Gas turbine engine and method of operating thereof

摘要

A turbine system and method of operating is provided. The system includes a compressor configured to generate a compressed low-oxygen air stream and a combustor configured to receive the compressed low-oxygen air stream and to combust a fuel stream to generate a post combustion gas stream. The turbine system also includes a turbine for receiving the post combustion gas stream to generate a low-NOx exhaust gas stream, a heat recovery system configured to receive the low-NOx exhaust gas stream and generate a cooled air stream and an auxiliary compressor configured to generate an oxygen and water vapor deficient cooled and compressed air stream. A portion of the oxygen and water vapor deficient cooled and compressed air stream is directed to the combustor to generate an Oxygen and H2O deficient film on exposed portions of the combustor, and another portion is directed to the turbine to provide a cooling flow.

主权项

1. A turbine system, comprising:
a compressor configured to generate a compressed air stream; a combustor configured to receive the compressed air stream from the compressor and to combust a fuel stream to generate a post combustion gas stream; a turbine for receiving the post combustion gas stream from the combustor to generate power and an exhaust gas stream containing a NOx level of less than 30 ppm; a heat recovery system configured to receive the exhaust gas stream exiting the turbine for generation of a cooled gas stream exiting the heat recovery system; a carbon dioxide (CO2) capture unit configured to receive the cooled gas stream exiting the heat recovery system for CO2 removal and generation of a CO2 stream, a remaining portion of the cooled gas stream exiting the carbon dioxide (CO2) capture unit; and an auxiliary compressor configured to receive the cooled gas stream exiting the carbon dioxide (CO2) capture unit for generation of a cooled and compressed gas stream containing less than 13% by volume of oxygen, wherein a first portion of the cooled and compressed gas stream exiting the auxiliary compressor is input to the combustor to generate a film on exposed portions of the combustor, and wherein a second portion of the cooled and compressed gas stream is input to the turbine to provide a cooling flow.