An optimal predictive control approach for the suppression of thermo-acoustic instabilities in the combustor chamber is investigated. The approach uses the combustor pressure fluctuations and fuel modulation data for building internal dynamic input-output models and designing the controller. The knowledge of the physical model of the system is not required. This data-based nature of the approac...

A multi-fidelity micro combustor design approach is developed for a small-scale combined heat and power CHP system. The characterised by the coupling of preliminary model using method 3D high-fidelity modelling experimental testing. integrated multi-physics schemes their underlying interactions are initially provided. During phase, rapid exploration achieved coupled reduced-order models, where ...

A feedback control strategy is applied to enhance the performance of a laboratory-scale pulsed combustor operating near the lower flammability limit. As with many combustion processes, at lean conditions, combustion instabilities develop which result in complex, lowfrequency fluctuations in fuel concentration and lead directly to misfire and flameout. The control strategy exploits the highly no...

The goal of this study was twofold. First, modelling strategies were proposed to characterize the dynamics driving the thermoacoustic instabilities in a swirl-stabilized premixed burner. Secondly, this model was used to synthesize controllers in order to apply active control strategies to suppress this phenomenon. An experimental combustor model based on acoustic properties of the combustion ch...

We apply symbol-sequence analysis to pulse-combustor oscillations to characterize the onset of instabilities near the fuel-lean limit. Using data from a laboratory combustor, we demonstrate that such techniques can be very useful for finding and classifying complex pressure patterns which can be precursors to misfires and flameout. On-line diagnosis of these instabilities could facilitate activ...

An estimation of the conversion efficiency (e) of fuel sulfur to SO3 and H2SO4, where e=([SO3]+[H2SO4])/[ST] and [ST] is the total sulfur atom concentration in the exhaust at the exit of an aircraft gas-turbine combustor, was derived from measurements by comparison with model results. The major results of the presented CIMS experiments and their interpretation with a model simulation are: (i) T...

Since a large number of physical parameters influence the flame dynamics in a full scale gas turbine combustor, it is virtually impossible to develop physically correlated reduced order models for flame dynamics by directly studying these complex reacting flows. Even the Rijke tube combustor system, though comprising of a simple geometry and a flat flame, shows a strong nonlinear coupling betwe...

Contributions from the combustor to the overall propulsion noise of civilian transport aircraft are starting to become important due to turbofan design trends and expected advances in mitigation of other noise sources. During on-ground, static-engine acoustic tests, combustor noise is generally sub-dominant to other engine noise sources because of the absence of in-flight effects. Consequently,...