Particulate separator assembly for a gas turbine engine

An assembly for a gas turbine engine of an aircraft propulsion system, the assembly comprising:

• at least one rotational assembly configured for rotation about an axis, the at least one rotational assembly comprising a shaft, a bladed compressor rotor, and a bladed turbine rotor, the shaft interconnecting the bladed compressor rotor and the bladed turbine rotor;
• a compressor comprising the bladed compressor rotor, the compressor configured to form a compressed air flow;
• a turbine comprising the bladed turbine rotor, the turbine comprising at least one rotor blade stage of the bladed turbine rotor and at least one vane stage;
• an engine static structure comprising an engine case assembly, the engine case assembly extending circumferentially about the axis, the engine case assembly surrounding the at least one rotational assembly;
• and
• a particulate separator assembly comprising a plurality of particulate separators, the plurality of particulate separators disposed outside of the engine case assembly, the plurality of particulate separators connected in fluid communication with and between an intermediate stage of the compressor and the at least one rotor blade stage and the at least one vane stage, the plurality of particulate separators configured to receive the compressed air flow from the intermediate stage, separate particulate from the compressed air flow, and direct the compressed air flow to the at least one rotor blade stage and the at least one vane stage.