COMPRESSOR DIFFUSER AND DIFFUSER PIPES THEREFOR

A diffuser for a compressor of a gas turbine engine is disclosed. The diffuser has a plurality of diffuser pipes (40) circumferentially distributed about an axis of the compressor, each of the plurality of diffuser pipes (40) extending from an inlet to an outlet and having a bend section (45) between the inlet and the outlet, a low pressure side and an opposite high pressure side. A recirculation conduit (50) defines a recirculation path from a first flow region to a second flow region in one or more of the plurality of the diffuser pipes (40), the first flow region having a greater static pressure than that of the second region, the recirculation conduit (50) having a conduit inlet (51) and a conduit outlet (52), at least the conduit outlet (52) located within the low pressure side of one of the plurality of the diffuser pipes (40).