Closed-loop combustion control system and control method thereof
A technology of a control system and a control method, which is applied in engine control, gas turbine devices, jet propulsion devices, etc., can solve problems such as damage to the combustion chamber tile, tripping, and load rejection, and achieve the effect of ensuring combustion stability.
Pending Publication Date: 2021-01-22
SHANGHAI ELECTRIC GAS TURBINE CO LTD
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Problems solved by technology
[0002] When the gas turbine is under load and the combustion is unstable, the acceleration amplitude of the combustion chamber will increase, which will continue to deteriorate and cause load shedding or trip accidents. In more serious cases, it will cause damage to the tiles of the combustion chamber, resulting in unforeseen economic loss recovered
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[0038] The implementation of the present invention will be illustrated by specific specific examples below, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification.
[0039] It should be noted that the structures, proportions, sizes, etc. shown in the drawings attached to this specification are only used to match the content disclosed in the specification, for those who are familiar with this technology to understand and read, and are not used to limit the implementation of the present invention. Limiting conditions, so there is no technical substantive meaning, any modification of structure, change of proportional relationship or adjustment of size, without affecting the effect and purpose of the present invention, should still fall within the scope of the present invention. within the scope covered by the disclosed technical content. At the same time, terms such as "upper", "lo...
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The invention provides a closed-loop combustion control system and a control method thereof. The closed-loop combustion control system comprises a gas turbine, a combustion state detector and a self-adaptive combustion regulation and control system, wherein the gas turbine comprises a combustion chamber, an on-duty valve for adjusting the on-duty gas supply amount, and a gas turbine control systemfor controlling the opening degree of the on-duty valve; the combustion state detector is used for measuring the thermo-acoustic oscillation intensity in the combustion chamber and is arranged on thecombustion chamber; and the self-adaptive combustion regulation and control system comprises a controller, an analog quantity receiving module, an analog quantity sending module and a digital quantity receiving and sending module, the analog quantity receiving module is connected with the controller and the combustion state detector, the analog quantity sending module is connected with the controller and the gas turbine control system, and the digital quantity receiving and sending module is respectively connected with the controller and the gas turbine control system. The combustion state ofthe combustion chamber can be monitored and adjusted in real time, and the combustion stability of the gas turbine is guaranteed.
Description
technical field [0001] The invention relates to the technical field of gas turbines, in particular to a closed-loop combustion control system and a control method thereof. Background technique [0002] When the gas turbine is under load and the combustion is unstable, the acceleration amplitude of the combustion chamber will increase, which will continue to deteriorate and cause load shedding or trip accidents. In more serious cases, it will cause damage to the tiles of the combustion chamber, resulting in unforeseen recovered economic losses. The thermoacoustic oscillation in the combustor of a gas turbine is the main cause of the acceleration deterioration of the combustor, and a hum probe is used in the gas turbine to measure the intensity of the thermoacoustic oscillation in the combustor. [0003] The causes of combustion instability usually include environmental factors, changes in fuel components, and aging of the unit. In order to avoid excessive thermoacoustic osc...
Claims
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IPC IPC(8): F02C9/00F02C9/16
CPCF02C9/00F02C9/16F05D2270/14
Inventor 成斌王浩同王伟
Owner SHANGHAI ELECTRIC GAS TURBINE CO LTD