Aircraft propulsion system air mover brake
AssigneePratt & Whitney Canada Corp.
InventorLouis-Philippe Larose
Life of this patent
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Abstract
A method of braking a rotational air mover portion of an aircraft propulsion system is provided. The method includes: using an electrical device to apply a torque to a propulsion unit driven by a propulsion system of an aircraft, the propulsion unit including a rotational air mover configured to provide thrust for propelling the aircraft, wherein the electrical device is configured to produce electrical energy during the process of applying the torque to the propulsion unit; controlling the electrical device to apply an amount of the torque that is sufficient to cause the rotational air mover to decelerate or to maintain the rotational air mover non-rotational; and directing the electrical energy produced by the electrical device to an aircraft component.
Claims18
A method of braking a rotational air mover portion of an aircraft propulsion system, the method comprising:
- using an electrical device to apply a torque to a propulsion unit, the propulsion unit driven by a hybrid electric propulsion (HEP) system of an aircraft, the HEP system including a thermal engine, the propulsion unit including the rotational air mover configured to provide thrust for propelling the aircraft, wherein the electrical device is configured to produce electrical energy during the process of applying the torque to the propulsion unit, wherein applying the torque to the propulsion unit is initiated when the thermal engine of the HEP system is shut off and the rotational air mover is rotating;
- controlling the electrical device to apply an amount of the torque that is sufficient to cause the rotational air mover to decelerate or to maintain the rotational air mover non-rotational;
- and
- directing the electrical energy produced by the electrical device to an aircraft component.
An aircraft propulsion system, comprising:
- a propulsion unit that includes a rotational air mover configured to provide thrust for propelling an aircraft;
- a hybrid electric propulsion (HEP) system that includes a thermal engine, the propulsion unit driven by the HEP system;
- an electrical device configured to apply a torque to the propulsion unit, and configured to produce electrical energy during the process of applying the torque to the propulsion unit, wherein the process of applying the torque to the propulsion unit is initiated when the thermal engine of the HEP system is shut off and the rotational air mover is rotating;
- and
- a system controller in communication with the electrical device and a non-transitory memory storing instructions, which instructions when executed cause the system controller to:
- control the electrical device to apply an amount of the torque that is sufficient to cause the rotational air mover to decelerate or to maintain the rotational air mover non-rotational;
- and
- direct the electrical energy produced by the electrical device to an aircraft component.
Dependencies are inferred from the claim text.