Patent ID: 8899050

Claim:
A compressor for a gas turbine, comprising: an outer wall; a compressor casing; a collecting chamber; a bleed opening; and a separating element, wherein a flow path exists, which is annular in cross section, for a medium which is to be compressed therein, wherein the flow path is delimited radially on the outside by the outer wall which is annular in cross section, and with the compressor casing which encompasses the outer wall, forming the collecting chamber which is arranged in between, and wherein the bleed opening in the outer wall extracts a part of the medium which flows in the flow path into the collecting chamber, wherein an opening is arranged in the casing in order to discharge the extracted part of the medium from the casing, wherein the separating element is arranged in the collecting chamber dividing the collecting chamber into a radially inner collecting chamber and a radially outer collecting chamber, wherein the separating element includes a discharge opening which via a passage is connected to the opening, wherein the radially outer collecting chamber is formed as a closed chamber which serves as an insulating cavity between the radially inner collecting chamber and the casing, wherein the collecting chamber, as seen in an axial direction of the compressor, is delimited by two sidewalls, wherein the two sidewalls extend in each case from the casing to the outer wall, and wherein the separating element is plate-like and the two sidewalls each include a slot which lie opposite each other and in which the plate-like separating element is inserted.