Fuel delivery system having a fuel oxygen reduction unit

Patent metadata

Field	Value
Publication number	US-11420763-B2
Application number	US-202016864441-A
Country	US
Kind code	B2
Filing date	May 1, 2020
Priority date	Nov 2, 2018
Publication date	Aug 23, 2022
Grant date	Aug 23, 2022

Abstract

A fuel system is provided for an aircraft having a fuel source. The fuel system includes a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path is in airflow communication with the fuel source.

First claim

What is claimed is:

1. A method of operating an aircraft fuel system, the aircraft fuel system comprising a fuel source, the method comprising:
using a fuel oxygen reduction unit, wherein using the fuel oxygen reduction unit comprises:
receiving, at a controller, data from a sensor, the data indicative of an operational parameter of the fuel oxygen reduction unit;
varying, via a control valve operably coupled to the controller, a ratio of (a) an amount of a first flow of gas provided from an air source to a stripping gas supply path of the fuel oxygen reduction unit to (b) an amount of a second flow of gas provided from the fuel source to the stripping gas supply path, wherein varying the ratio is commanded by the controller in response to the data indicative of an operational parameter of the fuel oxygen reduction unit being received by the controller;
receiving the amount of the first flow of gas and the second flow of gas into the stripping gas supply path of the fuel oxygen reduction unit;
reducing an oxygen content in liquid fuel from the fuel source; and
providing a reduced-oxygen content gas flow to the fuel source.

2. The method of claim 1 , wherein the operational parameter of the fuel oxygen reduction unit is a temperature of the flow of gas from the stripping gas supply path, a pressure of the flow of gas from the stripping gas supply path, a fuel content of the flow of gas from the stripping gas supply path, or a combination thereof.

3. The method of claim 1 , wherein providing the reduced-oxygen content gas flow to the fuel source comprises providing the reduced-oxygen content gas flow to an ullage of the fuel system.

4. The method of claim 1 , wherein the control valve is positioned at a juncture of (a) a first portion of the stripping gas supply path extending from the air source and (b) a second portion of the stripping gas supply path extending from the fuel source.

5. A fuel system for an aircraft, the fuel system comprising:
a fuel source;
a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path;
an air source separate from the fuel source, the stripping gas supply path in airflow communication with the air source and the fuel source;
a control valve in airflow communication with the stripping gas supply path;
a sensor positioned to sense data indicative of an operational parameter of the fuel oxygen reduction unit; and
a controller operably coupled to the control valve and the sensor, the controller configured to receive from the sensor the data indicative of the operational parameter of the fuel oxygen reduction unit and adjust the control valve to vary a ratio of (a) an amount of a first flow of gas provided from the air source to the stripping gas supply path to (b) an amount of a second flow of gas provided from the fuel source to the stripping gas supply path, the controller configured to perform the adjustment of the control valve to vary the ratio in response to the data received indicative of the operational parameter of the fuel oxygen reduction unit,
wherein the stripping gas return path is configured to be in fluid communication with the fuel source, and
wherein the liquid fuel supply path is fluidly connected to the fuel source, the fuel oxygen reduction unit being configured to receive a flow of liquid fuel from the fuel source.

6. The fuel system of claim 5 , wherein the air source comprises at least one of an air cycle machine, a gas turbine engine of the aircraft, or a device for collecting an ambient airflow.

7. The fuel system of claim 5 , wherein the stripping gas supply path comprises a first portion of the stripping gas supply path extending from the air source and a second portion of the stripping gas supply path extending from the fuel source, and wherein the control valve is positioned at a juncture where the first portion of the stripping gas supply path meets the second portion of the stripping gas supply path.

8. The fuel system of claim 5 , wherein the first flow of gas from the air source is provided at a first temperature and a first pressure, wherein the second flow of gas from the fuel source is provided at a second temperature and a second pressure, and wherein the first temperature is greater than the second temperature, the first pressure is greater than the second pressure, or both.

9. The fuel system of claim 5 , wherein the fuel oxygen reduction unit comprises:
a gas oxygen reduction unit positioned in the stripping gas supply path or the stripping gas return path, and wherein a fuel content within the second flow of gas from the fuel source assists with operation of the gas oxygen reduction unit.

10. The fuel system of claim 5 , wherein the fuel source comprises a fuel tank, wherein the fuel oxygen reduction unit further comprises:
an ullage pump in airflow communication with the stripping gas supply path.

11. The fuel system of claim 5 , wherein the fuel source comprises a fuel tank, and wherein the stripping gas return path is in airflow communication with an ullage of the fuel tank.

12. The fuel system of claim 5 , wherein the fuel source comprises a fuel tank, and wherein an ullage of the fuel tank is configured to provide an excess flow of gas to a location separate from the fuel oxygen reduction unit.

13. The fuel system of claim 5 , wherein the fuel oxygen reduction unit comprises:
a gas oxygen reduction unit positioned in the stripping gas supply path or the stripping gas return path; and
a fuel oxygen reduction assembly in fluid communication with the liquid fuel supply path and the liquid fuel outlet path, and further in airflow communication with the stripping gas supply path and stripping gas return path.

14. The fuel system of claim 13 , wherein the gas oxygen reduction unit is a first gas oxygen reduction unit positioned in the stripping gas supply path, and wherein the fuel oxygen reduction unit further comprises a second gas oxygen reduction unit in the stripping gas return path.

15. The fuel system of claim 13 , wherein the fuel oxygen reduction assembly comprises:
a contactor fluidly connected to the liquid fuel supply path and the stripping gas supply path for mixing a liquid fuel flow from the liquid fuel supply path with a stripping gas flow from the stripping gas supply path to form a fuel/gas mixture; and
a separator fluidly connected to the contactor for receiving the fuel/gas mixture and separating the fuel/gas mixture back into the stripping gas flow and the liquid fuel flow, the separator fluidly connected to the liquid fuel outlet path and the stripping gas return path for providing the liquid fuel flow to the liquid fuel outlet path and the stripping gas flow to the stripping gas return path.

16. The fuel system of claim 5 , wherein the sensor is positioned in the stripping gas supply path downstream of the control valve and upstream of the fuel oxygen reduction unit.

17. A propulsion system for an aircraft, comprising:
an aircraft engine; and
a fuel system comprising:
a fuel source;
a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path;
an air source separate from the fuel source, the stripping gas supply path in airflow communication with the air source for receiving a first flow of gas from the air source, the stripping gas supply path further in airflow communication with the fuel source for receiving a second flow of gas from the fuel source;
a control valve in airflow

Assignees

• Gen Electric

Inventors

• Niergarth Daniel Alan
• Miller Brandon Wayne

Classifications

• B64D37/10

  to facilitate fuel pressurisation · CPC title

• B64D37/34 Primary

  Conditioning fuel, e.g. heating (during filling B64D37/18) · CPC title

• F02C7/22

  Fuel supply systems · CPC title

• F23K5/08

  Preparation of fuel · CPC title

• B64D37/32

  Safety measures not otherwise provided for, e.g. preventing explosive conditions · CPC title