Injection system for a turbine engine annular combustion chamber
An injection system for a turbine engine annular combustion chamber includes a support configured to support and to center a fuel injector head. The support includes a frustoconical surface connected at its downstream end of smallest diameter to an upstream end of a cylindrical surface. The system further includes a bowl configured to mix air and fuel arranged downstream of the support and at least one axial swirl inducer extending at least in part around the support. Each swirl inducer includes vanes delimiting between them substantially axial channels for the passage of an air flow. The channels open at their upstream ends on said frustoconical surface.
1. An injection system for an annular combustion chamber of a turbine engine, comprising:
a support configured to support and to center a fuel injector head, the support comprising a frustoconical surface and a cylindrical surface, said frustoconical surface having a downstream end of smallest diameter which is connected to an upstream end of said cylindrical surface, said cylindrical surface being configured to cooperate by sliding with said fuel injector head,
a mixing bowl configured to mix air and fuel, said mixing bowl being arranged downstream of the support, and
a first swirl inducer extending at least in part around the support, said first swirl inducer comprising first vanes delimiting therebetween first substantially axial channels configured for a first passage of a first air flow,
a second swirl inducer extending at least in part around said first swirl inducer, said second swirl inducer comprising second vanes delimiting therebetween second substantially axial channels configured for a second passage of a second air flow,
wherein upstream ends of said first and second substantially axial channels open on said frustoconical surface which has a simile cone angle.
2. The injection system according to claim 1 , wherein said first and second vanes extend to said frustoconical surface and partially define said frustoconical surface.
3. The injection system according to claim 2 , wherein said first and second vanes have bevelled upstream ends, said bevelled upstream ends and said frustoconical surface having said single cone angle.
4. The injection system according to claim 1 , wherein said frustoconical surface comprises at least one annular row of orifices configured to supply the first and second air flows to said first and second substantially axial channels, respectively.
5. The injection system according to claim 1 , wherein said first and second vanes are axially recessed with respect to said frustoconical surface.
6. The injection system according to claim 5 , wherein said frustoconical surface comprises at least one annular opening configured to supply the first and second air flows to said first and second substantially axial channels, respectively.
7. The injection system according to claim 1 , wherein said first and second vanes are interrupted and each of said first and second vanes comprises at least two vane portions arranged axially from upstream to downstream.
8. The infection system according to claim 1 , wherein each of said first and second swirl inducers is defined between an inner cylindrical wall and an outer cylindrical wall.
9. The injection system according to claim 8 , wherein each of said cylindrical outer walls of said first and second swirl inducers comprises an annular row of through apertures configured to supply the air to said first and second swirl inducers, respectively.
10. The injection system according to claim 8 , wherein each of said cylindrical inner and outer walls comprises bevelled upstream ends, said bevelled upstream ends and said frustoconical surface having said single cone angle.
11. The infection system according to claim 1 , wherein said frustoconical surface is interrupted by a notch configured to receive said fuel injector head.
12. The injection system according to claim 1 , wherein said frustoconical surface has an upstream end of largest diameter which is connected to a cone, said cone and said frustoconical surface having said single cone angle.
13. A turbine engine, comprising an annular combustion chamber equipped with at least one injection system, the at least one injection system comprising:
a support configured to support and to center a fuel injector head, the support comprising a frustoconical surface and a cylindrical surface, said frustoconical surface having a downstream end of smallest diameter which is connected to an upstream end of said cylindrical surface, said cylindrical surface being configured to cooperate by sliding with said fuel injector head,
a mixing bowl configured to mix air and fuel, said mixing bowl being arranged downstream of the support, and
a first swirl inducer extending at least in part around the support, said first swirl inducer comprising first vanes delimiting therebetween first substantially axial channels configured for a first passage of a first air flow,
a second swirl inducer extending at least in part around said first swirl inducer, said second swirl inducer comprising second vanes delimiting therebetween second substantially axial channels configured for a second passage of a second air flow,
wherein upstream ends of said first and second substantially axial channels open on said frustoconical surface which has a single cone angle.