| 摘要 |
<p>The design of compressors for the cooling systems for combustion turbines is disclosed. Closed-loop air cooling systems and combustion turbines with ultra-low NOx emission combustion systems require nearly all of the compressor air to be pre-mixed with fuel. In either of these systems, it is necessary to extract a portion of the compressor delivery air, cool it, compress it and then re-introduce it into the combustion turbine. In the prior art, this was accomplished using an outside compressor. However, in accordance with the present invention, a compressor that supplies the required amount of increased pressure air for cooling hot end components is provided that is 'on-board' or internal to the combustion turbine system. In preferred embodiments, an axial compressor receives a portion of compressor delivery air, is diverted at the compressor exit inner diameter and then compressed in one or more reduced height axial compressor stages located below the inner wall of the main compressor exit diffuser that is itself located directly downstream from the auxiliary compressor. Methods of cooling combustion turbines are also disclosed.</p> |
