Gas Turbine Combustor Burning Research Articles

Development of a 1300.DEG.C.-class gas turbine combustor burning coal-derived low-BTU gaseous fuels.

Development of a 1300.DEG.C.-class gas turbine combustor burning coal-derived low-BTU gaseous fuels.

Heat transfer in gas turbine combustor fueled with coal-water mixture

It is possible to disperse high concentrations of finely pulverized beneficiated coal in water to produce a stable coal-water slurry fuel (CWF). One of the potential applications of CWF is as a fuel in gas turbines. This represents a relatively novel, developing technology. The gas turbine cycle is capable of accomodating an increased water content of the fuel without a significant loss in efficiency.In the present study a computer model is developed to simulate the heat transfer processes taking place in a gas turbine combustor (GTC) burning a CWF. The model predicts the species and the temperature distribution throughout the GTC, the heat flux patterns and the contribution of both convection and radiation to the total heat transfer rate.Data were obtained from the combustion of coal derived fuels in a 30 inch diameter, 4 foot long bench scale atmospheric unit fueled with CWF. The data is presented and compared with model predictions.

Designing method of gas turbine combustors burning low grade fuels.

From the fuel evaluation test results, it was confirmed that the combustibility oFlow calorie gas which is essentially poorer is able to be evaluated by using the factors of its inflammable gas content and hydrogen gas content. And the weight loss rate of heavy oil is about 1/1.7 times that of distillate oil. So the flame tube reference velocity of a low calorie gas combustor is necessary to be decreased for obtaining its flame stability. But that of a heavy oil combustor is necessary to be kept higher for improving its evaporation rate, and the combustor length is necessary to be extended for increasing a residence time within a combustion zone. And it was finally confirmed from the combustion test results that this designing method is available for burning low grade fuels.

Three-Dimensional Model of Spray Combustion in Gas Turbine Combustors

A mathematical model of the three-dimensional two-phase reacting flows in gas turbine combustors has been developed which takes into account the mass, momentum, and energy coupling between the phases. The fundamental equations of motion of the droplets are solved numerically in a Lagrangian frame of reference, using a finite-difference solution of the governing equations of the gas. Well-known relations are used to model the heat and mass transfer processes and the initial droplet heat-up is allowed for. The entire fuel spray is constructed using a finite number of size ranges obeying a two parameter droplet size distribution. The results are found to be in close agreement with experimental data. An important feature of this analytical technique is that it permits the rational selection or specification of fuel nozzle design.