Increasing the combustion temperatures in a gas turbine engine to achieve higher efficiency and power output also results in high heat loads to turbine components downstream of the combustor. The challenge of adequately cooling the nozzle guide vane directly downstream of the combustor is compounded by a complex vortical secondary flow at the junction of the endwall and the airfoil. This flow t...

Gas turbine engines have a high power-to-weight ratio, making them ideal for generation of aircraft thrust, and can have excellent electrical power generation efficiencies when used in a combined cycle power plant. A complex vortical flow at the junction of the nozzle guide vane airfoil and its casing (endwall) in the turbine section tends to decrease aerodynamic efficiency and increase metal t...

The central recirculation zone (CRZ) in a swirl stabilized gas turbine combustor has a dominant effect on the fuel air mixing process and flame stability. Most of state of the art swirlers share one disadvantage; the fixed swirl number for the same swirler configuration. Thus, in a mathematical sense, Reynolds number becomes the sole parameter for controlling the flow characteristics inside the...

Combustion noise comprises two components: direct combustion noise and indirect combustion noise. The latter is the lesser studied, with entropy noise believed to be its main component. Entropy noise is generated via a sequence involving diverse flow physics. It has enjoyed a resurgence of interest over recent years, because of its increasing importance to aero-engine exhaust noise and a recogn...

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...

The liner of a gas turbine combustor is a very flexible structure that is exposed to the pressure oscillations that occur in the combustor. These pressure oscillations can be of very high amplitude due to thermoacoustic instability, when the fluctuations of the rate of heat release and the acoustic pressure waves amplify each other. The liner structure is a dynamic mechanical system that vibrat...

Characterization of distributed combustion reformed methanolblends in a model gas turbine combustor

For some decades, efforts have been made to exploit nonsteady combustion and gas dynamic phenomenon. The theoretical potential of nonsteady-flowmachines has led to the investigation of various oscillatoryflowdevices suchas pulse detonation engines, wave rotors, pulse jets, and nonsteady ejectors. This paper aims to provide a progress review of past and current research in developing a particula...