Compressor assembly for gas turbine
View Patent ↗A compressor assembly, and more in general relates to a compressor for a gas turbine providing a solution that teaches to locate within a cavity formed by the outer casing of the compressor and the inner vane carrier a separator element, or membrane, such to divide the cavity into two sub-cavities. This advantageously results in a more flexible design with respect to the positioning of the flange blow-off extractor and to the cavity sizing, as the flange position is not necessarily the boundary for the flow anymore as it would be without the separator element.
1. A compressor assembly for a compressor of a gas turbine, the compressor assembly comprising:
a compressor outer casing including at least one blow-off opening;
a vane carrier defining a bleed duct;
wherein the compressor assembly is arranged such that the outer casing and the vane carrier define a cavity for gathering a flow of fluid, said cavity being adapted to receive the fluid through said bleed duct and to feed the fluid externally through said at least one blow-off opening; and
wherein the compressor assembly includes a separator element having a first end fixed to the outer casing and a second end fixed to the vane carrier, the separator element located in said cavity for dividing said cavity into first and second sub-cavities, wherein the first sub-cavity is in fluid communication with the at least one blow-off opening and wherein the second sub-cavity and the separator element are unperforated and an extension of the separator element along its entire length in a radial direction R of the compressor is greater than an extension of the separator element in an axial direction.
2. The compressor assembly according to claim 1 , wherein said separator element is arranged between said outer casing and said vane carrier.
3. The compressor assembly according to claim 1 , wherein at least an inner wall of the cavity is covered with a thermally insulating layer.
4. The compressor assembly according to claim 1 , wherein said thermally insulating layer comprises a coating material.
5. The compressor assembly according to claim 1 , wherein said coating material is a ceramic-based coating.
6. The compressor assembly according to claim 3 , wherein said thermally insulating layer comprises a metal sheet positioned on said inner wall of the cavity, said inner wall having a plurality of recesses such to establish a layer of thermally-insulating air between said inner wall and said metal sheet.
7. The compressor assembly according to claim 1 , wherein the separator element has upper and lower ends located within corresponding grooves embedded in respective opposed inner walls of said cavity.
8. The compressor assembly according to claim 1 , wherein said separator element comprises two halves connected to each other.
9. The compressor assembly according to claim 8 , wherein said two halves are connected by bolted elements.
10. The compressor assembly according to claim 8 , wherein said two halves are connected by a sealing lip.
11. A compressor for a gas turbine comprising a compressor assembly according to claim 1 .