METHOD AND KIT FOR PRESERVING A FUEL SYSTEM OF AN AIRCRAFT ENGINE

• US 20160349762A1
• Filed: 07/16/2015
• Published: 12/01/2016
• Est. Priority Date: 05/29/2015
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: GIRARD, Alain
• Granted Patent: US 10,287,909 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 25/00 Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• CPC Class Codes: F01D 25/002 Cleaning of turbomachines
• CPC Class Codes: F02B 77/04 Cleaning of, preventing corrosion or erosion in, or preventing unwanted deposits in, combustion engines cleaning of fuel injection apparatus F02M65/00
• CPC Class Codes: F02C 7/236 Fuel delivery systems comprising two or more pumps
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2230/72 Maintenance
• CPC Class Codes: F05D 2260/95 Preventing corrosion coating or surface treatment F05D2230/90

Abstract

A method and kit for preserving a fuel system of an aircraft engine outside of an engine test cell in preparation for a period of inactivity of the aircraft engine are disclosed. The method comprises: supplying preservation fluid to the fuel system of the aircraft engine; generating a signal to cause the opening of a valve of the fuel system using a control device other than the electronic engine controller of the aircraft engine; and driving a fuel pump of the fuel system to cause some of the preservation fluid to flow through the open valve and in at least part of the fuel system of the aircraft engine.

Claims

1. A method for preserving a fuel system of an aircraft engine outside of an engine test cell without powering an electronic engine controller of the aircraft engine in preparation for a period of inactivity of the aircraft engine, the method comprising:

supplying preservation fluid to the fuel system of the aircraft engine;

opening a valve of the fuel system using a control device, other than the electronic engine controller of the aircraft engine, coupled to the fuel system via a connector configured to provide an interface between the electronic engine controller of the aircraft engine and the fuel system of the aircraft engine; and

driving a fuel pump of the fuel system using a driver coupled to an accessory gearbox of the aircraft engine to cause some of the preservation fluid to flow through the open valve and in at least part of the fuel system of the aircraft engine.

2. The method as defined in claim 1, wherein the driver is coupled to an interface of the accessory gearbox configured for interfacing a starter of the aircraft engine to the accessory gearbox.

3. The method as defined in claim 2, comprising uncoupling the starter from the interface of the accessory gearbox and coupling the driver to the interface of the accessory gearbox.

4. The method as defined in claim 1, wherein the valve is a fuel metering valve of a hydro-mechanical metering unit of the fuel system.

5. The method as defined in claim 4, comprising using the control device to generate a signal to cause opening of the fuel metering valve.

6. The method as defined in claim 1, comprising uncoupling the electronic engine controller of the aircraft engine from the fuel system via the connector and coupling the control device to the fuel system via the connector.

7. The method as defined in claim 1, comprising using a bracket to facilitate coupling of the driver to the interface of the accessory gearbox.

8. The method as defined in claim 1, comprising:

uncoupling the control device from the fuel system via the connector;

uncoupling the driver from the accessory gearbox; and

closing the fuel system in preparation for the period of inactivity.

9. A kit for preserving a fuel system of an aircraft engine outside of an engine test cell without powering an engine electronic controller of the aircraft engine in preparation for a period of inactivity of the aircraft engine, the kit comprising:

a control device, other than the electronic engine controller of the aircraft engine, configured to;

be coupled to the fuel system via a connector configured to provide an interface between the electronic engine controller of the aircraft engine and the fuel system of the aircraft engine; and

cause a valve of the fuel system to open; and

a driver configured to be coupled to an accessory gearbox of the aircraft engine and drive a fuel pump of the fuel system via the accessory gearbox to cause some of the preservation fluid to flow in at least part of the fuel system of the aircraft engine.

10. The kit as defined in claim 9, wherein the driver comprises a motor of a handheld drill.

11. The kit as defined in claim 9, wherein the control device comprises a battery.

12. The kit as defined in claim 9, wherein the control device comprises a handheld unit including a 9-volt battery.

13. The kit as defined in claim 9, comprising a bracket to facilitate coupling of the driver to the accessory gearbox.

14. The kit as defined in claim 9, wherein the valve is a fuel metering valve of a hydro-mechanical metering unit of the fuel system and the control device is configured to generate a control signal to cause opening of the fuel metering valve.

15. The kit as defined in claim 9, wherein the driver is configured to be coupled to a starter interface of the accessory gearbox.

16. A method for preserving a fuel system of an aircraft engine outside of an engine test cell without powering an engine electronic controller of the aircraft engine in preparation for a period of inactivity of the aircraft engine, the method comprising:

supplying preservation fluid to the fuel system of the aircraft engine;

generating a signal to cause the opening of a valve of the fuel system using a control device other than the electronic engine controller of the aircraft engine; and

driving a fuel pump of the fuel system to cause some of the preservation fluid to flow through the open valve and in at least part of the fuel system of the aircraft engine.

17. The method as defined in claim 16, wherein the control device is coupled to the fuel system via a connector configured to provide an interface between the electronic engine controller of the aircraft engine and the fuel system of the aircraft engine.

18. The method as defined in claim 16, wherein driving the fuel pump is done using a driver, other than a starter of the aircraft engine, coupled to an accessory gearbox of the aircraft engine.

19. The method as defined in claim 18, wherein the driver is coupled to an interface of the accessory gearbox configured for interfacing the starter of the aircraft engine to the accessory gearbox.

20. The method as defined in claim 16, comprising uncoupling the electronic engine controller of the aircraft engine from the fuel system via the connector and coupling the control device to the fuel system via the connector.