Drive system for an aircraft, aircraft having a drive system and method for operating an aircraft

Patent metadata

Field	Value
Publication number	US-12320302-B2
Application number	US-202318484827-A
Country	US
Kind code	B2
Filing date	Oct 11, 2023
Priority date	Oct 13, 2022
Publication date	Jun 3, 2025
Grant date	Jun 3, 2025

Abstract

A drive system for an aircraft which is constructed for operation with a liquid fuel and a gaseous fuel, includes: at least one engine having a combustion chamber for operation with the liquid fuel and/or the gaseous fuel; and per fuel at least one separate tank chamber which is or can be brought into connection in flow terms with the combustion chamber via a fuel line for supplying it with the corresponding fuel. A drive system which is optimized in terms of emissions and efficiency is provided in that the drive system is constructed in such a manner that, in the event of firing at a great height, exclusively gaseous fuel is or can be used in the at least one engine during a firing operation at a great height.

First claim

The invention claimed is:

1. A drive system for an aircraft that is constructed for operation with a liquid fuel and a gaseous fuel, comprising:
at least one engine having at least one combustion chamber for operation with the liquid fuel and/or the gaseous fuel and
for each of the liquid fuel and the gaseous fuel, at least one separate tank chamber which is flowingly connectable with the at least one combustion chamber via a respective fuel line for supplying the at least one combustion chamber with the respective fuel,
 wherein the drive system is constructed such that, in the event of firing at a great height, exclusively gaseous fuel is used in the at least one combustion chamber during a firing operation at a great height;
 at least one additional tank chamber configured for storing at least a minimum quantity of the gaseous fuel to be used exclusively during the firing operation at the great height;
 an additional fuel line separate from the respective fuel lines and connecting the at least one additional tank chamber to the at least one combustion chamber;
 an additional valve configured and positioned to selectively control flow of the gaseous fuel from the at least one additional tank chamber to the at least one combustion chamber;
 wherein the drive system is configured:
to operate with a kerosene-based fuel or a kerosene-like fuel as the liquid fuel; and
to operate with hydrogen or methane or a gas admixture which has at least one of hydrogen and/or methane as the gaseous fuel;

 wherein a combustion chamber volume inside the at least one combustion chamber is configured for the firing operation at the great height with the gaseous fuel, and
 wherein the combustion chamber volume is constructed to be at least 10% smaller, than with a configuration of an equivalent engine for the firing operation at the great height with the liquid fuel;
 wherein the gaseous fuel supplied for the firing at great height comes from the at least one additional tank chamber.

2. The drive system according to claim 1 ,
wherein the at least one additional tank chamber includes an additional tank chamber per each of the at least one engine.

3. The drive system according to claim 1 ,
wherein the at least one additional tank chamber is arranged on the respective each of the at least one engine to which the minimum quantity is supplied.

4. The drive system according to claim 1 ,
wherein the at least one additional tank chamber is constructed in a pressure-resistant additional tank container.

5. The drive system according to claim 4 ,
wherein the additional tank container:
is constructed to comprise metal, or
is constructed to comprise a plastic material.

6. The drive system according to claim 1 ,
wherein a volume of the at least one additional tank chamber is sufficient to contain a quantity of the gaseous fuel sufficient to carry out at least one firing operation at the great height in the at least one engine.

7. An aircraft including the drive system according to claim 1 .

8. The drive system according to claim 1 ,
wherein the combustion chamber volume is constructed to be at least 20% smaller than with the configuration of the equivalent engine for the firing at the great height with the liquid fuel.

9. The drive system according to claim 1 ,
wherein the combustion chamber volume is constructed to be at least 30% smaller than with the configuration of the equivalent engine for the firing at the great height with the liquid fuel.

10. The drive system according to claim 1 ,
wherein the combustion chamber volume is constructed to be up to 50% smaller than with the configuration of the equivalent engine for the firing at the great height with the liquid fuel.

11. A method for operating an aircraft, comprising:
providing a drive system for an aircraft that is constructed for operation with a liquid fuel and a gaseous fuel, comprising:
at least one engine having at least one combustion chamber for operation with the liquid fuel and/or the gaseous fuel and
for each of the liquid fuel and the gaseous fuel, at least one separate tank chamber which is flowingly connectable with the at least one combustion chamber via a respective fuel line for supplying the at least one combustion chamber with the respective fuel,
wherein the drive system is constructed such that, in the event of firing at a great height, exclusively gaseous fuel is used in the at least one combustion chamber during a firing operation at a great height;
at least one additional tank chamber configured for storing at least a minimum quantity of gaseous fuel to be used exclusively during the firing operation at great height;
an additional fuel line separate from the respective fuel lines and connecting the at least one additional tank chamber to the at least one combustion chamber;
an additional valve configured and positioned to selectively control flow of the gaseous fuel from the at least one additional tank chamber to the at least one combustion chamber;

supplying the at least one combustion chamber, alternatively or simultaneously with the liquid fuel and the gaseous fuel, via a fuel line from the respective at least one separate tank chambers,
wherein in the event of the firing at the great height, using exclusively gaseous fuel in the at least one engine during the firing operation at the great height;
operating the drive system with a kerosene-based fuel or a kerosene-like fuel as the liquid fuel; and
operating the drive system with hydrogen or methane or a gas admixture which has at least one of hydrogen and/or methane as the gaseous fuel;
providing that a combustion chamber volume inside the at least one combustion chamber is configured for the firing operation at the great height with the gaseous fuel, and
providing that the combustion chamber volume is constructed to be at least 10% smaller, than with a configuration of an equivalent engine for the firing operation at the great height with the liquid fuel;
supplying the gaseous fuel for the firing at great height from the at least one additional tank chamber.

12. The method as claimed in claim 11 ,
wherein a minimum quantity, which is stored in the drive system, of gaseous fuel is used for the firing operation at the great height.

13. The method as claimed in claim 11 ,
wherein in the event of the firing at the great height, connecting the additional fuel line with the additional valve, via which a partial minimum quantity of gaseous fuel as required for the firing operation at the great height is directed out of the at least one additional tank chamber to the at least one combustion chamber, and throttling a pressure of the gaseous fuel via an interposed additional pressure reduction device to a pressure level which is necessary for the firing at the great height.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Clemen Carsten
• Dörr Thomas

Classifications

• F02C3/24

  the fuel or oxidant being liquid at standard temperature and pressure · CPC title

• F02C9/40

  specially adapted to the use of a special fuel or a plurality of fuels · CPC title

• F02C3/22

  the fuel or oxidant being gaseous at standard temperature and pressure (F02C3/28 takes precedence) · CPC title

• F02C7/22

  Fuel supply systems · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title