Combustion chamber of gas turbine and operation method of combustion chamber

Abstract

The invention relates to a combustion chamber of a gas turbine and an operation method of the combustion chamber. The combustion chamber provided by the invention is an annular combustion chamber, a plurality of head part structures are arranged in the circumferential direction of the combustion chamber for supplying fuel oil from a fuel oil pump to the combustion chamber, the head part structures are divided into at least two head part structure groups, a fuel oil manifold pipe is respectively arranged corresponding to each head part structure group, and a valve element is mounted on at least one of the fuel oil manifold pipes. A fuel oil control system is used for controlling the first valve element to open and close, thereby opening and closing at least one head part structure group. Through the structure of the combustion chamber, oil-gas ratio, supply pressure of fuel oil and the like of each head part structure can be kept constant, thereby ensuring atomization performance of the fuel oil and keeping combustion stability.

Description

technical field [0001] The present invention relates to a combustor for a gas turbine and also to a method of operating the combustor of the gas turbine. In particular, the gas turbine involved in the present invention can be used in fields such as aeroengines. Background technique [0002] With the development of technology, for today's gas turbines, especially for aviation gas turbine engines, the layout structure of the annular combustor has become the mainstream design form. [0003] figure 1 A longitudinal section view of a gas turbine with an annular combustor is shown in . As an example, the gas turbine is a turbojet engine comprising a combustor 100 , a compressor 200 upstream of the combustor 100 , a turbine 400 downstream of the combustor 100 and a tailpipe 300 downstream of the turbine 400 . Here, the so-called "upstream" and "downstream" are based on the flow direction of air or gas. [0004] A head structure 110 is provided at the entrance of the combustion ...

AI Technical Summary

Problems solved by technology

In this way, the amount of air in the gas turbine will be relatively excessive, which will cause the combustion chamber of the gas turbine to be in a fuel-lean state as a whole.

At the same time, under the influence of unstable combustion in the combustion chamber, there may be a situation where the gas turbine stalls

This situation is especially serious for aero engines, because the flameout of the gas turbine means air parking, which seriously affects flight safety

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