Aircraft braking method and ducted fan jet engine for implementing the method
AssigneeSnecma
InventorAlain Marie Joseph Lardellier
Life of this patent
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Abstract
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.
Claims15
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.
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.
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.
Dependencies are inferred from the claim text.