Compressor arrangement and gas turbine engine

A compressor arrangement of a gas turbine engine, comprising:

• a main compressor section comprising an inner boundary wall and an outer boundary wall that define therebetween a main fluid path through the main compressor section, and a second outer wall surrounding the outer boundary wall, 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;
• a cavity between the outer boundary wall and the second outer wall and comprising an annular shape;
• an effusion opening that opens directly into the cavity and connects 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 that opens directly into the cavity and connects 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 bleed valve arranged in a bleed duct which diverts from the cavity:
• (a) wherein 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,
• (b) wherein the compressor arrangement is configured to operate in an additional mode of operation, wherein the passage, in the closed position of the at least one valve and a closed position of the bleed valve, is arranged to provide no flow of fluid, and
• (c) wherein the compressor arrangement is configured to operate in a first mode of operation, wherein the passage, in an opened position of the at least one valve and the closed position of the bleed valve, is arranged to provide a flow of fluid from the cavity into the main fluid path at a location upstream of the effusion opening, and
• a control entity to perform at least the following steps during operation:
• measure a combustion temperature or at least one physical parameter indicative for the combustion temperature;
• compare the measured combustion temperature or the at least one physical parameter with a lower threshold value and open the at least one valve if the measured combustion temperature is below the lower threshold value, and/or
• compare the measured combustion temperature or the at least one physical parameter with an upper threshold value and close the at least one valve if the measured combustion temperature is above the upper threshold value.