US 7,380,749 B2 · Combined fuel cell aircraft auxiliary power unit and environmental control system

Abstract

Combined aircraft hybrid fuel cell auxiliary power unit and environmental control system and methods are disclosed. In one embodiment, an auxiliary power unit includes a fuel cell component which chemically converts combustible fuel into electrical energy. Unutilized fuel emitted by the fuel cell component is combusted by a burner to generate heated gas. The heated gas is received by and drives a turbine, which in turn drives a drive shaft. A compressor, coupled to the drive shaft, compresses a source of oxidizing gas for supplying compressed oxidizing gas to the fuel cell component and to an environmental control system. A heat exchanger controls the temperature of the pressurized air leaving the environmental control system to provide the cabin air supply. Finally, a generator is coupled to the drive shaft to be driven by the turbines to generate additional electrical energy.

Claims14

Dependent claims

A system for providing electrical power and a breathable airflow into a compartment, comprising:

a fuel cell component coupled to a fuel supply and to a first pressurized flow of air, the fuel cell component being configured to provide an electrical output and a combustible exhaust flow;
a burner coupled to receive the exhaust flow from the fuel cell component and disconnected from the fuel supply, the burner being configured to provide a hot gas outflow;
a turbine configured to be driven by the hot gas outflow from the burner;
and
at least one compressor mechanically driven by the turbine, the at least one compressor being configured to receive an inflow of air and to provide the first pressurized flow of air to the fuel cell component and to provide a second pressurized flow of air, the second pressurized flow of air being suitable to provide the breathable airflow into the compartment, wherein the at least one compressor includes a first compressor configured to provide the second pressurized flow of air, and a second compressor configured to provide the first pressurized flow of air to the fuel cell component.

2 more elements

An aerospace vehicle, comprising:

a fuselage having an interior compartment and a storage portion configured to store a fuel supply;
a lift producing surface operatively coupled to the fuselage;
at least one engine operatively coupled to the fuselage;
and
a hybrid system for providing an electrical output and a breathable airflow into the interior compartment, the system including:
a fuel cell component coupled to the fuel supply and to a first pressurized flow of air, the fuel cell component being configured to provide at least a portion of the electrical output and a combustible exhaust flow;
a burner coupled to receive the exhaust flow from the fuel cell component and disconnected from the fuel supply, the burner being configured to provide a hot gas outflow;
a turbine configured to be driven by the hot gas outflow from the burner;
and
at least one compressor mechanically driven by the turbine, the at least one compressor being configured to receive an inflow of air and to provide the first pressurized flow of air to the fuel cell component and to provide a second pressurized flow of air, the second pressurized flow of air being suitable to provide at least part of the breathable airflow into the interior compartment;
and
at least one heat exchanger configured to transfer heat from the hot gas outflow from the burner to the second pressurized flow of air.

9 more elements

Dependencies are inferred from the claim text.

Combined fuel cell aircraft auxiliary power unit and environmental control system

Life of this patent

Combined fuel cell aircraft auxiliary power unit and environmental control system

Life of this patent

Abstract

Claims14