Turbine engine combustion chamber
View Patent ↗An annular combustion chamber for a turbine engine, the chamber including an inner wall and an outer wall forming surfaces of revolution, the walls being connected together by a chamber end wall fitted with a fuel injection mechanism, each of the inner and outer walls including primary holes and dilution holes situated downstream from the primary holes in a gas flow direction, the primary and dilution holes being regularly distributed around the circumference of the inner and outer walls. The outer wall has a greater number of dilution holes than the inner wall.
1. An annular combustion chamber for a turbine engine, the chamber comprising:
an inner wall and an outer wall forming surfaces of revolution, the inner and outer walls being connected together by a chamber end wall fitted with a fuel injection device, each of the inner and outer walls including primary holes and dilution holes situated downstream from the primary holes in a gas flow direction, the primary and dilution holes being regularly distributed around a circumference of the inner and outer walls;
the chamber including n injectors and being subdivided into n angular sectors,
wherein in each angular sector, the outer wall includes a central dilution hole situated in a radial plane oriented along an axis of a corresponding injector of the injectors, two dilution half-holes situated at circumferential ends of the angular sector, and two other middle dilution holes situated on either side of the radial plane between the central hole and the end half-holes; and
wherein, in each angular sector, the inner wall includes a central dilution hole situated in the radial plane oriented along the axis of the corresponding injector, with two other dilution holes being situated on either side of the radial plane.
2. A combustion chamber according to claim 1 , wherein a diameter of the central dilution hole of each sector of the outer wall is greater than a diameter of the other dilution holes of the sector.
3. A combustion chamber according to claim 1 , wherein a diameter of the central hole in the sector of the outer wall is in a range of 6 mm to 7 mm, a diameter of the middle holes in the sector is in a range of 5 mm to 6 mm, and a diameter of the end half-holes is in a range of 4 mm to 5 mm.
4. A combustion chamber according to claim 1 , wherein a diameter of the central dilution hole in the sector of the inner wall is greater than a diameter of the other dilution holes in the sector.
5. A combustion chamber according to claim 4 , wherein a diameter of the central hole in the sector of the inner wall is in a range of 7 mm to 8 mm, and the diameter of the other dilution holes in the sector is in a range of 6 mm to 7 mm.
6. A combustion chamber according to claim 1 , wherein the dilution holes in a given wall are in alignment on a same circumference.
7. A turbine engine, an airplane turboprop, or a turbojet comprising a combustion chamber according to claim 1 .
8. A combustion chamber according to claim 1 , wherein in each angular sector, the outer wall includes the central dilution hole situated in the radial plane oriented along the axis of the corresponding injector, the two dilution half-holes situated at the circumferential ends of the angular sector, and only two of the other middle dilution holes situated on either side of the radial plane between the central hole and the end half-holes.
9. A combustion chamber according to claim 1 , wherein in each angular sector, the inner wall does not include any half-holes.
10. A combustion chamber according to claim 1 , wherein downstream ends of the central dilution hole and the two other middle dilution holes in the outer wall are in alignment on a same circumference.
11. A combustion chamber according to claim 1 , wherein all of the dilution holes in a given wall are in alignment on a same circumference.
12. A combustion chamber according to claim 1 , wherein in each angular sector, the inner wall includes two primary holes.
13. A combustion chamber according to claim 1 , wherein in each angular sector, the outer wall includes two primary holes.
14. A combustion chamber according to claim 1 , wherein the primary holes in a given wall are in alignment on a same circumference.