Ventilation of a turbomachine nacelle
View Patent ↗A jet pump type ejector for a turbomachine, including a duct through which a secondary ventilation air flow passes, and a first end of which forms an air intake and a second end of which forms an air outlet, the two nozzles for spraying a primary air flow being mounted in the duct which defines a mixer and a diffuser downstream from the nozzle, the two nozzles being parallel and adjacent to one another, the mixer including two substantially planar longitudinal walls, bottom and top respectively, connected to one another by two side walls having a semicircular cross-section, in which the radius of curvature R2 is centered on the axis of a nozzle, the center-to-center distance of the nozzles being substantially equal to Π/2 times R2 or (Π/2)R2.
1. An ejector of a jet pump type for a turbine engine, comprising a duct configured for a passage of a secondary ventilation air flow, a first end of said duct forming an air input and a second end of said duct forming an air output wherein two nozzles configured for spraying a primary air flow are mounted in the duct which defines a mixer and a diffuser downstream of the two nozzles, said two nozzles being parallel and next to one another, and wherein the mixer comprises two substantially planar longitudinal walls, lower and upper respectively, which are interconnected by two side walls having a semi-circular cross section and a bending radius R2, the bending radius R2 of each side wall being centered on an axis of one nozzle, a center-to-center distance of the two nozzles being substantially equal to (π/2)×R2.
2. The ejector according to claim 1 which has a length of between 10R2 and 16R2.
3. The ejector according to claim 1 , wherein the longitudinal walls are substantially parallel and have substantially the same dimensions.
4. A ventilation or pressurization system for the turbine engine which comprises at least one ejector according to claim 1 .
5. A turbine engine nacelle which comprises at least one ejector according to claim 1 .
6. The turbine engine nacelle according to claim 5 , wherein said first end of the duct forms the air input which is located in the turbine engine nacelle.
7. The turbine engine nacelle according to claim 5 , wherein the second end of the duct opens onto an outer surface of the turbine engine nacelle which is suitable for expelling air leaving the duct to the outside of the turbine engine.
8. The turbine engine nacelle according to claim 5 , which comprises an annular array of ejectors which are regularly distributed around a longitudinal axis of the turbine engine nacelle.
9. A turbine engine which comprises the turbine engine nacelle according to claim 5 , the nozzles being supplied with compressed air which is bled from a compressor of the turbine engine.
10. The turbine engine according to claim 9 , which is a turboprop engine having two unducted and contra-rotating propellers.