On-wing combustor cleaning using direct insertion nozzle, wash agent, and procedure

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.

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.

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.