US 2026/0285497 A1 · ELECTRICAL ASSEMBLY FOR A HYBRID-ELECTRIC AIRCRAFT PROPULSION SYSTEM

Abstract

A hybrid-electric aircraft propulsion system includes a gas turbine engine, an electrical assembly, and a gear train. The gas turbine engine includes a first rotational assembly rotatable about a rotational axis of the gas turbine engine. The electrical assembly includes a plurality of electric machines. The plurality of electric machines includes a first electric machine and a second electric machine. The gear train includes a first shaft, a second shaft, a third shaft, a first gear, a second gear, and a transmission assembly. The first shaft couples the first electric machine with the first rotational assembly. The second shaft is coupled with the second electric machine. The second shaft is selectively coupled with the third shaft by the transmission assembly. The first gear is mounted on the first shaft. The second gear is mounted on the third shaft and engaged with the first gear.

Claims20

Dependent claims

A hybrid-electric aircraft propulsion system comprising:

a gas turbine engine comprising a first rotational assembly rotatable about a rotational axis of the gas turbine engine;
an electrical assembly comprising a plurality of electric machines, the plurality of electric machines comprising a first electric machine and a second electric machine;
and
a gear train comprising a first shaft, a second shaft, a third shaft, a first gear, a second gear, and a transmission assembly, the first shaft coupling the first electric machine with the first rotational assembly, the second shaft being coupled with the second electric machine, the second shaft being selectively coupled with the third shaft by the transmission assembly, the first gear being mounted on the first shaft, the second gear being mounted on the third shaft and engaged with the first gear.

1 more element

A method for executing an engine start sequence for a gas turbine engine of a hybrid-electric aircraft propulsion system, the method comprising:

applying a first rotation force and a second rotational force to a first rotational assembly of the gas turbine engine with a first electric machine and a second electric machine, respectively, the first electric machine being coupled with the first rotational assembly by a first shaft, the second electric machine being coupled with the first rotational assembly by a second shaft, a third shaft, a first gear, a second gear, and a transmission assembly, the second shaft being coupled with the second electric machine, the transmission assembly coupling the second shaft and the third shaft, the first gear being mounted on the first shaft, the second gear being mounted on the third shaft and engaged with the first gear;
stopping applying the second rotational force to the first rotational assembly with the second electric machine at a first rotation speed of the first rotational assembly;
stopping applying the first rotational force to the first rotational assembly with the first electric machine at a second rotation speed of the first rotational assembly, the second rotation speed being greater than the first rotation speed.

Dependencies are inferred from the claim text.

Electrical assembly for a hybrid-electric aircraft propulsion system

Life of this patent

Electrical assembly for a hybrid-electric aircraft propulsion system

Life of this patent

Abstract

Claims20