GAS TURBINE ENGINE AND METHOD WITH CORE FLOW DEBRIS CLEANER

An assembly (200) of a gas turbine engine (20) includes a low pressure compressor (44), a high pressure compressor (52), an intermediate case (45) between the low pressure compressor (44) and the high pressure compressor (52), and a cleaning apparatus (70) having an annular arrangement (400) about the intermediate case (45). A core flow path (C) is defined through the low pressure compressor (44), the intermediate case (45), and the high pressure compressor (52). The annular arrangement (400) includes a scroll portion (300) configured to extract debris from an airstream at an outer diameter wall (204) of the core flow path (C) and return the airstream to the core flow path (C).