Patent ID: 8893511
Filing Date: 2014-11-25
Classification: F02C,F23R

Abstract:
1. A gas turbine system comprising: a compressor operative to output an airstream; a diffuser having an inlet to receive the airstream and an outlet to output the airstream, the outlet having an area larger than the inlet to diffuse the airstream; a fuel nozzle operative to receive fuel and emit the fuel in a combustor; at least one bleed duct having a first and a second inlet between the compressor and the outlet of the diffuser, the second inlet located upstream of the first inlet, and the at least one bleed duct operative to direct bleed air from downstream of the compressor directly to the fuel nozzle; a first vortex cavity at the first inlet of the bleed duct operative to draw compressed air from the at least one airstream in the diffuser; and a second vortex cavity at the second inlet, the first and second vortex cavities arranged such that bleed air from each of the first and second vortex cavities flows into the same bleed duct prior to flowing to the fuel nozzle.