Micro-premixing on-duty nozzle assembly and micro-premixing combustion chamber of gas turbine

Abstract

The invention discloses a micro-premixing on-duty nozzle assembly and a micro-premixing combustion chamber of a gas turbine. The micro-premixing combustion chamber of the gas turbine comprises a flametube and a combustor, the combustor is arranged at the end part of the flame tube; the combustor comprises a plurality of combustor main nozzle areas and a combustor on-duty nozzle area; the structure of the combustor on-duty nozzle area is the same as that of the micro-premixing on-duty nozzle assembly; wherein the plurality of combustor main nozzle areas are arranged around the circumference ofthe combustor on-duty nozzle area. Compared with a traditional combustion chamber of the gas turbine, the center on-duty nozzle enables a certain backflow area to be formed near an outlet of the on-duty nozzle through space angle arrangement, and therefore the flame stabilizing effect is achieved; and meanwhile, the lengths of fuel conveying pipes on an inner ring and an outer ring of the on-dutynozzle are different, each main nozzle micro-premixing pipe can adopt different structure schemes, inherent frequency difference is achieved, the thermo-acoustic coupling probability is reduced, andthe problem of unstable combustion can be effectively avoided.

Description

technical field [0001] The invention relates to the technical field of gas turbine combustion chambers, in particular to a micro-premix duty nozzle assembly and a gas turbine micro-premix combustion chamber. Background technique [0002] Gas turbine is an efficient and clean power machine. The power generation based on gas turbine and its combined cycle has accounted for 22% of the world's total power generation, and will continue to rise in the future. In order to improve the cycle efficiency of the gas turbine, the gas initial temperature and supercharging ratio are constantly increasing. Taking heavy-duty gas turbines as an example, the initial gas temperature of F-class gas turbines is around 1650K, and the combined cycle efficiency is 57%; the initial gas temperatures of H-class and J-class gas turbines are around 1750K and 1850K, and the combined cycle efficiencies are 60% and 1850K respectively. 61%; the initial gas temperature of the next-generation gas turbine will...

AI Technical Summary

Problems solved by technology

Compared with combustion engines using conventional fuels (such as natural gas, etc.), combustion engines using hydrogen-rich fuels, due to the strong fuel activity of hydrogen, especially its high flame velocity, low ignition energy and wide flammability limit increase flashback, Risk of spontaneous combustion and oscillation

Also, the high adiabatic flame temperature of hydrogen is a challenge for low NOx formation

However, hydrogenation of ordinary fuel will reduce the ignition delay time of the fuel and increase the combustion speed.

This will lead to high local temperature, high nitrogen oxides, fast flame propagation speed and easy tempering and oscillation

These properties challenge the development of advanced combustion technologies and burners for hydrogen-rich fuels

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