A gas turbine engine comprising: an engine core defining a rotating axis, the engine core includes a compressor having an impeller arranged to rotate about the axis to compress air with an impeller tip and a diffuser for collecting compressed air from the impeller tip, a combustor fluidly connected to receive compressed air from the diffuser for combustion, and a turbine fluidly connected to receive exhaust products from the combustor, the impeller, the diffuser, the combustor, and the turbine collectively defining a core flow path; an outer shell disposed about the engine core to house the engine core therein; and a bleed circuit (24, 1024) fluidly connected between the compressor and the turbine for communicating a stream of impeller air from the impeller to the turbine, the bleed circuit including a bleed inlet (32, 1032) arranged at the impeller tip and stationary with respect to the impeller; characterised in that the bleed circuit (24, 1024) includes a transport section (36, 1036), at least one inlet passage defined through at least one blade of the diffuser and in communication with the bleed inlet, and at least one transport passage in fluid communication with the at least one inlet passage; the bleed inlet being configured to bleed the stream of impeller air out from the core flow path and to communicate the stream to the transport section, the transport section being in fluid communication with a deposit junction (34, 1034) of the turbine; the at least one inlet passage receiving the stream of impeller air from the bleed inlet, at least a portion of the inlet passage being located aft of the impeller, the at least one inlet passage proceeding through the diffuser and penetrating through the outer shell at a location for connection with the transport section (36, 1036); and the transport passage penetrating through the outer shell and extending along the axis outside of the outer shell to a location near the turbine and into a plenum of a second stage vane of the turbine. an engine core defining a rotating axis, the engine core includes a compressor having an impeller arranged to rotate about the axis to compress air with an impeller tip and a diffuser for collecting compressed air from the impeller tip, a combustor fluidly connected to receive compressed air from the diffuser for combustion, and a turbine fluidly connected to receive exhaust products from the combustor, the impeller, the diffuser, the combustor, and the turbine collectively defining a core flow path; an outer shell disposed about the engine core to house the engine core therein; and a bleed circuit (24, 1024) fluidly connected between the compressor and the turbine for communicating a stream of impeller air from the impeller to the turbine, the bleed circuit including a bleed inlet (32, 1032) arranged at the impeller tip and stationary with respect to the impeller; characterised in that the bleed circuit (24, 1024) includes a transport section (36, 1036), at least one inlet passage defined through at least one blade of the diffuser and in communication with the bleed inlet, and at least one transport passage in fluid communication with the at least one inlet passage; the bleed inlet being configured to bleed the stream of impeller air out from the core flow path and to communicate the stream to the transport section, the transport section being in fluid communication with a deposit junction (34, 1034) of the turbine; the at least one inlet passage receiving the stream of impeller air from the bleed inlet, at least a portion of the inlet passage being located aft of the impeller, the at least one inlet passage proceeding through the diffuser and penetrating through the outer shell at a location for connection with the transport section (36, 1036); and the transport passage penetrating through the outer shell and extending along the axis outside of the outer shell to a location near the turbine and into a plenum of a second stage vane of the turbine.