A wave rotor is proposed for use as a constant volume combustor. A novel design feature is investigated as a remedy for hot gas leakage, premature ignition, and pollutant emissions that are possible in this class of unsteady machines. The base geometry involves fuel injection partitions that allow stratification of fuel/oxidizer mixtures in the wave rotor channel radially, enabling pilot igniti...

The development of a liquid fueled mesoscale catalytic combustor is presented, based on the coupling of multiplexed electrosprays for liquid fuel dispersion and a stack of catalytic grids. The grids act as a compact catalytic reactor for combustion initiation, stabilization and enhanced conversion, as well as ground electrodes for the electrospray. The combustor has a volume on the order of few...

In this paper, we define a mathematically consistent set of thermo-acoustic equations via asymptotic multiple scale methods in the low-Mach number limit. The final thermoacoustic equations consist of reacting low-Mach number (LMN) equations for hydrodynamic phenomena and acoustic (AC) equations. The two sets of equations are two-way coupled. The coupling terms depend on which multiple scales ar...

A cross-power spectrum phase based adaptive technique is discussed which iteratively determines the time delay between two digitized signals that are coherent. The adaptive delay algorithm belongs to a class of algorithms that identifies a minimum of a pattern matching function. The algorithm uses a gradient technique to find the value of the adaptive delay that minimizes a cost function based ...

In this Simulation, supersonic combustion of hydrogen at Mach 3.12 has been presented. The combustor has a single fuel injection perpendicular to the main flow from the base. Finite rate chemistry model with K-ε model have been used for modeling of supersonic combustion. The pressure rise due to the combustion is not very high on account of global equivalence ratio being quite low. Within the i...

Cooling of gas turbine hot section components such as combustor liners, combustor transition pieces, turbine vanes (nozzles) and blades (buckets) is a critical task for improving the life and reliability of hotsection components. Conventional cooling techniques using air-film cooling, impingement jet cooling, and turbulators have significantly contributed to cooling enhancements in the past. Ho...

The objective of this work is to investigate the turbulent reacting flow in a three dimensional combustor with emphasis on the effect of inlet swirl flow through a numerical simulation. Flow field is analyzed using the SIMPLE method which is known as stable as well as accurate in the combustion modeling, and the finite volume method is adopted in solving the radiative transfer equation. In this...

A parallel multi-zone method for the simulation of large-scale multidisciplinary applications involving field equations from multiple branches of physics is outlined. The equations of mathematical physics are expressed in a unified form that enables a single algorithm and computational code to describe problems involving diverse, but closely coupled, physics. Specific sub-disciplines include fl...

Large Eddy Simulation (LES) is applied to investigate the turbulent non-premixed combustion flow, including species concentrations and temperature, in a cylindrical combustor. Gaseous propane (C3H8) is injected through a circular nozzle which is attached at the centre of the combustor inlet. Preheated air with a temperature of 773K is supplied through the annulus surrounding of this fuel nozzle...