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Gas compressor control method and device

A control method and control device technology, applied in the direction of pump control, mechanical equipment, machine/engine, etc., can solve problems such as shortage, achieve balanced load distribution, reduce the risk of human error, and reduce the dependence on unit operating experience

Active Publication Date: 2021-11-05
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] It can be seen that the above-mentioned prior art adopts the method of angle threshold or multiple tests to improve the working efficiency of the gas turbine, but how to improve the stall margin of the compressor and how to adjust the adjustable vane of the compressor under specific working conditions, especially There is a relative lack of research on multi-stage adjustable vanes

Method used

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  • Gas compressor control method and device

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0062] Such as figure 1 As shown, a gas turbine compressor control method, preferably, this control method can be activated when the gas turbine compressor is in a low-speed working condition, but when the gas turbine compressor is in other working conditions, this control method can also be used for control and adjustment . At the same time, it should be noted that the compressors of other turbomachines can also be regulated by this control method.

[0063] The compressor includes multi-stage moving blades and multi-stage stationary vanes, the multi-stage stationary vanes include multi-stage adjustable stationary vanes, and the angle of each adjustable stationary vane in the multi-stage adjustable stationary vanes is can be adjusted during the working process of the machine, and the control method includes the following steps:

[0064] S1, the step of setting the initial angle of the adjustable vane, wherein the initial angle of the adjustable vane is determined according t...

Embodiment 2

[0076] Such as image 3 As shown, a gas turbine compressor control method, preferably, this control method can be activated when the gas turbine compressor is in a low-speed working condition, but when the gas turbine compressor is in other working conditions, this control method can also be used for control and adjustment . At the same time, it should be noted that the compressors of other turbomachines can also be regulated by this control method.

[0077] The compressor includes multi-stage moving blades and multi-stage stationary vanes, the multi-stage stationary vanes include multi-stage adjustable stationary vanes, and the angle of each adjustable stationary vane in the multi-stage adjustable stationary vanes is can be adjusted during the working process of the machine, and the control method includes the following steps:

[0078] S6, a step of establishing a flow calculation example of the compressor, wherein a flow calculation example of the compressor to be analyzed...

Embodiment 3

[0099] Such as Figure 5 As shown, a gas turbine compressor control method, preferably, this control method can be activated when the gas turbine compressor is in a low-speed working condition, but when the gas turbine compressor is in other working conditions, this control method can also be used for control and adjustment . At the same time, it should be noted that the compressors of other turbomachines can also be regulated by this control method.

[0100] The compressor includes multi-stage moving blades and multi-stage stationary vanes, the multi-stage stationary vanes include multi-stage adjustable stationary vanes, and the angle of each adjustable stationary vane in the multi-stage adjustable stationary vanes is can be adjusted during the working process of the machine, and the control method includes the following steps:

[0101] S6, a step of establishing a flow calculation example of the compressor, wherein a flow calculation example of the compressor to be analyze...

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PUM

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Abstract

The invention provides a gas compressor control method and device. A gas compressor comprises multiple stages of movable blades and multiple stages of stationary blades, the multiple stages of stationary blades comprise multiple stages of adjustable stationary blades, and the angle of each stage of adjustable stationary blade in the multiple stages of adjustable stationary blades can be adjusted in the working process of the gas compressor. The control method comprises an adjustable stationary blade initial angle setting step, a load factor calculation step, a load factor comparison step and an adjustable stationary blade adjustment step. The invention further relates to the corresponding control device. According to the control method and device, by adjusting the angles of blades of all the stages of adjustable stationary blades, the front stages of loads of the gas compressor can be evenly increased, the margin of the gas compressor reaches the highest, and the optimal control rule of the multiple stages of adjustable stationary blades capable of adapting to different working conditions of the gas compressor is generated.

Description

technical field [0001] The invention relates to a method and device for controlling a gas compressor, in particular to a method and device for controlling multi-stage adjustable vanes of a gas turbine. Background technique [0002] As the technical indicators of modern heavy-duty gas turbines become more and more advanced, the inlet flow and stage load requirements of the compressor, one of the three major components of the gas turbine, are also getting higher and higher, which makes the internal flow of the compressor more complicated and more prone to stall and panting Vibration and other flow instability phenomena threaten the safety of gas turbine operation. [0003] For the operation of gas turbines under variable working conditions (mainly low-speed operation), due to the low speed, the tangential speed of the rotor blade rotation is insufficient, the work added by each stage of the compressor and the degree of gas compression are low, and the gas cannot reach the expe...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D27/00
CPCF04D27/00F04D27/002
Inventor 周国宇吴宏阙晓斌
Owner CHINA UNITED GAS TURBINE TECH CO LTD