Turbomachine with angular air delivery

1. A turbomachine assembly comprising:

an annular compression section for compressing air passing through said turbomachine;

a turbomachine casing formed by an outer annular shell centered on a longitudinal axis (X-X) of the turbomachine and an inner annular shell secured coaxially inside the outer shell by a plurality of radial support arms;

an annular combustion section housed inside the turbomachine casing, disposed at the outlet from the compression section and within which the air coming from the compression section is mixed with fuel in order to be burnt therein; and

an annular turbine section disposed at the outlet from the combustion section and having a plurality of moving wheels that are driven in rotation by the gas coming from the combustion section, the air coming from the compression section presenting rotary motion with an angle of inclination relative to the longitudinal axis (X-X) of the turbomachine;

wherein each of the support arms presents an angle of inclination (α) relative to the longitudinal axis (X-X) of the turbomachine that is substantially equal to or greater than the angle of inclination of the air coming from the compression section so as to impart to the gas coming from the combustion section rotary motion with an angle of inclination that is substantially equal to or greater than the angle of inclination of the air coming from the compression section.

2. An assembly according to claim 1 , further comprising additional angular distribution means for determining air flow direction and formed at one or more of the following component elements of the turbomachine: a fairing of the combustion section; fuel injector systems of the combustion section; a transverse wall of the combustion section; and axial walls of the combustion section.

3. A turbomachine assembly comprising:

an annular compression section for compressing air passing through said turbomachine;

a turbomachine casing formed by an outer annular shell centered on a longitudinal axis (X-X) of the turbomachine and an inner annular shell secured coaxially inside the outer shell by a plurality of radial support arms;

an annular combustion section housed inside the turbomachine casing, disposed at the outlet from the compression section and within which the air coming from the compression section is mixed with fuel in order to be burnt therein; and

an annular turbine section disposed at the outlet from the combustion section and having a plurality of moving wheels that are driven in rotation by the gas coming from the combustion section, the air coming from the compression section presenting rotary motion with an angle of inclination relative to the longitudinal axis (X-X) of the turbomachine;

said turbomachine assembly further comprising wherein each of the support arms presents an angle of inclination (α) relative to the longitudinal axis (X-X) of the turbomachine that is substantially equal to or greater than the angle of inclination of the air coming from the compression section so as to impart to the gas coming from the combustion section rotary motion with an angle of inclination that is substantially equal to or greater than the angle of inclination of the air coming from the compression section;

additional angular distribution means for determining air flow direction and formed at one or more of the following component elements of the turbomachine: a fairing of the combustion section; fuel injector systems of the combustion section; a transverse wall of the combustion section; and axial walls of the combustion section,

wherein the additional angular distribution means are formed at the fairing of the combustion section, the combustion section being formed by an outer annular wall centered on the longitudinal axis (X-X) of the turbomachine, an inner annular wall coaxial with the outer wall, a transverse wall interconnecting the upstream ends of the outer and inner walls, a plurality of fuel injector systems passing through the transverse wall, and an annular fairing mounted on said transverse wall, said fairing having a plurality of openings for passing the fuel injector systems, the assembly being characterized in that each opening in the fairing has an axial wall forming an angle of inclination (β) relative to the longitudinal axis (X-X) of the turbomachine that is substantially equal to or greater than the angle of inclination of the air coming from the compression section.

4. An assembly according to claim 3 , in which the additional angular distribution means are formed at the fuel injector systems of the combustion section, each of said fuel injector systems comprising a fuel injector nozzle having one end mounted on a bowl provided with radial air swirlers, the assembly being characterized in that the air swirlers of each bowl present varying permeability to the air.

5. An assembly according to claim 4 , wherein the spacing between the air swirlers of each bowl varies depending on the inclination of the air coming from the combustion section.

6. An assembly according to claim 3 , wherein the additional angular distribution means are formed at the fuel injector systems of the combustion section, and wherein each of said fuel injector systems presents an angle of inclination (γ) relative to the longitudinal axis (X-X) of the turbomachine that is substantially equal to or greater than the angle of inclination of the air coming from the compression section.

7. An assembly according to claim 3 , wherein the additional angular distribution means are formed at the transverse wall of the combustion section, said combustion section being formed by an outer annular wall centered on the longitudinal axis (X-X) of the turbomachine, an inner annular wall coaxial with the outer wall, a transverse wall interconnecting the upstream ends of the inner and outer walls, and a plurality of fuel injector systems passing through the transverse wall, the assembly being characterized in that and wherein said transverse wall presents at each fuel injector system an angle of inclination (δ) relative to a transverse plane (P) of the turbomachine.

8. An assembly according to claim 7 , wherein the additional angular distribution means are formed at the axial walls of the combustion section, said axial walls of the combustion section being provided with a plurality of orifices aligned in rows and forming channels for passing air, wherein the rows of air-passing orifices present an angle of inclination (ε) relative to the longitudinal axis (X-X) of the turbomachine that is substantially equal to or greater than the angle of inclination of the air coming from the compression section.

9. An assembly according to claim 8 , wherein each channel presents an angle of inclination (θ 1 ) relative to an axis (Z-Z) perpendicular to axial walls of the combustion section.

10. An assembly according to claim 9 , wherein each channel is situated in a plane perpendicular to the axial walls of the combustion section presenting an angle of inclination (θ 2 ) relative to the longitudinal axis (X-X) of the turbomachine that is substantially equal to the angle of inclination (ε) of the rows of orifices.

11. A turbomachine according to claim 9 , wherein each channel is situated in a plane perpendicular to the axial walls of the combustion section presenting an angle of inclination (θ 2 ′) relative to the longitudinal axis (X-X) of the turbomachine that is substantially greater than the angle of inclination (ε) of the rows of orifices.

12. A turbomachine according to claim 11 , wherein the angle of inclination (θ 2 ′) of the plane perpendicular to the axial walls of the combustion section in which the channels are situated lies in the range ε to ε+90° relative to the longitudinal axis (X-X) of the turbomachine.

13. A turbomachine including an assembly according to claim 3 .