In order to further extend the turbine fuel flex capability, a test under atmospheric conditions of a full-scale SGT-400 burner was performed to study the combustion behavior when operating on hydrogen enriched natural gas. A high speed camera was installed in the rig to investigate the flame dynamics on different operation conditions. NOx emissions were measured for all presented conditions. The combustion system was instrumented with thermocouples on all the key locations to allow flame position monitoring and to avoid flame attachment on the hardware. Further measurements included static pressure probes to monitor combustor pressure drop. The test was conducted in a systematic matrix format to include the most important combustion parameters in order to identify their individual effects on the combustion behaviors. The quantity of hydrogen in natural gas, fuel split, air preheat temperature, air reference velocity and flame temperature were the combustion related variables studied in the presented test campaign. The volumetric hydrogen quantity could be increased to 30% maintaining stable operation for all measured conditions. Higher hydrogen contents up to 80 vol-% were reached without flash back tendency. A glowing spark igniter prevented testing at even higher hydrogen contents. Hydrogen enriched gas showed higher NOx emissions and improved blowout limit. Hydrogen blending in the fuel also reduced the combustor pressure drop, lowered the prechamber temperature and raised the pilot tip temperature.
In order to further extend the turbine fuel flex capability, a test under atmospheric condi tions of a full-scale SGT-400 burner was performed to study the combustion behavior when operating on hydrogen enriched natural gas (NG). A high speed camera was in stalled in the rig to investigate the flame dynamics on different operation conditions. NOx emissions were measured for all presented conditions. The combustion system was instru mented with thermocouples on all the key locations to allow flame position monitoring and to avoid flame attachment on the hardware. Further measurements included static pressure probes to monitor combustor pressure drop. The test was conducted in a system atic matrix format to include the most important combustion parameters in order to iden tify their individual effects on the combustion behaviors. The quantity of hydrogen in natural gas, fuel split, air preheat temperature, air reference velocity and flame tempera ture were the combustion related variables studied in the presented test campaign. The volumetric hydrogen quantity could be increased to 30% maintaining stable operation for all measured conditions. Higher hydrogen contents up to 80 vol. % were reached without flash back tendency. A glowing spark igniter prevented testing at even higher hydrogen contents. Hydrogen enriched gas showed higher NOx emissions and improved blowout limit. Hydrogen blending in the fuel also reduced the combustor pressure drop, lowered the prechamber temperature and raised the pilot tip temperature.
Following successful testing of the SGT-400 combustion system at atmospheric conditions with hydrogen enriched natural gas, a high pressure combustion test campaign was carried out at the Siemens test facility in Lincoln UK. Combustion performance at full engine operating conditions was studied, with the aim of demonstrating the capability of the standard SGT-400 combustion hardware to fire fuels with increased hydrogen content. Measurements consisted of: a pilot tip thermocouple to monitor the risk of flashback; pressure sensors to capture the combustion dynamics signature; and emissions instrumentation measuring NOx and CO. The combustor was also instrumented with thermocouples to monitor both the distribution of wall temperatures and potential locations of flashback when utilizing the highly reactive hydrogen enriched gas. The current paper reports the findings of the high pressure tests and compares with the atmospheric results that had been documented previously. Combustion behavior at full engine pressure and temperature was found to be consistent with atmospheric conditions. Pilot tip temperature increased with the hydrogen gas content due to the higher flame speed. Combustion dynamics shifted to a higher frequency for the hydrogen enriched gas, and heat release fluctuations increased. NOx emission also increased with the hydrogen blending due to the enhanced fuel reactivity. The high pressure tests demonstrated that the SGT-400 standard DLE combustion system can operate without risk of flashback for up to 20% vol hydrogen content. The next phase of the hydrogen program is to test a production engine using enriched gas and confirm its full operational characteristics. Extending the operational envelope of the standard DLE combustion system to hydrogen contents above 20% vol is also of interest.
This paper presents the extension and optimization of the Siemens Industrial Turbomachinery Ltd Dry Low Emission combustion system from the existing SGT-300 Single-Shaft turbine to the new SGT-300 Twin-Shaft engine. The SGT-300 Twin-Shaft combustion development follows the Siemens Product Development Process and the new engine is now validated for introduction to the market. Different designs are tested and optimized at full engine pressure and temperature conditions in Lincoln, UK Siemens combustion high pressure rig facility. Optimized combustion design is installed to the new design SGT-300 Twin-Shaft engine to validate in the Siemens gas turbine test bed in Lincoln, UK. Blocker bars have been designed and applied to the combustion rig to capture the acoustic signature of the nozzle guide vane. Traverse is performed in the high pressure rig to identity the combustor exit hot gas temperature map. Emission turndown to 50% load with NOx < 9 ppm and CO < 10 ppm capability is one of the major Key Performance Indicators. The SGT-300 Twin-Shaft combustion system is optimized for excellent emission behavior in this load range. Additionally, some of the compressor delivery air is bypassed around the combustor to exhaust through the air bleed system at part load.
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