Groove-type end wall treatment method for axial flow compressor
A technology of an axial flow compressor and a treatment method, which is applied to components, mechanical equipment, machines/engines, etc. of pumping devices for elastic fluids, and can solve problems affecting the economy and stability of gas turbines, compressor performance degradation, blade Problems such as temporary or permanent increase of tip clearance, to reduce sensitivity, weaken strength, and reduce leakage loss
Active Publication Date: 2018-09-07
HUANENG POWER INT INC +1
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Problems solved by technology
However, the performance of the compressor is highly sensitive to the blade tip clearance, and the increase of the clearance during operation usually leads to the decline of the performance of the compressor.
During the actual service process, the blade tip clearance may increase temporarily or permanently, thus affecting the economy and stability of gas turbine operation
Method used
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Embodiment Construction
[0023] The present invention will be further described below with reference to the accompanying drawings and embodiments.
[0024] like Figure 4 to Figure 6 , The invention provides a groove end wall treatment method for an axial flow compressor, which determines the axial range of the end wall treatment through the peak efficiency and the distribution of the axial component of the tip leakage flow velocity in the near-stall condition, and determines the end wall treatment. A number of sawtooth circumferential grooves are provided in the treatment range to reduce the sensitivity of the compressor efficiency to tip clearance by reducing leakage flow directed upstream.
[0025] Take the first stage rotor of a gas turbine high-pressure compressor as an example.
[0026] Part of the design parameters of the compressor rotor are shown in Table 1.
[0027] Table 1 Design parameters of the first-stage rotor of a gas turbine high-pressure compressor.
[0028]
[0029] The groov...
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The invention discloses a groove-type end wall treatment method for an axial flow compressor. The axial arrange of end wall treatment is confirmed through peak efficiency and distribution of blade tipleakage flow speed axial component in a near-stall working condition, and a plurality of zigzag circumferential grooves are formed in the treatment range. Sensitivity of compressor efficiency to blade tip clearances is reduced by reducing leakage flow pointing toupstream.Through the groove-type end wall treatment method, the sensitivity of the compressor efficiency to the blade tip clearances canbe lowered. The groove-type end wall treatment method for the axial flow compressor uses the peak efficiency and the distribution of the blade tip leakage flow speed axial component in the near-stallworking condition to confirm the treatment range, the zigzag circumferential grooves are formed in the treatment range, the leakage flow flowing upstream is reduced, so that leakage loss is reduced,the compressor efficiency is maintained or even enhanced in a large clearance condition; and meanwhile, compressor margin is seldom affected.
Description
technical field [0001] The invention belongs to the technical field of impeller machinery, and in particular relates to a groove end wall treatment method for an axial flow compressor, which is used for reducing the clearance sensitivity of the blade tip of the axial flow compressor of a gas turbine. Background technique [0002] The flow process in the gap region of the gas turbine compressor is very complex, and the loss caused by the gap flow accounts for a large proportion of the total energy loss of the bucket and compressor stage. The performance of the compressor is highly sensitive to the tip clearance, and the increase of the clearance during the operation usually leads to the decline of the performance of the compressor. In the actual service process, the tip clearance may increase temporarily or permanently, thus affecting the economy and stability of gas turbine operation. [0003] The end wall treatment technology is an early research and successful application...
Claims
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IPC IPC(8): F04D29/52F04D29/66
CPCF04D29/526F04D29/667
Inventor 段静瑶肖俊峰高松李园园蔡柳溪于飞龙上官博
Owner HUANENG POWER INT INC