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Axial grading combustion chamber of gas turbine and control method of axial grading combustion chamber

A technology of gas turbines and secondary combustion chambers, applied in combustion methods, combustion chambers, continuous combustion chambers, etc., can solve problems such as increased emissions, increased CO emissions, and unstable combustion, so as to increase outlet temperature and increase the proportion of flue gas return flow Effect

Active Publication Date: 2020-03-13
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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Problems solved by technology

Because the air volume flow rate of the conventional turbine engine combustor remains basically unchanged under low load, it is easy to cause combustion instability and increase CO emissions, and if the fuel ratio of the duty nozzle is increased, it will lead to NO x rise in emissions

Method used

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  • Axial grading combustion chamber of gas turbine and control method of axial grading combustion chamber
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  • Axial grading combustion chamber of gas turbine and control method of axial grading combustion chamber

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Embodiment Construction

[0051] The present invention forms two-stage high-efficiency low-pressure drop reflux inside the combustion chamber through the first and second-stage high-speed jet entrainment reflux, which promotes the mixing of unburned matter and flue gas, so that the combustion zone maintains a high-temperature and low-oxygen atmosphere and forms a Two-stage soft burn. Therefore, the residence time of fuel in the high temperature zone is reduced, and the emission of nitrogen oxides is reduced. At the same time, because the secondary unburned gas is directly burned in the high-temperature flue gas, it has good combustion stability and burnout efficiency, and can achieve a wide load adjustment range. Therefore, under the premise of ensuring combustion efficiency and combustion stability, the present invention can realize rapid response to burnout load, and can realize extremely low emission of nitrogen oxides in a wider load range.

[0052] In order to make the object, technical solution ...

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Abstract

The invention discloses an axial grading combustion chamber of a gas turbine and a control method of the axial grading combustion chamber. The axial grading combustion chamber comprises a combustion chamber structural assembly, a first-stage premixed jet nozzle assembly, a first-stage on-duty nozzle assembly and a second-stage premixed jet nozzle assembly. A head baffle of a first-stage combustionchamber and a front wall of a combustion chamber case form a head part of the combustion chamber, and the first-stage on-duty nozzle assembly is arranged in the center of the head part of the combustion chamber; the first-stage premixed jet nozzle assembly is arranged on a circumference of the head part of the combustion chamber by taking the center of the head part of the combustion chamber as acircle center; and the second-stage premixed jet nozzle assembly is positioned on a circumference of a head baffle of a second-stage combustion chamber by taking an axis of a flame tube of the first-stage combustion chamber as a circle center. According to the axial grading combustion chamber provided by the invention, through grading injection of fuel, residence time of the fuel in a high-temperature region is shortened while combustion efficiency is ensured, and two-stage soft combustion is realized, so that emission of nitrogen oxide by the combustion chamber of the gas turbine is greatlyreduced, and an outlet temperature of the combustion chamber can be further improved.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to an axially graded combustion chamber of a gas turbine and a control method thereof. Background technique [0002] In order to improve the power cycle efficiency of gas turbines, and with the development of turbine materials and cooling technologies, the outlet temperature of the combustor has increased significantly in recent decades and is gradually approaching the lower limit of the temperature where thermal NO emissions increase sharply. It has been shown that when the combustion chamber temperature exceeds 1800K, due to the rapid growth of thermal NO, the low NO x The emission potential will be exhausted, so it is urgent to explore more advanced combustor design solutions to achieve low NO at higher combustor outlet temperatures x emission. [0003] In addition, the emission characteristics of conventional gas turbine engine combustors generally perform better at full-...

Claims

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Application Information

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IPC IPC(8): F23R3/38
CPCF23R3/38
Inventor 熊燕郑祥龙朱子儒曾洁玙肖云汉
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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