Aircraft braking method and ducted fan jet engine for implementing the method
View Patent ↗The braking method for an aircraft propelled by at least one ducted fan jet engine, the latter comprising a fan, a jet engine core in which the primary flow circulates, a secondary flow exhaust nozzle, encased in a nacelle, comprises the step, in low-power operation, of unloading at least part of the secondary flow so as to reduce the residual thrust of the jet engine without producing any thrust. With the method of the invention, aircraft braking can be achieved without any thrust reverser device using the braking force generated by the drag of the jet engine or engines completed by reduction of residual thrust by unloading the secondary flow.
1. A method for braking an aircraft propelled by at least one ducted fan jet engine, the jet engine comprising a fan, a jet engine core in which a primary flow circulates, and a secondary flow exhaust nozzle, encased by a nacelle, the method comprising:
positioning a blocking mechanism to obstruct a secondary flow in the secondary flow exhaust nozzle, the blocking mechanism being located directly downstream from a support member positioned downstream from a radial opening of the nacelle; and
unloading, in a low-power operation, at least part of the secondary flow through the radial opening by lifting a door that was blocking the radial opening to reduce a residual thrust of the jet engine without producing any thrust, wherein the radial opening is located downstream from an opening of a primary flow channel.
2. The braking method as in claim 1 , wherein an entirety of the secondary flow is unloaded so as to reduce the residual thrust of the jet engine to a sole thrust of the primary flow.
3. A ducted fan jet engine, comprising:
a fan;
a jet engine core configured to receive a primary flow from the fan via a primary flow channel;
a secondary flow exhaust nozzle configured to receive a secondary flow from the fan;
a door
a nacelle surrounding the secondary flow exhaust nozzle and including radial opening means positioned downstream from the primary flow channel and configured to enable unloading of part of the secondary flow, without producing any thrust, wherein the radial opening means includes at least one orifice that can be closed or opened by the door;
a support member positioned downstream from the radial opening means and extending between the nacelle and the jet engine core; and
obstruction means configured to obstruct the secondary flow exhaust nozzle and positioned directly downstream from the support member.
4. The ducted fan jet engine as in claim 3 , wherein, when the orifice is opened by the door, the door ensures an airbrake function.
5. The ducted fan jet engine as in claim 3 , wherein
the obstruction means comprise at least one profiled panel extending along a radial axis in the secondary flow exhaust nozzle, and
the at least one profiled panel is rotationally mounted about the radial axis.
6. The ducted fan jet engine as in claim 5 , wherein the profiled panel is profiled to guide, direct, and rectify the secondary flow in the secondary flow exhaust nozzle.
7. The ducted fan jet engine according to claim 5 , wherein the at least one profiled panel is configured to be rotated by a few degrees to reduce a section of the secondary flow exhaust nozzle.
8. The ducted fan jet engine as in claim 3 , wherein a bypass ratio of the jet engine is 10 or higher.
9. A ducted fan jet engine, comprising:
a fan configured to produce a primary air flow and a secondary air flow;
a jet engine core configured to receive the primary air flow via a primary flow channel;
a secondary flow exhaust nozzle configured to receive the secondary air flow;
a nacelle surrounding the secondary flow exhaust nozzle and including at least one radial opening positioned downstream from an entrance of the primary flow channel and configured to enable unloading of part of the secondary air flow;
a door configured to block the at least one radial opening in a first position and configured to be removed from the at least one radial opening in a second position;
a support member positioned downstream from the at least one radial opening and extending between the nacelle and the jet engine core; and
an obstruction mechanism configured to obstruct the secondary flow exhaust nozzle and positioned directly downstream from the support member.
10. The ducted fan jet engine according to claim 9 , wherein the obstruction mechanism includes a plurality of panels configured to rotate around a radial axis of the jet engine.
11. The ducted fan jet engine according to claim 10 , wherein, in an open position, at least one of the panels and the support member overlap and are parallel in a direction of the secondary air flow.
12. The ducted fan jet engine according to claim 10 , wherein the plurality of panels are configured to be rotated by a few degrees to reduce a section of the secondary flow exhaust nozzle.
13. The ducted fan jet engine according to claim 9 , wherein, in the second position, the door is completely removed from the at least one radial opening such that the door does not influence an air flow path of the secondary air flow exiting through the radial opening.
14. The ducted fan jet engine according to claim 9 , wherein, in the second position, the secondary air flow exiting through the at least one radial opening flows in a radial direction from a longitudinal axis of the jet engine.
15. The ducted fan jet engine according to claim 9 , wherein the at least one radial opening includes a first radial opening and a second radial opening diametrically opposed to the first radial opening.