In general, techniques are described by which to provide a turbine engine compressor particulate offtake. A gas turbine engine comprising a compressor may perform the techniques. The compressor may comprise a plurality of compressor stages, where each compressor stage comprises a circumferential row of stator vanes and a rotor. The compressor may also include an outer circumferential casing that defines a fluidic opening within or between adjacent compressor stages. The fluidic opening may be configured to receive particulate flowing and air through the compressor and output the particulate and air outside of the gas turbine engine. The gas turbine engine also includes a combustor in series flow downstream of the compressor, and a turbine in series flow downstream of the combustor.