GAS TURBINE MECHANICAL DESCRIPTION Sample Clauses

GAS TURBINE MECHANICAL DESCRIPTION. The gas turbine output flange is located at the compressor end of the rotor assembly to provide "cold end" drive. This feature substantially improves alignment control and provides an axial exhaust to optimize the plant arrangement for combined cycle or waste heat recovery applications. The generator is connected to the gas turbine through a solid coupling. The direction of rotation is counter-clockwise when facing the direction of airflow through the gas turbine. [GRAPHIC OMITTED] The gas turbine has an eighteen stage axial flow compressor with modulated inlet guide vanes. Interstage extraction is used for turbine nozzle and wheelspace cooling. A reverse flow, fourteen chamber combustion system is utilized with multiple fuel nozzles per chamber. Redundant spark plugs and flame detectors are a standard part of the combustion system with crossfire tubes connecting each combustion chamber to adjacent xxxxxxxx. If required, water injection can be introduced for NOx emissions control. Transition pieces are effectively cooled by air impingement. Thermal barrier coatings are applied to the inner walls of the combustion liners for smoother temperature gradients. The gas turbine has three turbine stages with the first and second stage nozzles and buckets being air cooled. The buckets are designed with long xxxxxx to isolate the turbine wheel rim from the hot gas path. Precision cast buckets are used for each turbine stage with the second and third stages incorporating an integral tip shroud for better gas path leakage control. All turbine buckets are coated to provide corrosion resistance. The turbine section is coupled to an axial diffuser with optimum pressure recovery for higher thermal efficiency. The rotor is a two bearing single shaft design with high torque capability. It incorporates internal cooling and thermal response control in the turbine section. Both the compressor and turbine sections are constructed of individually rabbeted discs held with through bolts. For field changeout, the unit rotor is handled as one piece. The turbine and compressor casings are horizontally split for ease of inspection and maintenance. For each combustion chamber, the liners and transition pieces can be individually changed out. Borescope holes are located in the compressor, combustion and turbine sections to facilitate visual inspection.
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