Combustion Emissions and Reliability with premixed combustors and Alternative fuels are a challenge for of premix burners water injection gas turbine combustors with respect to n Premixed hydrogen combustion at combustion emissions, stability, Syngas combustion in premixed n ultra-high combustor inlet autoignition and flashback safety. This swirl burners temperatures work group investigates the fundamental n Premixed swirl burner aerodynamics processes and develops rules applicable n Lean blowout and emissions to new combustor designs with respect to Staged premixed combustion n low-emission fuel-flexible operation. n CO quenching in staged gas turbine Mie scattering signal of a lean combustors at part load premixed hydrogen-air flame Projects Improvement of gas turbine part load n n Wall flashback emissions by on-board fuel reforming n Combustion induced vortex breakdown n Power augmentation of gas turbines n Flame stabilization at the fuel injectors Combustion Instabilities and Noise propagation in vehicle auxiliary heaters The strong coupling of acoustics and and aeroengine combustors heat release in confined flames leads to a feedback loop which can result in violent combustion instabilities. These are a threat for gas turbines, rocket motors and other combustion devices because they Instantaneous pressure distri- bution in result in substantial pressure oscillations, a rocket motor nozzle related to higher order acoustic modes structural vibrations and increased heat transfer. Combustion instabilities reduce the lifetime, limit the operation range or even lead to severe damage of combus- tion systems. This research group uses numerical and experimental techniques on a wide range of topics from combustion instability like flame-to-flame interaction, prediction of combustion instability, active instability control and flame noise. Projects n Combustor design for thermoacoustic stability (DETAS) n Thermoacoustic stability of annular gas turbine combustors n Thermoacoustics of aeroengine com- bustors High frequency instabilities in gas n turbine combustors n Acoustic transfer functions of gas turbine and rocket motor flames n Acoustic losses in combustion chambers n Passive damping of combustion instabilities Rocket motor damping mechanisms n Rocket motor flame dynamics and n stability n Combustion noise generation and
Combustion Emissions and Reliability Alternative fuels are a challenge for gas turbine combustors with respect to combustion emissions, stability, autoignition and flashback safety. This work group investigates the fundamental processes and develops rules applicable to new combustor designs with respect to low-emission fuel-flexible operation. Projects n Wall flashback n Combustion induced vortex breakdown n Flame stabilization at the fuel injectors of premix burners n Syngas combustion in premixed swirl burners n Premixed swirl burner aerodynamics n Lean blowout and emissions n Staged premixed combustion n CO quenching in staged gas turbine combustors at part load n Improvement of gas turbine part load emissions by on-board fuel reforming n Power augmentation of gas turbines with premixed combustors and water injection n Premixed hydrogen combustion at ultra-high combustor inlet temperatures Mie scattering signal of a lean premixed hydrogen-air flame Combustion Instabilities and Noise The strong coupling of acoustics and heat release in confined flames leads to a feedback loop which can result in violent combustion instabilities. These are a threat for gas turbines, rocket motors and other combustion devices because they result in substantial pressure oscillations, structural vibrations and increased heat transfer. Combustion instabilities reduce the lifetime, limit the operation range or even lead to severe damage of combus- tion systems. This research group uses numerical and experimental techniques on a wide range of topics from combustion instability like flame-to-flame interaction, prediction of combustion instability, active instability control and flame noise. Projects n Combustor design for thermoacoustic stability (DETAS) n Thermoacoustic stability of annular gas turbine combustors n Thermoacoustics of aeroengine com- bustors n High frequency instabilities in gas turbine combustors n Acoustic transfer functions of gas turbine and rocket motor flames n Acoustic losses in combustion chambers n Passive damping of combustion instabilities n Rocket motor damping mechanisms n Rocket motor flame dynamics and stability n Combustion noise generation and propagation in vehicle auxiliary heaters and aeroengine combustors Instantaneous pressure distri- bution in a rocket motor nozzle related to higher order acoustic modes
32-Sattelmayer-Institute_of_Thermodynamics_2015.docx