Architecture for an electric power generator for aviation
AssigneeThe Boeing Company
InventorsJeremiah Vannest, Lijun Gao, Julia Zhang, Shengyi Liu
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Abstract
A system, apparatus, and/or method for an aircraft that provides a novel independent-speed variable-frequency generator for aviation power generation. The generator architecture utilizes a 2-stage generator architecture with a wound rotor PM exciter (PME) that provides excitation to the rotor of a generator. A rotating bi-directional AC/DC/AC electric power converter connects the rotor windings of the exciter and the generator.
Claims20
An electric power generator for an aircraft, comprising:
- a two-stage variable-frequency generator including a main generator, a permanent magnet exciter, a rotating bi-directional AC/DC/AC electric power converter system, and a controller;
- wherein the rotating bi-directional AC/DC/AC electric power converter system is coupled to a rotatable shaft;
- wherein the rotating bi-directional AC/DC/AC electric power converter system includes a first rotating bi-directional electric power converter for AC/DC conversion and a second rotating bi-directional electric power converter for DC/AC conversion;
- wherein the first rotating bi-directional electric power converter and the second rotating bi-directional electric power converter are disposed adjacent to one another along the rotatable shaft;
- and
- wherein the first rotating bi-directional electric power converter is electrically coupled to the second rotating bi-directional electric power converter via a DC power link.
An electric power generator for an aircraft, comprising:
- a two-stage variable-frequency generator including a main generator and a permanent magnet exciter, a controllable rectifier, and a controller;
- wherein the permanent magnet exciter includes a first rotor winding that is coupled to a rotatable shaft;
- wherein a first rotating bi-directional electric power converter and a second rotating bi-directional electric power converter are disposed adjacent to one another along the rotatable shaft;
- wherein the controllable rectifier is arranged to rectify electric power between the first rotor winding of the permanent magnet exciter and a field winding of the main generator;
- and
- wherein the controller regulates a stator output voltage of the main generator according to a control law.
A system for electric power generation in an aircraft, comprising:
- an electric power generator having a rotatable shaft coupled to an engine, and a controller;
- the electric power generator including a two-stage variable-frequency generator including a main generator, a permanent magnet exciter, a rotating bi-directional AC/DC/AC electric power converter system;
- wherein the rotating bi-directional AC/DC/AC electric power converter system is coupled to the rotatable shaft;
- wherein the rotating bi-directional AC/DC/AC electric power converter system includes a first rotating bi-directional electric power converter for AC/DC conversion and a second rotating bi-directional electric power converter for DC/AC conversion;
- and
- wherein the first rotating bi-directional electric power converter and the second rotating bi-directional electric power converter are disposed adjacent to one another along the rotatable shaft.
Dependencies are inferred from the claim text.