Engine for propelling an aircraft and aircraft having at least one engine and at least one hydrogen tank

Patent metadata

Field	Value
Publication number	US-9897041-B2
Application number	US-201414549730-A
Country	US
Kind code	B2
Filing date	Nov 21, 2014
Priority date	Nov 27, 2013
Publication date	Feb 20, 2018
Grant date	Feb 20, 2018

Abstract

An engine for propelling an aircraft includes an annular fuel cell arrangement having at least one fuel cell, at least one electric motor couplable to the fuel cell arrangement, at least one fan couplable to the electric motor and a cowling having an inlet and an outlet nozzle. The fuel cell arrangement is arranged inside the cowling, the at least one fan is arranged between the inlet and the fuel cell arrangement inside the cowling, the electric motor is operable under consumption of electric power delivered by the fuel cell arrangement and the at least one fan is designed to produce a thrust force by creating an accelerated airflow at the outlet nozzle. The engine is extremely efficient and comprises a distinct low noise.

First claim

The invention claimed is:

1. An engine for propelling an aircraft, comprising:
a fuel cell arrangement having at least one fuel cell unit;
at least one electric motor couplable to the fuel cell arrangement;
at least one first fan couplable to the at least one electric motor; and
an outermost cowling having an inlet and an outlet nozzle,
wherein the fuel cell arrangement is positioned at an inner surface of the outermost cowling, said inner surface of the outermost cowling defining a flow duct of the at least one first fan,
said fuel cell arrangement configured to receive a portion of an airflow generated by the at least one first fan in said flow duct,
wherein the at least one first fan is arranged between the inlet and the fuel cell arrangement inside the outermost cowling,
wherein the at least one electric motor is operable under consumption of electric power delivered by the fuel cell arrangement, and
wherein the at least one first fan is configured to produce a thrust force by creating an accelerated airflow at the outlet nozzle.

2. The engine of claim 1 , wherein the fuel cell arrangement comprises a plurality of fuel cell units arranged annularly within the outermost cowling.

3. The engine of claim 2 , wherein the at least one electric motor comprises a plurality of coils fixedly arranged inside the outermost cowling and a plurality of magnets mechanically coupled with the at least one first fan.

4. The engine of claim 3 , wherein each coil of the plurality of coils is coupled with at least one electrical inverter,
wherein the at least one electrical inverter is coupled with the fuel cell arrangement and is controllable by a control unit.

5. The engine of claim 4 , wherein the at least one electrical inverter is arranged in an annular arrangement between the inlet and the fuel cell arrangement.

6. The engine of claim 4 , wherein the fuel cell arrangement comprises the plurality of fuel cell units being arranged annularly within the outermost cowling, and
wherein each fuel cell unit of the plurality of fuel cell units is coupled with the at least one electrical inverter.

7. The engine of claim 6 , wherein each fuel cell unit of the plurality of fuel cell units is mechanically and electrically coupled with the at least one electrical inverter without using an electric cable.

8. The engine of claim 3 , further comprising a magnetic bearing between the at least one first fan and the outermost cowling for rotatably supporting the at least one first fan, and
wherein the plurality of coils and the plurality of magnets provide the magnetic bearing.

9. The engine of claim 1 , further comprising a magnetic bearing between the at least one first fan and the outermost cowling for rotatably supporting the at least one first fan.

10. The engine of claim 1 , wherein the at least one fuel cell is one of a PEM (Proton Exchange Membrane) fuel cell and a closed cathode PEM fuel cell.

11. The engine of claim 1 , further comprising an exhaust gas recirculation outlet and a recirculation line,
wherein the recirculation line is connected with a fuel cell exhaust gas outlet and with the recirculation outlet, and
wherein the exhaust gas recirculation outlet is arranged upstream of the fuel cell arrangement.

12. The engine of claim 1 , further comprising a second fan, and a second electric motor,
wherein the at least one first and second fans are arranged one behind another in an axial direction and
wherein the at least one electric motor and the second electric motor are adapted for counter-rotating the at least first and second fans.

13. The engine of claim 1 , wherein the at least first fan is centerless.

14. The engine of claim 1 , further comprising a combustion engine.

15. The engine of claim 1 , wherein the outermost cowling encloses all active components of the at least one engine.

16. An aircraft, comprising at least one engine and at least one hydrogen tank for supplying the at least one engine with hydrogen, the at least one engine comprising:
a fuel cell arrangement having at least one fuel cell unit;
at least one electric motor couplable to the fuel cell arrangement;
at least one first fan couplable to the at least one electric motor; and
an outermost cowling having an inlet and an outlet nozzle,
wherein the fuel cell arrangement is positioned at an inner surface of the outermost cowling, said inner surface defining a flow duct of the at least one first fan,
said fuel cell arrangement configured to receive a portion of an airflow generated by the at least one first fan in said flow duct,
wherein the at least one first fan is arranged between the inlet and the fuel cell arrangement inside the outermost cowling,
wherein the at least one electric motor is operable under consumption of electric power delivered by the fuel cell arrangement, and
wherein the at least one first fan is configured to produce a thrust force by creating an accelerated airflow at the outlet nozzle.

Assignees

• Airbus Operations Gmbh
• Airbus Defence & Space Gmbh

Inventors

• Hoffjann Claus
• Wolff Christian

Classifications

• F02K7/08 Primary

  the jet being continuous · CPC title

• B64D27/355

  using fuel cells · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• F01D15/10 Primary

  Adaptations for driving, or combinations with, electric generators · CPC title