Hybrid emergency power unit system

Patent metadata

Field	Value
Publication number	US-9871260-B2
Application number	US-201414289365-A
Country	US
Kind code	B2
Filing date	May 28, 2014
Priority date	May 28, 2014
Publication date	Jan 16, 2018
Grant date	Jan 16, 2018

Abstract

An integrated hybrid emergency power system having various features is disclosed. A hybrid emergency power system may have an auxiliary power unit and an emergency power unit. The emergency power unit may have a fuel cell. The auxiliary power unit may have an engine. The emergency power unit may be connected to the auxiliary power unit by an emergency power unit efficiency improvement apparatus. In this manner, the operating efficiency of the emergency power unit may be enhanced.

First claim

The invention claimed is:

1. An integrated energy conversion system comprising:
an emergency power unit comprising a fuel cell having an electrical power output and a water waste output, wherein the electrical power output of the fuel cell is in electronic communication with an aircraft electrical bus; and
an emergency power unit efficiency improvement apparatus comprising a heat exchanger, a first tubing adapted to permit water to be conveyed from the fuel cell to an auxiliary power unit, and a bypass valve, the heat exchanger in fluidic communication with the emergency power unit,
wherein a water waste output is configured to release the water from the fuel cell, the water waste output is in fluidic communication with the first tubing, a fluidic interconnection between the water waste output of the emergency power unit and the auxiliary power unit, wherein the fluidic interconnection is configured to inject the water into an inlet of a compressor of an engine of the auxiliary power unit;
wherein the heat exchanger is configured to heat compressed air and supply the compressed air to an inlet of the emergency power unit, wherein the compressed air is uncombusted, wherein the bypass valve is configured to selectively bypass the heat exchanger and connect directly to an oxygen input of the emergency power unit.

2. The integrated energy conversion system of claim 1 , wherein the emergency power unit efficiency improvement apparatus comprises:
wherein the bypass valve is configured to selectively convey the compressed air to the emergency power unit without warming.

3. The integrated energy conversion system of claim 2 , wherein the emergency power unit comprises:
a fuel input comprising an aperture interconnected with a pipe configured to convey fuel to the fuel cell;
the oxygen input comprising an aperture in fluidic communication with the emergency power unit efficiency improvement apparatus; and
a gas waste output configured to release gas waste from the fuel cell.

4. The integrated energy conversion system of claim 3 , wherein the emergency power unit efficiency improvement apparatus comprises:
wherein the heat exchanger comprises a first fluid path and a second fluid path,
whereby the first fluid path is configured to accept pressurized air from a bypass air output of the engine of the auxiliary power unit,
whereby the second fluid path is configured to accept waste received from a waste output of the engine of the auxiliary power unit.

5. The integrated energy conversion system of claim 4 , wherein the fuel cell is a hydrogen fuel cell.

6. An integrated energy conversion system comprising:
an emergency power unit comprising a fuel cell, wherein the fuel cell comprises an electrical power output, an oxygen input, and a water waste output, wherein the electrical power output of the fuel cell is in electronic communication with an aircraft electrical bus;
an auxiliary power unit comprising an engine and a generator, wherein the engine is configured to drive the generator to produce electrical power, wherein the engine comprises a bleed air output for pressurized air, wherein a water input of the auxiliary power unit is in fluid communication with the water waste output of the fuel cell, wherein an electrical power output of the auxiliary power unit is in electronic communication with the aircraft electrical bus; and
an emergency power unit efficiency improvement apparatus comprising a heat exchanger and a bypass valve, the heat exchanger in fluidic communication with the emergency power unit and the auxiliary power unit, wherein the heat exchanger is configured to conduct an exhaust stream leaving the engine from a waste output of the engine to an exhaust sink and warm the pressurized air entering the oxygen input of the fuel cell from the bleed air output of the engine, wherein the pressurized air is uncombusted,
wherein the bypass valve is configured to selectively bypass the heat exchanger and connect directly to the oxygen input;
wherein the emergency power unit efficiency improvement apparatus comprises a first tubing configured to convey water from the fuel cell to the engine, wherein the water waste output is in fluidic communication with the first tubing of the emergency power unit efficiency improvement apparatus, and wherein the first tubing is configured to convey the water from the emergency power unit to the auxiliary power unit and inject the water into an inlet of a compressor of the auxiliary power unit.

7. The integrated energy conversion system of claim 6 , wherein the engine comprises a gas turbine.

8. The integrated energy conversion system of claim 6 , wherein the fuel cell comprises a hydrogen fuel cell.

9. The integrated energy conversion system of claim 6 , wherein the integrated energy conversion system is installed in an aircraft.

10. The integrated energy conversion system of claim 6 , wherein the heat exchanger is configured to selectively warm compressed air and convey the compressed air from the engine to the fuel cell.

11. The integrated energy conversion system of claim 10 , wherein the fuel cell comprises:
a fuel input comprising an aperture configured to interconnect with a pipe, wherein the pipe is configured to convey fuel from a fuel supply to the fuel cell;
the oxygen input comprising an aperture in fluidic communication with the emergency power unit efficiency improvement apparatus;
a gas waste output in fluidic communication with a waste gas sink.

12. The integrated energy conversion system of claim 11 , wherein the waste gas sink comprises a fire extinguishing system.

13. The integrated energy conversion system of claim 11 , wherein the waste gas sink comprises a fuel tank inerting system.

14. The integrated energy conversion system of claim 11 , wherein the auxiliary power unit comprises:
a gas turbine; and
an electrical generator,
wherein the gas turbine drives the electrical generator, and
wherein the generator is connected to the electrical power output of the auxiliary power unit and connected to the aircraft electrical bus.

15. The integrated energy conversion system of claim 14 , wherein the emergency power unit efficiency improvement apparatus comprises:
the heat exchanger comprising a first fluid path and a second fluid path,
wherein the first fluid path is configured to accept the pressurized air from the bleed air output of the gas turbine,
wherein the second fluid path is configured to accept waste received from a waste output of the gas turbine, and
wherein the pressurized air is configured to warm in response to the waste and conveyed to the oxygen input of the fuel cell of the emergency power unit.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Ribarov Lubomir A
• Veilleux Jr Leo J

Classifications

• H01M8/04201

  Reactant storage and supply, e.g. means for feeding, pipes · CPC title

• H01M8/04156

  with product water removal · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• H02J9/066

  characterised by the use of dynamo-electric machines (H02J9/08 takes precedence) · CPC title

• H01M8/04067 Primary

  Heat exchange or temperature measuring elements, thermal insulation, e.g. heat pipes, heat pumps, fins · CPC title