This paper reports on our research in developing a micro power generation system based on gas turbine engine and piezoelectric converter. The micro gas turbine engine consists of a micro combustor, a turbine and a centrifugal compressor. Comprehensive simulation has been implemented to optimal the component design. We have successfully demonstrated a silicon-based micro combustor, which consist...

Abstract—There is a gap at combustor-turbine interface where leakage flow comes out to prevent hot gas ingestion into the gas turbine nozzle platform. The leakage flow protects the nozzle endwall surface from the hot gas coming from combustor exit. For controlling flow’s stream, the gap’s geometry is transformed by changing fillet radius size. During the operation, step configuration is occurre...

Recently, we have completed the development of an The ability to obtain quantitative planar laserincorporates a production fuel injector and is capable of induced fluorescence (PLIF) measurements in a highoperating at pressures up to 50 atm with preheated air. pressure combustor would represent a significant This facility allows laser-based imaging techniques to be advance in the application of...

A detection method of lean blowout in a laboratory-scale premixed gas-turbine model combustor has been proposed from a view point of nonlinear dynamics. The translation error, which quantifies the degree of the parallelism of trajectories in the phase space constructed from the time-series data of the combustion-chamber pressure fluctuations, is used as a detector in this work. The dynamic beha...

Improving the performance and durability of gas turbine aircraft engines depends highly on achieving a better understanding of the flow interactions between the combustor and turbine sections. The flow exiting the combustor is very complex and it is characterized primarily by elevated turbulence and large variations in temperature and pressure. The heat transfer and aerodynamic losses that occu...

The modern gas turbine engine requires innovative cooling techniques to protect its internal components from the harsh operating environment typically seen downstream of the combustor. Much research has been performed on the design of these cooling techniques thus allowing for combustion temperatures higher than the melting point of the parts within the turbine. As turbine inlet temperatures an...

Original scientific paper Numerical simulations of four combustion processes in a dual-fuel combustor of chemically recuperated gas turbine (CRGT) were carried out in this work. The fuels in the four combustion processes were liquid fuel, liquid fuel + steam, liquid fuel + reformed gas and reformed gas, respectively. The mathematical models adopted for different fuels combustion consist of real...

Numerical simulations of complex large-scale flow systems must capture a variety of physical phenomena in order to predict the flow accurately. Currently, many flow solvers are specialized to simulate one part of a flow system effectively, but are either inadequate or too expensive to be applied to a generic problem. As an example, the flow through a gas turbine can be considered. In the compre...

This paper presents an Artificial Neural Network (ANN)-based modeling technique for prediction of outlet temperature, pressure and mass flow rate of gas turbine combustor. Results obtained by present modeling were compared with those obtained by experiment. The results showed the effectiveness and capability of the proposed modeling technique with reasonable accuracies of about 95 percent. This...

Title of Document: Investigation of Colorless Distributed Combustion (CDC) with Swirl for Gas Turbine Application Ahmed Essam ElDin Khalil Hasan, PhD, 2013 Directed By: Dr. Ashwani K. Gupta Distinguished University Professor Department of Mechanical Engineering Colorless Distributed Combustion (CDC) with swirl is investigated for gas turbine engine applications due to its benefits for ultra-low...