circumferential rows of first cooling orifices overlaps with the second circumferential row of the plurality of dilution holes at a same position in the axial direction.
11. The wall as claimed in claim 1 , wherein the ones of the second cooling orifices in the second row that overlap the dilution holes in the axial direction exhibit greater densification than ones of the second cooling orifices in a fourth row of the plurality of circumferential rows of second cooling orifices that overlap the dilution holes in the axial direction, the fourth row being directly downstream from the second row of the second cooling orifices.