Propulsion and electrical system for an aircraft including a fuel cell and a turbine engine

Abstract

A propulsion and electrical system for an aircraft including a turbine engine, a bleed air valve assembly, and a fuel cell. The turbine engine includes a compressor to generate compressed air containing oxygen. A portion of the compressed air is bleed air containing oxygen. The bleed air valve assembly is fluidly coupled to the compressor to receive the bleed air. The bleed air valve assembly is positionable to regulate the bleed air to generate pressurized air containing oxygen. The fuel cell is fluidly coupled to a hydrogen source to receive hydrogen and fluidly coupled to the compressor via the bleed air valve to receive the pressurized air containing oxygen. The fuel cell generates electricity when receiving the hydrogen and the pressurized air.

Dependencies are inferred from the claim text.