Abstract
Abstract A detailed investigation on flame structures and stabilization mechanisms of confined high momentum jet flames by one-dimensional (1D)-laser Raman measurements is presented. The flames were operated with natural gas (NG) at gas turbine relevant conditions in an optically accessible high-pressure test rig. The generic burner represents a full scale single nozzle of a high temperature FLOX® gas turbine combustor including a pilot stage. 1D-laser Raman measurements were performed on both an unpiloted and a piloted flame and evaluated on a single shot basis revealing the thermochemical states from unburned inflow conditions to burned hot gas in terms of average and statistical values of the major species concentrations, the mixture fraction and the temperature. The results show a distinct difference in the flame stabilization mechanism between the unpiloted and the piloted case. The former is apparently driven by strong mixing of fresh unburned gas and recirculated hot burned gas that eventually causes autoignition. The piloted flame is stabilized by the pilot stage followed by turbulent flame propagation. The findings help to understand the underlying combustion mechanisms and to further develop gas turbine burners following the FLOX concept.
Highlights
Gas turbines (GT) increasingly play a key role in future power generation markets
Section Experimental Setup of the present paper describes the investigated model FLOX R combustor and the selected operating conditions for the Raman measurements as well as the GTP-19-1600
Model Combustor The combustion chamber and the burner were mounted onto a test carrier that is placed inside the pressure casing for the tests
Summary
Gas turbines (GT) increasingly play a key role in future power generation markets. With the capability of fast startup and load changes they are well suited to balance the fluctuating power supply from wind and solar power systems and to maintain grid reliability. Are a cleaner alternative to coal based power generation for the provision of the required basic load. In order to fulfill the requirements in complex growing markets for power generation combustor concepts for modern gas turbines require a high level of both fuel and load flexibility. Fuel flexibility includes the capability of firing with gaseous and liquid backup fuels, and the stable combustion of gaseous fuels of different compositions and a wide range of Wobbe indices. Operational flexibility requires the reliable operation in a wide load range while keeping the emissions below the legal limits at any time
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