Combustion processes generate a band-limited pseudo-random sound that is often referred to as “combustion roar.” Although combustion roar sound is moderately intense but it is rather straight forward to quiet to a non-objectionable level by properly applying sound absorbing material around the burner area. In addition to the 'roar' sound which almost always exists in any confined combustion, on...

Pulse detonation technology can be a revolutionary approach for propulsion system since it offers significant fuel efficiency, higher thrust to weight ratio and low cost. Although the design concept of a pulse detonation engine is comparatively simple, but the development and stabilization of sustainable detonation wave front is difficult. Consequently pulse detonation engine technology is stil...

In this thesis, a physics-based model of an aircraft gas turbine combustor is developed for predicting NO, and CO emissions. The objective of the model is to predict the emissions of current and potential future gas turbine engines within quantified uncertainty bounds for the purpose of assessing design tradeoffs and interdependencies in a policy-making setting. The approach taken is to capture...

Combustion air humidification has proven to be effective stabilize hydrogen combustion and avoid flashback apparition in a typical micro Gas Turbine (mGT). However, both the fuel alteration dilution will impact cycle performance. A complete characterization of this thermodynamic is essential ensure that mGTs become cleaner, fully flexible fit with expectation future small-scale decentralized po...

Probabilistic progressive failure analysis (PFA) is used to predict the life of a Sylramic/MI ceramic matrix composite (CMC) combustor liner in a JTAGG-III engine under both rig and engine conditions. PFA simulations of the combustor liner were made to predict fracture paths and life cycles based on microcrack damage evolution and the contribution of failure modes to total failure. Combustor li...

This paper describes the modifications and evolution of a thermal pulse combustionmodel for predicting the combustion oscillations of an aerovalved 250 kW pulse combustorincorporating a soot formation-combustion model. Validation of the model is carried out from theexperimental data of an aerovalved Helmholtz type pulse combustor, where a sinusoidal air inlet massflow coupled with pressure osci...