Detergent delivery methods and systems for turbine engines

Patent metadata

Field	Value
Publication number	US-9957066-B2
Application number	US-201514621465-A
Country	US
Kind code	B2
Filing date	Feb 13, 2015
Priority date	Feb 13, 2015
Publication date	May 1, 2018
Grant date	May 1, 2018

Abstract

Methods and systems for in situ cleaning of internal cooling circuits of a turbine engine with detergent that provide cleaning a turbine engine that includes circumferentially arranged internal impingement cooling circuits that each include a baffle plate configured to air cool a respective surface or component of the turbine engine. Detergent is introduced through the outer wall and proximate to a back side of a baffle plate such that the detergent passes through at least one aperture in the baffle plate and acts at least upon the surface or component that the baffle plate is configured to cool. The detergent may also act on the front side of the baffle plate that is proximate to the surface or component.

First claim

We claim:

1. A method of cleaning a turbine engine that includes a plurality of internal impingement cooling circuits, each with a baffle plate, the plurality of internal impingement cooling circuits configured to air cool a respective circumferentially arranged component of the turbine engine, the method comprising:
introducing detergent to a back side of each baffle plate of the turbine engine such that the detergent passes through at least one aperture in each baffle plate and acts at least upon the circumferentially arranged component that the baffle plate is configured to air impingement cool to clean matter from the circumferentially arranged component; and
adjusting the amount of detergent introduced to the back side of each baffle plate to compensate for gravity and thereby effectuate uniform detergent jet-component interactions around a full circumference of the engine to uniformly clean matter from the circumferentially arranged component.

2. The cleaning method of claim 1 , wherein introducing detergent to a back side of a baffle plate of the turbine engine comprises introducing detergent into a pre-baffle cavity positioned proximate to the back side of the baffle plate.

3. The cleaning method of claim 1 , further comprising accessing the back side of the baffle plate of the turbine engine through a port in an outer wall of the turbine engine.

4. The cleaning method of claim 3 , wherein the port in the outer wall of the turbine engine provides a passageway to an internal cooling air channel of a respective internal impingement cooling circuit that feeds the baffle plate with air to air cool the component.

5. The cleaning method of claim 3 , wherein the port is an aperture in an outer case of the turbine engine configured to house a fuel line coupled to a fuel nozzle.

6. The cleaning method of claim 3 , wherein accessing a back side of a baffle plate of the turbine engine through a port in an outer wall of the turbine engine includes positioning a detergent delivery mechanism through the port and proximate to the back side of the baffle plate.

7. The cleaning method of claim 1 , wherein the component is a shroud coupled to a shroud hanger positioned at least partially on the back side of the shroud.

8. The cleaning method of claim 7 , wherein the detergent is passed through at least one aperture in the hanger and is introduced into a pre-baffle cavity formed between the hanger and the back side of the shroud.

9. The cleaning method of claim 1 , wherein the detergent acts on a front side of the baffle plate that substantially faces the component that the baffle plate is configured to air impingement cool.

10. The cleaning method of claim 1 , wherein the detergent includes an acidic, water-based reagent including an organic surfactant and a corrosion inhibitor designed to selectively dissolve at least one of sulfate, chloride and carbonate based species while being substantially unreactive with the material forming the component.

11. The cleaning method of claim 1 , wherein the turbine engine is attached to an aircraft.

12. The cleaning method of claim 1 , further comprising substantially simultaneously introducing detergent to the back side of each baffle plate such that the detergent passes through the at least one aperture in the baffle plate and acts upon the respective circumferentially arranged component that the baffle plate is configured to air cool.

13. The cleaning method of claim 1 , further comprising introducing detergent to a back side of a baffle plate of the turbine engine such that the detergent passes through a plurality of apertures in the baffle plate to form a plurality of discrete jets of detergent that act at least upon the component that the baffle plate is configured to air impingement cool to clean matter from the component.

14. A method of cleaning a turbine engine, the method comprising:
obtaining a turbine engine including a plurality of circumferentially arranged internal impingement cooling circuits each with a baffle plate configured to air impingement cool a respective circumferentially arranged component of the turbine engine, wherein the baffle plates each include a back side, a front side positioned proximate to the respective component, and at least one aperture extending from the front side to the back side;
positioning a detergent delivery mechanism through at least one access aperture in the outer wall of the turbine and proximate to the back side of the baffle plates;
introducing detergent to the back side of the baffle plates via the detergent delivery mechanism such that the detergent passes through the at least one aperture in the baffle plates and acts upon the components and the front sides of the baffle plates to clean matter therefrom, and
adjusting the amount of detergent introduced to the back side of the baffle plates to compensate for gravity and thereby effectuate uniform detergent jet-component interactions around a full circumference of the engine to uniformly clean matter from the circumferentially arranged components.

15. The cleaning method of claim 14 , wherein the components are circumferentially arranged shrouds each coupled to a shroud hanger positioned at least partially on the back side of the shrouds, and wherein the method further comprises passing the detergent through an aperture in each of the hangers and into a pre-baffle cavity formed between the hangers and the back sides of the baffle plates.

16. The cleaning method of claim 15 , wherein the aperture in each of the hangers is in communication with a respective internal cooling passageway of a respective circumferentially arranged internal impingement cooling circuit to feed air to a respective baffle plate to air cool a respective component.

17. The cleaning method of claim 14 , wherein the turbine engine is attached to an aircraft.

18. The cleaning method of claim 14 , wherein the detergent includes an acidic, water-based reagent including an organic surfactant and a corrosion inhibitor designed to selectively dissolve at least one of sulfate, chloride and carbonate based species while being substantially unreactive with the material forming the components.

Assignees

• Gen Electric

Inventors

• Bewlay Bernard Patrick
• Kulkarni Ambarish Jayant
• Tibbetts Nicole Jessica
• Ellis Brian Michael
• Bueno Manuel K
• Reyes Ever
• Bates Noel
• Kalb Brian

Classifications

• B64F5/30 Primary

  Cleaning aircraft · CPC title

• B64F5/0018 Primary

  Operations & Transport · mapped topic

• F05D2260/221

  Improvement of heat transfer · CPC title

• F01D25/12

  Cooling · CPC title

• B08B9/032

  by the mechanical action of a moving fluid, e.g. by flushing (B08B9/04 takes precedence {; by fluid jets mounted on cleaning devices B08B9/0433}) · CPC title