Title of Document: DEVELOPMENT OF COLORLESS DISTRIBUTED COMBUSTION FOR GAS TURBINE APPLICATION Vaibhav Kumar Arghode, PhD, 2011 Directed By: Dr. Ashwani K. Gupta Distinguished University Professor Department of Mechanical Engineering Colorless Distributed Combustion (CDC) is investigated for gas turbine engine application due to its benefit for ultra-low pollutant emission, improved pattern fac...

This study investigates the combined effect of catalyst placement and solid thermal conductivity on stability a U-bend catalytic heat-recirculating micro-combustor. The CFD code ANSYS Fluent 2020 R1 was used for two-dimensional simulations lean premixed propane/air combustion by varying inlet gas velocity, i.e., input power. Three configurations were compared at low (3 W/(m K)) high (30 wall co...

Mesoscale–combustor is one component of the micropower generator. The mesoscale–combustor function to produce heat energy from combustion chemical hydrocarbon compounds. small dimensions meso-combustor cause large losses and short residence times for reactants. These two factors lead narrow flame flammability limits. This study aims increase limits by lengthening reactant time increasing mixing...

The objective of this study was to optimize the design injection nozzle hole fuel injector a model MGT engine. To achieve higher combustion efficiency mixed gas in chamber, first, well-mixed homogeneous should be formed accelerate flame propagation chamber reach temperature and pressure. In study, four different shapes were designed, formation characteristics numerically analyzed. Three paramet...

Microjet hydrogen flames can be directly used as micro heat sources or applied in propulsion systems. In our previous study, under zero gravity and without an active air supply, the combustion completeness of jet within a mesoscale tube with inner diameter 5 mm was very low. this we were dedicated to improving efficiency by using convergent nozzle (tilt angle around 68°) instead straight one, e...

Coupling model for two-dimensional mixed-compression supersonic inlet with Mach number of 2.5 at design point and pulse detonation combustor was established, three working schemes were designed to investigate multi cycle process by using unsteady numerical simulation chemical reaction. The results show that the following two measurements can both restrain back-propagating compression wave broad...