Gas turbine engine and method of operating thereof

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 NO x 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 (CO 2 ) capture unit configured to receive the cooled gas stream exiting the heat recovery system for CO 2 removal and generation of a CO 2 stream, a remaining portion of the cooled gas stream exiting the carbon dioxide (CO 2 ) capture unit; and

an auxiliary compressor configured to receive the cooled gas stream exiting the carbon dioxide (CO 2 ) 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.

2. The turbine system of claim 1 , wherein the combustor is a rich burn combustor configured to allow fuel-rich combustion of the fuel stream.

3. The turbine system of claim 1 , wherein the heat recovery system is a heat recovery steam generator (HRSG) configured to receive the exhaust gas stream from the turbine for generation of steam and the cooled gas stream.

4. The turbine system of claim 1 , further comprising an exhaust gas recirculation valve to control a flow of the cooled gas stream from the heat recovery system to the auxiliary compressor.

5. The turbine system of claim 1 , wherein a portion of the exhaust gas stream is recirculated to the compressor to generate the compressed air stream.

6. The turbine system of claim 1 , wherein the exhaust gas contains a NO x level of less than 5 ppm.

7. The turbine system of claim 1 , wherein the film is generated on exposed portions of the combustor liner, a combustor dome and turbine purge cavities.

8. A turbine system, comprising:

a compressor configured to compress ambient air and at least a portion of an-exhaust gas stream containing a NO x level of less than 30 ppm to form a compressed air stream;

a combustor configured to receive the compressed air stream from the compressor, and to combust a fuel stream in a rich-quench-lean (RQL) mode of combustion to generate a post combustion gas stream;

a turbine for receiving the post combustion gas stream from the combustor to generate electricity and the exhaust gas stream;

a heat recovery system configured to receive a portion of the exhaust gas stream from the turbine for generation of a cooled gas stream exiting the heat recovery system;

a carbon dioxide (CO 2 ) capture unit configured to receive the cooled gas stream exiting the heat recovery system for CO 2 removal and generation of a CO 2 stream, a remaining portion of the cooled gas stream exiting the carbon dioxide (CO 2 ) capture unit; and

an auxiliary compressor configured to receive the cooled gas stream from exiting the heat recovery system carbon dioxide (CO 2 ) 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 is directed 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 directed to the turbine to provide a cooling flow.

9. The turbine system of claim 8 , wherein the heat recovery system is a heat recovery steam generator (HRSG) configured to receive the exhaust gas stream from the turbine for generation of steam.

10. The turbine system of claim 8 , wherein the combustor comprises:

a rich zone configured to allow fuel-rich combustion of the fuel stream;

a quench zone configured to allow conversion of the fuel-rich combustion to a fuel-lean combustion of the fuel stream; and

a lean zone configured to allow the fuel-lean combustion of the fuel stream.

11. A method of operating a turbine system, comprising:

producing a compressed air stream in a compressor;

combusting the compressed air stream with a fuel stream in a combustor to form a post combustion gas stream;

expanding the post combustion gas stream in a turbine to generate an exhaust gas stream containing a NO x level of less than 30 ppm;

cooling the exhaust gas stream in a heat recovery system to generate a cooled gas stream exiting the heat recovery system;

removing carbon dioxide (CO 2 ) from the cooled gas stream exiting the heat recovery system in a carbon dioxide (CO 2 ) capture unit and generating a CO 2 stream, a remaining portion of the cooled gas stream exiting the carbon dioxide (CO 2 ) capture unit; and

compressing the cooled gas stream exiting the carbon dioxide (CO 2 ) capture unit in an auxiliary compressor to form a cooled and compressed gas stream containing less than 13% by volume of oxygen; and

injecting the cooled and compressed gas stream into the combustor and turbine to provide a cooling flow.

12. The method of claim 11 , further comprising, recirculating another portion of the exhaust gas stream to an inlet of the compressor to generate the compressed air stream.

13. The method of claim 11 , comprising combusting the compressed air stream in a rich-quench-lean (RQL) mode of combustion.

14. 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 expanded combustion gas stream;

at least one additional combustor configured to receive the expanded combustion gas stream from the turbine and to combust an additional fuel stream to generate an additional post combustion gas stream;

at least one additional turbine for receiving the additional post combustion gas stream from the at least one additional combustor to generate power and an exhaust gas stream containing a NO x level of less than 30 ppm;

a heat recovery system configured to receive the exhaust gas stream from the at least one additional turbine for generation of a cooled gas stream;

a carbon dioxide (CO 2 ) capture unit configured to receive the cooled gas stream exiting the heat recover system for CO 2 removal and generation of a COstream, a remaining portion of the cooled gas stream exiting the carbon dioxide (CO 2 ) capture unit; and

an auxiliary compressor configured to receive at least a portion of the cooled gas stream from the heat recovery system 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 is directed to the combustor to generate film on exposed portions of the combustor, and

wherein a second portion of the cooled and compressed gas stream is directed to the turbine to provide a cooling flow.

15. The turbine system of Claim 14 , wherein the at least one additional combustor is a lean burn combustor configured to allow fuel-lean combustion of the additional fuel stream.

16. The turbine system of claim 14 , wherein the combustor is configured to combust the fuel stream in a rich-quench-lean (RQL) mode of combustion and the at least one additional combustor is configured to combust the additional fuel stream in a rich-quench-lean (RQL) mode.