A cooling arrangement for a compressor drive cone (48) in a gas turbine engine (10). An annular cavity (62) defined by the drive cone (48), a portion of a compressor rotor disc (44) and a downstream cavity wall (52). The cavity (62) comprising a recirculation zone (66) at its radially outermost region. The cavity (62) arranged to ingest hot working gas radially inwardly into the recirculation zone (66). An annular array of pipes (70) that penetrate through the cavity wall (52) close to the radially inward extent of the recirculation zone (66). The pipes (70) coupled to a supply of cooling fluid and having an open end arranged to direct the cooling air, in use, across the recirculation zone (66) towards the drive cone (48).