Turbine engine cleaning systems and methods
A system and method for cleaning an installed gas turbine engine is provided. The system may include a controller on an engine core, wherein the engine core defines a primary gas path and includes at least one airfoil extending into the primary gas path. The method may include initiating a cleaning program and directing a cleaning fluid toward the engine core in response to the initiation of the cleaning program. The method may further include initiating delivery of the cleaning fluid as a non-vaporized liquid within the primary gas path to the engine core.
1. A method for cleaning of an installed gas turbine engine comprising an engine core and defining a primary gas path, the engine core including at least one airfoil extending into the primary gas path, the method comprising:
initiating a cleaning program, wherein initiating the cleaning program comprises;
executing a flight schedule having a plurality of predetermined flight stages, wherein the plurality of predetermined flight stages comprises a cruising stage and a descent stage; and
establishing that the installed gas turbine engine is in one of the cruising stage or the descent stage;
directing a cleaning fluid toward the engine core in response to the initiation of the cleaning program; and
initiating delivery of the cleaning fluid through a non-atomizing nozzle as a non-vaporized liquid within the primary gas path to the engine core.
2. The method of claim 1 , wherein initiating the cleaning program includes receiving a pre-buildup abatement signal.
3. The method of claim 1 , wherein initiating the cleaning program includes receiving a particulate detection signal.
4. The method of claim 1 , wherein initiating the cleaning program includes determining a temperature limit has been exceeded.
5. The method of claim 1 , wherein the cleaning fluid includes a primary liquid, wherein the gas turbine engine encloses a reservoir configured to store the primary liquid, and wherein directing the cleaning fluid includes motivating the primary liquid from the reservoir.
6. The method of claim 5 , wherein directing the cleaning fluid includes selectively introducing a secondary agent into the primary liquid.
7. The method of claim 1 , wherein initiating the cleaning program includes determining reduced combustion within the gas turbine engine.
8. A method for cleaning of an installed gas turbine engine comprising an engine core and defining a primary gas path, the engine core including at least one airfoil extending into the primary gas path, the method comprising:
initiating a cleaning program;
directing a cleaning fluid toward the engine core in response to the initiation of the cleaning program;
initiating delivery of the cleaning fluid through a non-atomizing nozzle as a non-vaporized liquid within the primary gas path to the engine core; and
tuning engine output, including maintaining an engine thrust at a predetermined level during delivery of the cleaning fluid to the gas turbine engine in-flight.
9. A method for cleaning of a gas turbine engine installed on an aircraft, the gas turbine engine comprising an engine core and defining a primary gas path, the engine core including at least one airfoil extending into the primary gas path, the method comprising:
executing a flight schedule having a plurality of predetermined flight stages, wherein the plurality of predetermined flight stages comprises a takeoff stage, and ascent stage, a cruising stage, a descent stage, and a landing stage;
establishing that the landing stage has been completed;
taxiing the aircraft with the gas turbine engine operating in an idle mode;
initiating a cleaning program;
directing a cleaning fluid toward the engine core in response to the initiation of the cleaning program; and
initiating delivery of the cleaning fluid through a non-atomizing nozzle as a non-vaporized liquid within the primary gas path to the engine core while the aircraft is taxiing.
10. The method of claim 9 , wherein the cleaning fluid is carried on board the aircraft.
11. The method of claim 9 , wherein the cleaning fluid comprises a water on board the aircraft, the method further comprising:
taxiing the aircraft to a destination gate;
establishing a reduced combustion state within the gas turbine engine by ceasing combustion; and
replenishing the water on board the aircraft.