초록 ▼

A cleaning method for a combustor comprises positioning a spray portion of a nozzle through an igniter plug boss and spraying an acid solution inside the combustion chamber. The acid solution impinges the inner liner and the outer liner, dissolving contaminant deposits inside the effusion holes. The

A cleaning method for a combustor comprises positioning a spray portion of a nozzle through an igniter plug boss and spraying an acid solution inside the combustion chamber. The acid solution impinges the inner liner and the outer liner, dissolving contaminant deposits inside the effusion holes. The nozzle can have a second spray portion outside the combustion chamber to provide acid solution to the radially outward surface of the outer liner. After cleaning, distilled water is sprayed through the nozzle to remove the acid solution residue from the combustor. The used acid solution and distilled water can be collected, filtered and pumped through the nozzle to provide a recirculating cleaning/rinsing system.

대표청구항 ▼

We claim: 1. A method of cleaning a combustor of a gas turbine engine, comprising the steps of: inserting at least part of at least one nozzle assembly into an interior of said combustor when said combustor is mounted within said gas turbine engine, wherein said inserting step further comprises ins

We claim: 1. A method of cleaning a combustor of a gas turbine engine, comprising the steps of: inserting at least part of at least one nozzle assembly into an interior of said combustor when said combustor is mounted within said gas turbine engine, wherein said inserting step further comprises inserting said at least one part of said at least one nozzle assembly through an igniter plug boss of said combustor; and spraying a fluid through said at least one nozzle assembly and towards at least one surface of said combustor, said nozzle assembly held in position relative to said combustor by an adapter portion of said nozzle assembly. 2. The method of claim 1, wherein said fluid comprises a cleaning fluid. 3. The method of claim 1, wherein said fluid comprises a recirculating fluid. 4. The method of claim 1, wherein said combustor comprises an annular combustor. 5. The method of claim 1, wherein said step of spraying comprises spraying towards an interior surface of said combustor. 6. The method of claim 1, wherein said nozzle assembly comprises a first spray portion and a second spray portion. 7. The method of claim 1, wherein said fluid comprises an acetic acid solution with a pH between about 2.0 and about 3.0. 8. The method of claim 2, further comprising a step of spraying a rinse fluid through said nozzle assembly and towards said surface of said combustor. 9. The method of claim 6, wherein said step of spraying comprises spraying a first portion of said fluid through said first spray portion and towards an interior surface of said combustor and spraying a second portion of said fluid through said second spray portion and towards an exterior surface of said combustor. 10. A method of cleaning an on-wing combustor of a gas turbine engine, the combustor having an interior surface and an exterior surface with a nozzle assembly having a first spray portion and a second spray portion, comprising the steps of: inserting said first spray portion of said nozzle assembly through an igniter plug boss of said combustor and into an interior portion of said combustor when said on-wing combustor is mounted within said gas turbine engine; and spraying a cleaning fluid through said nozzle assembly such that a first portion of said cleaning fluid passes through said first spray portion of said nozzle assembly and towards said interior surface and a second portion of said cleaning fluid passes through said second spray portion of said nozzle assembly and towards said exterior surface. 11. The method of claim 10, further comprising a step of spraying a rinse fluid through said nozzle assembly such that a first portion of said rinse fluid passes through said first spray portion and towards said interior surface and a second portion of said rinse fluid passes through said second spray portion and towards said exterior surface. 12. The method of claim 10, wherein said step of spraying a cleaning fluid produces an effluent, and wherein said effluent is collected, filtered and returned to and sprayed through said nozzle assembly. 13. The method of claim 10, wherein said step of spraying a cleaning fluid comprises pumping a cleaning fluid through a receiving aperture of said nozzle assembly. 14. The method of claim 10, wherein said first spray portion comprises a rotating spray head. 15. The method of claim 10, wherein said second spray portion comprises a rotating spray head. 16. The method of claim 10, wherein said nozzle assembly comprises a plurality of nozzle openings, each nozzle opening having a diameter between about 0.01 inches and about 0.05 inches. 17. The method of claim 13, wherein said pumping is at a flow rate between about 1 gallon per minute and about 30 gallons per minute. 18. The method of claim 13, wherein said pumping is at a pressure between about 10 psi and about 250 psi. 19. A method of cleaning a combustor in a gas turbine engine having at least one igniter plug boss comprising the steps of: inserting a spray portion of a nozzle assembly through said igniter plug boss of the combustor in the gas turbine engine; and pumping a cleaning fluid through said nozzle assembly such that at least one fluid stream impinges an interior surface of said combustor. 20. The method of claim 19, wherein said step of pumping a cleaning fluid comprises pumping an acetic acid solution. 21. The method of claim 19, wherein said cleaning fluid has a pH between about 2.0 and about 3.0. 22. A method of cleaning an annular combustor with a nozzle assembly having a first rotating spray head and a second rotating spray head, the annular combustor forming part of a gas turbine engine of an aircraft, the method comprising the steps of: inserting the first rotating spray head through an igniter plug boss and into the annular combustor when the combustor is mounted within said gas turbine engine of said aircraft; and pumping an acid solution through said nozzle assembly such that a first portion of said acid solution passes through said first rotating spray head of said nozzle assembly and towards an interior surface of said annular combustor and a second portion of said acid solution passes through said second rotating spray head of said nozzle assembly and towards an exterior surface of said annular combustor. 23. The method of claim 22, wherein said acid solution comprises acetic acid. 24. The method of claim 22, wherein said pumping is at a pressure between about 10 psi and about 250 psi. 25. The method of claim 22, wherein said acid solution is a recirculating acid solution. 26. The method of claim 22, wherein said acid solution has a pH between about 2.0 and about 3.0. 27. A method of removing a contaminant deposit from an effusion hole of an on-wing combustor of a gas turbine aircraft engine, the method comprising the steps of: inserting at least one nozzle assembly through an igniter plug boss of said on-wing combustor; pumping a recirculating fluid through at least one nozzle assembly, said recirculating fluid comprises acetic acid, said nozzle assembly having a first rotating spray head, a second rotating spray head and an adapter portion, wherein a first portion of said recirculating fluid passes through said first rotating spray head and impinges an interior surface of said on-wing combustor mounted within said gas turbine aircraft engine and a second portion of said recirculating fluid passes through said second rotating spray head and impinges an exterior surface of said on-wing combustor, thereby removing said contaminant deposit; and pumping a rinse fluid comprising distilled water through said nozzle assembly.