Systems and Methods for Extending Gas Turbine Emissions Compliance

Abstract

A gas turbine system for operation at low loads. The gas turbine system may include a number of inlet guide vanes, a compressor, a turbine, and an air movement system for maintaining an emission from the gas turbine system below a predetermined level.

1 . A gas turbine system for operation at low loads, comprising:
 a plurality of inlet guide vanes;   a compressor;   a turbine; and   air movement means for maintaining an emission from the gas turbine system below a predetermined level.   
     
     
         2 . The gas turbine system of  claim 1 , wherein the air movement means comprises an inlet bleed heat line extending from the compressor to upstream of the plurality of inlet guide vanes. 
     
     
         3 . The gas turbine system of  claim 1 , wherein the compressor comprises a compressor discharge casing and wherein the air recirculation means comprises an inlet bleed heat line extending from the compressor discharge casing to upstream of the plurality of inlet guide vanes. 
     
     
         4 . The gas turbine system of  claim 1 , wherein the compressor comprises a plurality of stages and wherein the air movement means comprises a compressor recirculation line extending from a downstream compressor stage to an upstream compressor stage. 
     
     
         5 . The gas turbine system of  claim 1 , wherein the air movement means comprises a compressor cooling line extending from the compressor to the turbine. 
     
     
         6 . The gas turbine system of  claim 5 , wherein the compressor cooling lines comprises a plurality of compressor cooling lines. 
     
     
         7 . The gas turbine system of  claim 1 , wherein the air movement means comprises an extraction line extending from the compressor to downstream of the turbine. 
     
     
         8 . The gas turbine system of  claim 1 , wherein the compressor comprises a compressor discharge casing and wherein the air extraction means comprises an extraction line extending from the compressor discharge casing to downstream of the turbine. 
     
     
         9 . The gas turbine system of  claim 1 , wherein the plurality of inlet guide vanes comprises an angle of about thirty (30) to about fifty (50) degrees. 
     
     
         10 . The gas turbine system of  claim 1 , wherein the load thereon comprises about as low as about thirty percent (30%). 
     
     
         11 . A gas turbine for operation at low loads, comprising:
 a plurality of inlet guide vanes;   a compressor; and   air recirculation means to raise a temperature of an outlet air stream leaving the compressor.   
     
     
         12 . The gas turbine of  claim 11 , wherein the air recirculation means comprises an inlet bleed heat line extending from the compressor to upstream of the plurality of inlet guide vanes. 
     
     
         13 . The gas turbine of  claim 11 , wherein the compressor comprises a compressor discharge casing and wherein the air recirculation means comprises an inlet bleed heat line extending from the compressor discharge casing to upstream of the plurality of inlet guide vanes. 
     
     
         14 . The gas turbine of  claim 11 , wherein the compressor comprises a plurality of stages and wherein the air recirculation means comprises a compressor recirculation line extending from a downstream compressor stage to an upstream compressor stage. 
     
     
         15 . The gas turbine of  claim 11 , wherein the plurality of inlet guide vanes comprises an angle of about thirty (30) to about fifty (50) degrees. 
     
     
         16 . A gas turbine system for operation at low loads, comprising:
 a plurality of inlet guide vanes;   a compressor;   a turbine; and   air extraction means to extract air from the compressor.   
     
     
         17 . The gas turbine system of  claim 16 , wherein the air extraction means comprises a compressor cooling line extending from the compressor to the turbine. 
     
     
         18 . The gas turbine system of  claim 17 , wherein the compressor cooling lines comprises a plurality of compressor cooling lines. 
     
     
         19 . The gas turbine system of  claim 16 , wherein the air extraction means comprises an extraction line extending from the compressor to downstream of the turbine. 
     
     
         20 . The gas turbine system of  claim 16 , wherein the compressor comprises a compressor discharge casing and wherein the air extraction means comprises an extraction line extending from the compressor discharge casing to downstream of the turbine.