US 11,913,350 B2
Injector for a high-pressure turbine
Jérôme Claude George Lemonnier, Moissy-Cramayel (FR); Franck Davy Boisnault, Moissy-Cramayel (FR); Nicolas Li Yen Kuhn, Moissy-Cramayel (FR); and Antoine Bruno Van Noort, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/767,314
Filed by Safran Aircraft Engines, Paris (FR)
PCT Filed Oct. 8, 2020, PCT No. PCT/FR2020/051769
§ 371(c)(1), (2) Date Apr. 7, 2022,
PCT Pub. No. WO2021/069838, PCT Pub. Date Apr. 15, 2021.
Claims priority of application No. 1911138 (FR), filed on Oct. 8, 2019.
Prior Publication US 2022/0364470 A1, Nov. 17, 2022
Int. Cl. F01D 5/08 (2006.01); F02C 7/18 (2006.01); B22F 10/28 (2021.01)
CPC F01D 5/082 (2013.01) [B22F 10/28 (2021.01); F01D 5/081 (2013.01); F02C 7/18 (2013.01); F05D 2220/323 (2013.01); F05D 2260/20 (2013.01)] 8 Claims
OG exemplary drawing
 
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.