Tail cone for a microjet rotary turbine engine
The invention relates to a rear casing for a turbine engine comprising a primary body generating a primary flow ( 10 ) to be ejected through a primary nozzle ( 6 ), said rear casing ( 7 ) being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbine engine, the path followed by the primary flow downstream from the primary nozzle ( 6 ). The tail cone is characterised in that it comprises a connection to a system for supplying a pressurised gas and at least one perforation ( 8 ) for injecting the pressurised gas through the perforation and into the primary flow. The casing preferably comprises at least one means for rotating same about the axis of rotation of the mobile elements of the primary body.
1. A bypass turbine engine having a longitudinal axis of rotation, said bypass turbine engine comprising:
a nacelle having a front part surrounding a fan rotatable around said longitudinal axis:
a bypass stream ejection nozzle located at a downstream end of said nacelle;
a primary stream ejection nozzle having a trailing edge located at a downstream end of a primary cowl;
a cylindrical bypass stream duct delimited between the nacelle and the primary cowl;
a tail cone equipped with a plurality of perforations distributed azimuth-wise on an external wall of the tail cone, the plurality of perforations located downstream of the trailing edge of said primary stream ejection nozzle; and
a cylindrical primary stream duct delimited between the primary cowl and the tail cone, wherein each perforation of the plurality of perforations in the tail cone is configured to jet compressed air into a primary stream downstream of said primary stream ejection nozzle; wherein said tail cone is rotatable around said longitudinal axis.
2. The bypass turbine engine of claim 1 that when in operation produces less noise than an otherwise identical engine that does not have a tail cone equipped with said plurality of perforations.
3. The bypass turbine engine of claim 1 , wherein the tail cone has between 2 and 8 perforations of the plurality of perforations evenly distributed about the circumference of the tail cone.
4. The bypass turbine engine of claim 1 , wherein each perforation of the plurality of perforations directs the compressed air outward at an angle of 20° to 90° with respect to the longitudinal axis.
5. The bypass turbine engine of claim 1 , wherein each perforation of the plurality of perforations directs the compressed air outward at an angle of 90° with respect to the longitudinal axis.
6. The bypass turbine engine of claim 1 , wherein the compressed air injected through each perforation of the plurality of perforations does not exceed 0.25% of a flow rate of the primary stream.
7. The bypass turbine engine of claim 1 , wherein the compressed air is injected through each perforation of the plurality of perforations at a speed that is at most sonic.
8. The bypass turbine engine of claim 1 , wherein the compressed air is injected at a constant pressure.
9. The bypass turbine engine of claim 1 , further comprising a primary spool enclosed within the primary cowl.
10. The bypass turbine engine of claim 1 , wherein the primary stream ejection nozzle comprises an upstream portion of the tail cone and a downstream portion of the primary cowl.
11. A bypass turbine engine having a longitudinal axis of rotation, said bypass turbine engine comprising:
a tail cone equipped with a plurality of perforations distributed azimuth-wise on an external wall of the tail cone, the plurality of perforations located downstream of a trailing edge of a primary stream ejection nozzle of the bypass turbine engine, and
wherein each perforation of the plurality of perforations is configured to jet compressed air outward at an angle of 90° with respect to the longitudinal axis, the compressed air bled from a compressor of said bypass turbine engine, wherein said tail cone is rotatable around said longitudinal axis.