Compressor arrangement , particularly part of a gas turbine engine, comprising - a main compressor section comprising boundary walls of a main fluid path through the main compressor section , the main compressor section comprising a plurality of rows of blades and a plurality of rows of vanes and being segmented into an upstream sub section and a downstream sub section , each comprising at least one row of blades and at least one row of vanes arranged within the main fluid path ; - a transition piece located downstream of the plurality of rows of blades of the main compressor section , the transition piece comprising further boundary walls of the main fluid path through the transition piece ; - an annular cavity ; - an effusion opening connecting the downstream sub section or the transition piece and the cavity ; - at least one valve to control effusion of compressor fluid from the main fluid path into the cavity via the effusion opening during operation; - a passage connecting the cavity and the main compressor section to guide fluid between the cavity and the main fluid path of the main compressor section during operation, wherein the passage is located between the upstream sub section and the downstream sub section and located at least one row of blades and at least one row of vanes upstream of the effusion opening characterised in that the compressor arrangement further comprises a bleed valve arranged in a bleed duct which diverts from the cavity , and in that (a) the compressor arrangement is configured to operate in a normal mode of operation, wherein the passage , in a closed position of the at least one valve and an open position of the bleed valve , is arranged to provide a flow of fluid from the main fluid path into the cavity , and (b) the compressor arrangement is configured to operate in a additional mode of operation, wherein the passage , in a closed position of the at least one valve and a closed position of the bleed valve , is arranged to provide no flow of fluid.. - a main compressor section comprising boundary walls of a main fluid path through the main compressor section , the main compressor section comprising a plurality of rows of blades and a plurality of rows of vanes and being segmented into an upstream sub section and a downstream sub section , each comprising at least one row of blades and at least one row of vanes arranged within the main fluid path ; - a transition piece located downstream of the plurality of rows of blades of the main compressor section , the transition piece comprising further boundary walls of the main fluid path through the transition piece ; - an annular cavity ; - an effusion opening connecting the downstream sub section or the transition piece and the cavity ; - at least one valve to control effusion of compressor fluid from the main fluid path into the cavity via the effusion opening during operation; - a passage connecting the cavity and the main compressor section to guide fluid between the cavity and the main fluid path of the main compressor section during operation, wherein the passage is located between the upstream sub section and the downstream sub section and located at least one row of blades and at least one row of vanes upstream of the effusion opening (a) the compressor arrangement is configured to operate in a normal mode of operation, wherein the passage , in a closed position of the at least one valve and an open position of the bleed valve , is arranged to provide a flow of fluid from the main fluid path into the cavity , and (b) the compressor arrangement is configured to operate in a additional mode of operation, wherein the passage , in a closed position of the at least one valve and a closed position of the bleed valve , is arranged to provide no flow of fluid.. <EOS>