Compressor for a gas turbine
An axial compressor providing a thermal adjustment of a housing of a compressor of a stationary gas turbine to the rotor is provided. A partial flow is decoupled from the compressor air flow for cooling gas turbine components. The contact of the partial flow decoupled from the compressor with the interior side of the housing is substantially limited, or even avoided, by a separating element in a collection chamber annularly encompassing the flow path in order to prevent the premature thermal heating of the gas turbine or of the housing during cold starting.
1. 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.
2. The compressor as claimed in claim 1 , wherein the separating element is arranged closer to an inner side of the casing than to an outer side of the outer wall.
3. The compressor as claimed in claim 1 , wherein the outer wall includes a plurality of radially arranged bleed openings.
4. The compressor as claimed in claim 1 , wherein the collecting chamber covers only an axial section of the flow path of the compressor.
5. The compressor as claimed in claim 4 , wherein the axial section is provided in a plurality of rear compressor stages, with regard to the medium.
6. The compressor as claimed in claim 1 ,
further comprising a plurality of collecting chambers,
wherein an individual separating element may be arranged only in one collecting chamber or a plurality of individual separating elements may be arranged in several of the plurality of collecting chambers, or the plurality of individual separating elements may be arranged in all of the plurality the collecting chambers in each case.
7. A stationary gas turbine which is exposed to axial throughflow, comprising:
a compressor, 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.
8. The gas turbine as claimed in claim 7 , wherein the separating element is arranged closer to an inner side of the casing than to an outer side of the outer wall.
9. The gas turbine as claimed in claim 7 , wherein the outer wall includes a plurality of radially arranged bleed openings.
10. The gas turbine as claimed in claim 7 , wherein the collecting chamber covers only an axial section of the flow path of the compressor.
11. The gas turbine as claimed in claim 10 , wherein the axial section is provided in a plurality of rear compressor stages, with regard to the medium.
12. The gas turbine as claimed in claim 7 ,
further comprising a plurality of collecting chambers,
wherein an individual separating element may be arranged only in one collecting chamber or a plurality of individual separating elements may be arranged in several of the plurality of collecting chambers, or the plurality of individual separating elements may be arranged in all of the plurality the collecting chambers in each case.