Hydrogen fuel system for aircraft

Patent metadata

Field	Value
Publication number	US-2023339621-A1
Application number	US-202318305030-A
Country	US
Kind code	A1
Filing date	Apr 21, 2023
Priority date	Apr 22, 2022
Publication date	Oct 26, 2023
Grant date	—

Abstract

A hydrogen fuel system for an aircraft is configured to provide hydrogen fuel to the engines for propulsion. The fuel system also may provide hydrogen fuel to a fuel cell arrangement to generate electricity for use on the aircraft. The fuel cell arrangement may be selectively coupled to the feed lines for the engines. A ventilation system regulates the pressure within the one or more fuel tanks and the feed lines. The ventilation system can vent hydrogen vapor to atmosphere or can transfer hydrogen vapor between the fuel tanks and the fuel cell arrangement. A jet pump and accumulator may pull vapor from the feed lines as needed.

First claim

1 . A hydrogen fuel system for an aircraft, the hydrogen fuel system comprising:
a fuel tank configured to store hydrogen in a liquid state; a boost pump arrangement disposed within the fuel tank; an engine feeder sub-system including a feed line connecting the boost pump arrangement to a high pressure pump disposed at an engine of the aircraft, the high pressure pump directing fuel from the feed line to a first heat exchanger and then to a fuel injector, the first heat exchanger being configured to heat the hydrogen to a supercritical liquid state; and a fuel cell sub-system including a fuel cell arrangement and a second heat exchanger upstream of the fuel cell arrangement, the second heat exchanger being coupled to the feed line of the engine feeder sub-system, the second heat exchanger being configured to heat the hydrogen to a gaseous state.

2 . The hydrogen fuel system of claim 1 , wherein the boost pump arrangement includes three boost pumps.

3 . The hydrogen fuel system of claim 1 , wherein a flow meter unit is disposed between the high pressure pump and the first heat exchanger.

4 . The hydrogen fuel system of claim 1 , further comprising an accumulator disposed in parallel with the feed line via input and output lines, the accumulator being configured to store pressurized fuel.

5 . The hydrogen fuel system of claim 4 , further comprising a jet pump having a first input connected to the accumulator, a second input connected to the feed line, and an output connected to the fuel cell sub-system, the jet pump configured to suck hydrogen vapor from the feed line and to direct the sucked hydrogen vapor to the fuel cell sub-system.

6 . The hydrogen fuel system of any of claims 1 - 5 , wherein the fuel tank is a first fuel tank, the boost pump arrangement is a first boost pump arrangement, the feed line is a first feed line, the high pressure pump is a first high pressure pump, and the engine is a first engine; and wherein the hydrogen fuel system further comprises a second fuel tank, a second boost pump arrangement at the second fuel tank, and a second feed line extending from the second boost pump arrangement to a second high pressure tank at a second engine of the aircraft.

7 . The hydrogen fuel system of claim 6 , wherein the first engine is disposed at a first wing of the aircraft and the second engine is disposed at a second wing of the aircraft.

8 . The hydrogen fuel system of claim 6 , wherein the first and second fuel tanks are disposed at opposite sides of the fuel cell sub-system.

9 . The hydrogen fuel system of claim 6 , wherein the first and second feed lines are selectively isolated from each other at a crossfeed valve.

10 . The hydrogen fuel system of claim 6 , wherein the second heat exchanger of the fuel cell sub-system also being coupled to the second feed line.

11 . The hydrogen fuel system of claim 10 , further comprising a first shutoff valve configured to selectively isolate the second heat exchanger from the first feed line and a second shutoff valve configured to selectively isolate the second heat exchanger from the second feed line.

12 . The hydrogen fuel system of claim 1 , further comprising a ventilation sub-system including a ventilation line extending between a pressure regulator at the fuel tank and a port to atmosphere.

13 . The hydrogen fuel system of claim 12 , wherein the ventilation line extends between respective pressure regulators at the first and second fuel tanks and the port to atmosphere.

14 . The hydrogen fuel system of claim 1 , further comprising a tank pressurization line extending between the fuel tank and a fuel line of the fuel cell sub-system separate from the feed line, the tank pressurization line being in communication with hydrogen vapor within the fuel tank, the fuel line being disposed downstream of the second heat exchanger and upstream of the fuel cell arrangement.

15 . The hydrogen fuel system of claim 14 , wherein a first shutoff valve selectively isolates the first fuel tank from the fuel line and a second shutoff valve selectively isolates the second fuel tank from the fuel line.

16 . A hydrogen fuel system for an aircraft, the hydrogen fuel system comprising:
a fuel tank configured to store hydrogen in a liquid state; an engine feeder sub-system including a feed line connecting the fuel tank to a high pressure pump disposed at an engine of the aircraft, the high pressure pump directing fuel from the feed line to a first heat exchanger and then to a fuel injector, the first heat exchanger being configured to heat the hydrogen to a supercritical liquid state; an accumulator disposed in parallel with the feed line to store pressurized hydrogen obtained from the feed line, the accumulator being configured to selectively direct the pressurized hydrogen to the high pressure pump; and a jet pump having a first input coupled to the feed line, a second input coupled to the accumulator, and an output, the jet pump being configured to draw hydrogen vapor from the feed line via the first input when the accumulator directs pressurized hydrogen through the jet pump towards the output.

17 . The hydrogen fuel system of claim 16 , further comprising a fuel cell arrangement including a second heat exchanger and a stack of one or more fuel cells, wherein the output of the jet pump is directed to the fuel cell arrangement.

18 . The hydrogen fuel system of claim 16 or claim 17 , wherein the fuel tank is a first fuel tank, the feed line is a first feed line, the accumulator is a first accumulator, and the jet pump is a first jet pump; and wherein the hydrogen fuel system further comprises a second fuel tank, a second feed line, a second accumulator disposed in parallel with the second feed line, and a second jet pump having a first input coupled to the second feed line and a second input coupled to the second accumulator.

19 . A hydrogen fuel system for an aircraft, the hydrogen fuel system comprising:
a fuel tank configured to store hydrogen in a liquid state; a fuel cell sub-system including a fuel cell arrangement and a heat exchanger upstream of the fuel cell arrangement, the heat exchanger being coupled to the fuel tank via a feed line, the second heat exchanger being configured to heat the hydrogen obtained via the feed line to a gaseous state; a tank pressurization line separate from the feed line, the tank pressurization line extending between the fuel tank and a fuel cell line that is disposed downstream of the heat exchanger and upstream of the fuel cell arrangement; and a shutoff valve disposed along the tank pressurization line to selectively isolate the fuel tank from the fuel cell line.

20 . The hydrogen fuel system of claim 16 or claim 17 , wherein the fuel tank is a first fuel tank, the feed line is a first feed line, and the shutoff valve is a first shutoff valve; and wherein the hydrogen fuel system further comprises a second fuel tank to which the tank pressurization line extends, a second feed line extending between the second fuel tank and the heat exchanger, and a second shutoff valve disposed along the tank pressurization line to selectively isolate the second fuel tank from the fuel cell line, the second feed line being separate from the tank pressurization line.

Assignees

• Eaton Intelligent Power Ltd

Inventors

• Sarkar Subrata

Classifications

• B64D37/30 Primary

  Fuel systems for specific fuels · CPC title

• B64D37/04

  Arrangement thereof in or on aircraft · CPC title

• B64D37/18

  Conditioning fuel during filling · CPC title

• F04F5/36

  characterised by using specific inducing fluid · CPC title

• F04F5/44

  Component parts, details, or accessories not provided for in, or of interest apart from, groups F04F5/02 - F04F5/42 · CPC title