Patent ID: 11913350
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B  Y | IPC B  F

Claim 0:
1. A turbine injector comprising an annular ring extending about a longitudinal axis and having a radially external rim and a radially internal rim, wherein the ring has at least two channels intended to fluidly connect the radially external rim to the radially internal rim, each channel extending in a radial plane of the ring and having an inlet opening in the vicinity of the external rim and an outlet opening in the vicinity of the radially internal rim, each channel presenting a gradual variation in the orientation of the channel according to a tangential component between an inlet section of the inlet opening and an outlet section of the outlet opening, wherein each inlet section has substantially the shape of a parallelogram surmounted by a triangle or the shape of a triangle and wherein the injector is obtained by additive manufacturing.