Aircraft with electric propulsor

A propulsor adapted to produce thrust for use in an aircraft, the propulsor comprising

• an electric motor configured to convert electrical power to mechanical rotation,
• a fan unit including a nacelle structure and a fan rotor coupled to the electric motor to be rotationally driven by the electric motor about a central axis relative to the nacelle structure, the nacelle structure including a hub arranged along the central axis, a fan case arranged around the fan rotor and the central axis, and a plurality of guide vanes that extend from the hub to the fan case aft of the fan rotor so that all accelerated air discharged from the fan rotor interacts with the guide vanes as all the accelerated air moves through the nacelle structure, and
• a thrust control system coupled to the nacelle structure and located immediately aft of guide vanes so that the thrust control system is the next structure movable relative to the nacelle structure that interacts with all the accelerated air as it the air leaves the nacelle structure, the thrust control system being configured to provide a variable area nozzle and thrust reverser,
• wherein the thrust control system includes a first flap mounted to rotate about a first-flap axis and a rotation actuator coupled to the first flap to drive movement of the first flap about the first-flap axis,
• wherein the thrust control system includes a second flap mounted to rotate about a second-flap axis and the rotation actuator is configured to drive movement of the second flap about the second flap axis, and
• wherein the first flap and the second flap are each mounted to slide along the central axis relative to the nacelle structure from a first position abutting an aft end of the fan case to a second position spaced apart from the aft end of the fan case.

A propulsor comprising

• a fan unit including a nacelle structure and a fan rotor configured to be rotationally driven by an electric motor about a central axis relative to the nacelle structure, the nacelle structure including a hub arranged along the central axis, a fan case arranged around the fan rotor and the central axis, and guide vanes that extend from the hub to the fan case aft of the fan rotor so that all accelerated air discharged from the fan rotor interacts with the guide vanes as all the accelerated air moves through the nacelle structure, and
• a thrust control system coupled to the nacelle structure and located immediately aft of the guide vanes so that the thrust control system is the next structure movable relative to the nacelle structure that interacts with all the accelerated air as the air leaves the nacelle structure, wherein the thrust control system includes a first flap mounted to rotate about a first-flap axis and a second flap mounted to rotate about a second-flap axis, and the first flap and the second flap are selectively movable from a first configuration defining a first area through which all the accelerated air passes as the air leaves the propulsor to a second configuration defining a second area through which all the accelerated air passes as it leaves the propulsor, and wherein the first flap and the second flap are each mounted to slide along the central axis relative to the nacelle structure from a first position abutting an aft end of the fan case to a second position spaced apart from the aft end of the fan case.

An aircraft comprising

• an airframe,
• an electric motor, and
• a propulsor including a fan unit configured to provide accelerated air and a thrust control system configured to provide a variable area nozzle and thrust reverser that interacts with accelerated air from the fan unit,
• wherein the fan unit includes a nacelle structure and a fan rotor coupled to the electric motor for rotation about a central axis relative to the nacelle structure,
• wherein the nacelle structure includes a hub arranged along the central axis, a fan case arranged around the fan rotor and the central axis, and guide vanes that extend from the hub to the fan case aft of the fan rotor so that all accelerated air discharged from the fan rotor interacts with the guide vanes as all the accelerated air moves through the nacelle structure, and
• wherein the thrust control system is coupled to the nacelle structure and located immediately aft of the guide vanes so that the thrust control system is the next structure movable relative to the nacelle structure that interacts with all the accelerated air as it the air leaves the nacelle structure,
• wherein the thrust control system includes a first flap mounted to rotate about a first-flap axis and a second flap mounted to rotate about a second-flap axis, and the first flap and the second flap are selectively movable from a first configuration defining a first area through which all the accelerated air as the air leaves the propulsor to a second configuration defining a second area through which all the accelerated air passes as the air leaves the propulsor, and
• wherein the first flap and the second flap are each mounted to slide along the central axis relative to the nacelle structure from a first position abutting an aft end the fan case to a second position spaced apart from the aft end of the fan case.