US 11,808,286 B2
Jet pump for a turbomachine, comprising blading for imparting rotation to active fluid
Philippe Vertenoeuil, Paris (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 16/095,559
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Apr. 25, 2017, PCT No. PCT/FR2017/050978
§ 371(c)(1), (2) Date Oct. 22, 2018,
PCT Pub. No. WO2017/187082, PCT Pub. Date Nov. 2, 2017.
Claims priority of application No. 16 53747 (FR), filed on Apr. 27, 2016.
Prior Publication US 2019/0107125 A1, Apr. 11, 2019
Int. Cl. F04F 5/46 (2006.01); F02C 7/236 (2006.01); F04F 5/10 (2006.01); F02M 37/02 (2006.01)
CPC F04F 5/463 (2013.01) [F02C 7/236 (2013.01); F02M 37/025 (2013.01); F04F 5/10 (2013.01); F05D 2260/601 (2013.01); Y02T 50/60 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A jet pump for a fluid supply system of a turbomachine, comprising:
an inlet;
a mixer; and
a diffuser at an outlet of the jet pump,
wherein the jet pump is delimited by an external tube extending along a longitudinal
axis of the jet pump, the external tube including a convergent portion at the inlet, a cylindrical intermediate portion at the mixer, and a divergent portion at the diffuser,
wherein the jet pump further comprises an internal tube disposed in and concentric with the external tube that is extending along the longitudinal axis, the internal tube extending along the longitudinal axis of the jet pump,
wherein the inlet includes
an active fluid inlet conduit comprising the internal tube extending along the longitudinal axis, the internal tube delimiting the active fluid inlet conduit, and a passive fluid inlet conduit, which is fluidly separated from the active fluid inlet conduit by the internal tube extending along the longitudinal axis,
wherein the active fluid inlet conduit comprises twisted vanes which are located inside the internal tube, wherein the twisted vanes are configured to rotatably drive an active fluid with respect to the longitudinal axis of the jet pump,
wherein each of the twisted vanes comprises a wall element which includes an inner side edge and an outer side edge, which is opposite to the inner side edge,
wherein the inner side edge of each of the twisted vanes being directly connected to each other, the inner side edge of each of the twisted vanes being substantially parallel to the longitudinal axis of the jet pump and extending in a center of the internal tube,
wherein a trailing edge of a first vane of the twisted vanes comprises, along a radial direction of the first vane, an inner portion of the trailing edge and an outer portion of the trailing edge,
wherein the inner portion of the trailing edge comprises a NACA type aerodynamic profile, and
wherein the outer portion of the trailing edge of the first vane comprises a substantially planar external surface which is substantially orthogonal to a side surface of the wall element, and
wherein a ratio of a length of the inner portion of the trailing edge of the first vane to a total length of the trailing edge of the first vane is between 50% and 80% of the total length of the trailing edge of the first vane.