Aircraft engine entrained particle removal system and method

A method of directing particles entrained within an airflow disposed to enter a gas turbine engine of an aircraft, the gas turbine engine including a nose cone, a fan section, a compressor inlet, a compressor section, and a turbine section, wherein the compressor section and the turbine section are in communication with a core gas path, and the nose cone is fixed for rotation with the fan section, the method comprising:

• providing an entrained particle removal (EPR) system configured to inject a fluid outward from the nose cone from a plurality of nozzles engaged with the nose cone, wherein the plurality of nozzles are spaced apart from one another around a circumference of the nose cone;
• and
• controlling the EPR system to inject the fluid from the plurality of nozzles into the airflow;
• wherein particles wetted by the injected fluid are subject to centrifugal force in and aft of the fan section and are directed radially outward of the compressor inlet.

An aircraft, comprising:

• a gas turbine engine having a nose cone, a fan section, a compressor inlet, a compressor section, and a turbine section arranged along an axial centerline, wherein the compressor section and the turbine section are in communication with a core gas path;
• an entrained particle removal (EPR) system including a plurality of nozzles engaged with the nose cone, wherein the nozzles are configured to inject a fluid outward from the nose cone;
• and
• a controller in communication with the EPR system and a non-transitory memory storing instructions, which instructions when executed cause the controller to control the EPR system to provide the fluid to the nozzles for injection outward from the nozzles;
• wherein the gas turbine engine is configured such that particles entrained within an airflow disposed to engage the gas turbine engine that are wetted by the fluid injected by the EPR system are directed radially outside of the compressor inlet.