Aircraft engine cleaning system

Patent metadata

Field	Value
Publication number	US-9657590-B2
Application number	US-201514749252-A
Country	US
Kind code	B2
Filing date	Jun 24, 2015
Priority date	Aug 4, 2014
Publication date	May 23, 2017
Grant date	May 23, 2017

Abstract

An aircraft comprising a cabin air system, a gas turbine engine including an engine core coupled to the cabin air system to provide compressed bleed air to the cabin air system and a cleaning agent supply connector coupled to the engine core to conduct a cleaning agent to the engine core, and a pneumatic coupling system including a first valve coupled between the cabin air system and the engine core, a second valve coupled between the engine core and the cleaning agent supply connector, and a controller coupled to the first valve, the controller configured to automatically close the first valve and block compressed bleed air that may contain cleaning agent moving through the engine core from moving into the cabin air system in response to receipt of an input associated with a cleaning cycle.

First claim

What is claimed is:

1. An aircraft comprising
a cabin air system,
a gas turbine engine including an engine core coupled to the cabin air system to provide compressed bleed air to the cabin air system and a cleaning agent supply connector coupled to the engine core to conduct a cleaning agent to the engine core, and
a pneumatic coupling system including a first valve coupled between the cabin air system and the engine core, a second valve coupled between the engine core and the cleaning agent supply connector, and a controller coupled to the first valve, the controller configured to automatically close the first valve and block compressed bleed air that may contain cleaning agent moving through the engine core from moving into the cabin air system in response to receipt of an input associated with a cleaning cycle.

2. The aircraft of claim 1 , wherein the controller is coupled to the cleaning agent supply connector and the cleaning agent supply connector is configured to send the input associated with a cleaning cycle to the controller in response to a cleaning agent supply being coupled to the cleaning agent supply connector.

3. The aircraft of claim 2 , wherein the controller is coupled to the second valve and the controller is configured to automatically open the second valve in response to receipt of the input associated with a cleaning cycle.

4. The aircraft of claim 1 , wherein the controller is coupled to the second valve and the second valve is configured to send the input associated with a cleaning cycle to the controller in response to movement of the second valve from a closed position to an opened position.

5. The aircraft of claim 1 , wherein the pneumatic coupling system includes a user interface coupled to the controller and the user interface is configured to send the input associated with a cleaning cycle to the controller.

6. A cleaning system comprising
an aircraft including an airframe, a cabin air system, a gas turbine engine coupled to the airframe, and a starter air supply coupled to the airframe, the starter air supply sized to constantly dry motor the gas turbine engine for a predetermined starting cycle, and
a mobile supply unit movable relative to the aircraft, the mobile supply unit including a cleaning agent supply adapted to provide cleaning agent to the gas turbine engine and a cleaning air supply sized to provide enough compressed air to constantly dry motor the gas turbine engine for a predetermined cleaning cycle, the cleaning cycle being longer than the starting cycle,
wherein the gas turbine engine includes an engine core coupled to the cabin air system to provide compressed bleed air to the cabin air system and a cleaning agent supply connector coupled to the engine core to conduct a cleaning agent to the engine core, and
wherein the aircraft includes a pneumatic coupling system including a first valve coupled between the cabin air system and the engine core, a second valve coupled between the engine core and the cleaning agent supply connector, and a controller coupled to the first valve, the controller configured to automatically close the first valve and block compressed bleed air that may contain cleaning agent moving through the engine core from moving into the cabin air system in response to receipt of an input associated with a cleaning cycle.

7. The cleaning system of claim 6 , wherein the gas turbine engine includes a cleaning agent supply connector coupled to the cleaning agent supply by a hose and an engine core coupled to the cleaning agent supply connector to receive cleaning agent from the cleaning agent supply connector.

8. The cleaning system of claim 7 , wherein the cleaning agent supply connector is coupled to the controller and is configured to send the input associated with a cleaning cycle to the controller in response to a cleaning agent supply being coupled to the cleaning agent supply connector.

9. The aircraft of claim 8 , wherein the pneumatic coupling system coupled between the cleaning agent supply connector and the engine core and the controller is configured to automatically adjust the pneumatic coupling system to allow cleaning solution to move from the cleaning agent supply connector to the engine core in response to receipt of the input associated with a cleaning cycle.

10. The aircraft of claim 7 , wherein the pneumatic coupling system includes a user interface coupled to the controller and the user interface is configured to send the input associated with a cleaning cycle to the controller.

11. A method of cleaning an aircraft engine, the method comprising
coupling an external cleaning air supply to a gas turbine engine included in an aircraft;
introducing a cleaning agent into the gas turbine engine; and
dry motoring the gas turbine engine for a predetermined cleaning cycle time by conducting compressed air from the external cleaning air supply to the gas turbine engine,
wherein the aircraft includes a cabin air system, the gas turbine engine, and a pneumatic coupling system,
wherein the gas turbine engine includes an engine core coupled to the cabin air system to provide compressed bleed air to the cabin air system and a cleaning agent supply connector coupled to the engine core to conduct a cleaning agent to the engine core, and
wherein the pneumatic coupling system includes a first valve coupled between the cabin air system and the engine core, a second valve coupled between the engine core and the cleaning agent supply connector, and a controller coupled to the first valve, the controller configured to automatically close the first valve and block compressed bleed air that may contain cleaning agent moving through the engine core from moving into the cabin air system in response to receipt of an input associated with a cleaning cycle.

12. The method of claim 11 further comprising coupling a cleaning agent supply to a cleaning agent supply connector included in the gas turbine engine.

13. The method of claim 12 , wherein the external cleaning air supply and the cleaning agent supply are mounted to a transport vehicle for movement together relative to the aircraft.

14. The method of claim 11 , wherein the cleaning agent supply connector is coupled to the controller and is configured to send the input associated with a cleaning cycle to the controller in response to a cleaning agent supply being coupled to the cleaning agent supply connector.

15. The method of claim 14 , wherein the pneumatic coupling system coupled between the cleaning agent supply connector and the engine core and the controller is configured to automatically adjust the pneumatic coupling system to allow cleaning solution to move from the cleaning agent supply connector to the engine core in response to receipt of the input associated with a cleaning cycle.

16. The method of claim 11 , further comprising interacting with a user interface coupled to the controller, wherein the user interface is configured to send the input associated with a cleaning cycle to the controller.

Assignees

• Rolls Royce Corp

Inventors

• Griffiths George F
• Heggere Prahlad R D
• Green Jeffrey A

Classifications

• B64D27/20

  within, or attached to, fuselages · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• B64F5/30 Primary

  Cleaning aircraft · CPC title

• B64D13/02

  the air being pressurised · CPC title

• F01D25/002 Primary

  Cleaning of turbomachines · CPC title