Computational Study of Combustion Dynamics in a Single-Element Lean Direct Injection Gas Turbine Combustor
AIR FORCE RESEARCH LAB EDWARDS AFB CA AEROSPACE SYSTEMS DIRECTORATE
Pagination or Media Count:
Simulations of self-excited combustion instabilities in a model configuration of a lean direct injection LDI gas turbine combustor were performed and investigated with different operating conditions air temperature and equivalence ratio. Concurrently, experimental data were obtained at the same conditions in a well-instrumented test combustor with the same configuration to validate the simulation results. The simulations are used to investigate the coupling between the acoustic and heat release modes and the important flow dynamics to understand the physics that lead to combustion instabilities in the LDI combustor. A Precessing Vortex Core PVC hydrodynamic instability was found to be significant in driving spray and flame responses. Detailed and systematic studies of the PVC instability are also performed using non-reacting simulations of an acoustically-open combustor to minimize the acoustic and combustion effects on the flow field.
- Combustion and Ignition
- Jet and Gas Turbine Engines