Gas turbine compressor casing anti-surge structure and surge margin evaluation method thereof

A gas turbine, surge margin technology, applied in the direction of machines/engines, liquid fuel engines, mechanical equipment, etc., can solve the problems of small increase in the axial velocity of the exhaust section and small air intake in the intake section, and achieve Reduce the effect of increasing the air volume, improving the flow state, and reducing the angle of attack

Inactive Publication Date: 2021-01-01
NAVAL UNIV OF ENG PLA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The main function of compressor casing treatment is to reduce the flow rate at the stall point, thereby increasing the surge margin of the compressor. However, in the process of casing treatment in the existing casing structure, there is an air intake in the intake section. Smaller, the increase in the axial velocity of the exhaust section is small;

Method used

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  • Gas turbine compressor casing anti-surge structure and surge margin evaluation method thereof
  • Gas turbine compressor casing anti-surge structure and surge margin evaluation method thereof
  • Gas turbine compressor casing anti-surge structure and surge margin evaluation method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0088] The main function of the treatment of the compressor case is to reduce the flow rate at the stall point, thereby increasing the surge margin of the compressor. In this embodiment, the analysis and calculation of the treatment case of the prototype machine are carried out to analyze the treatment of different structural forms of the case. The performance effect is evaluated by taking the surge margin improvement as the evaluation index of the casing handling performance:

[0089] In the formula, π and G represent the total pressure ratio and flow rate, respectively, and the subscripts s and 0 represent the near-stall point and working point of the casing, respectively;

[0090]In order to calculate the surge margin of the above-mentioned case processing expansion stability structure, this embodiment designs a method for evaluating the surge margin of the anti-surge structure of the gas turbine compressor casing, and the anti-surge structure of the gas turbine compressor...

Embodiment 2

[0127] Example 2: Calculate the result value of Y+ value and detect y + Whether the value of is between 0 and 10, judge the feasibility of the grid division method in Step 2 of this evaluation method:

[0128] (1) The calculation results show that most of the area y on the wall surface of this method + + <5, the total number of three-dimensional grids of the impeller group is 18 million, and the total number of grid blocks is 221. After the grid quality inspection, the grid parameters are all within the reasonable value range. The inspection results are as follows:

[0129] Table 1.1 3D Mesh Quality Check

[0130]

[0131] (2) further calculate the result value of the Y+ value of the method for gas turbine compressor casing anti-surge structure surge margin of the present invention to calculate, whether the value of detection y+ is between 0~10, judge the feasibility of this evaluation method: pass Figure 10 It can be seen from the Y+ value distribution cloud diagram sh...

Embodiment 3

[0132] Embodiment 3: After calculating the surge margin of the compressor working under the design working conditions in step S402 of Embodiment 1, it also includes using the Y+ value distribution, entropy increase distribution and relative Mach number distribution for the evaluation method. Feasibility further verification process, including:

[0133](1) calculate for the result value of Y+ value, concrete process and result are as shown in above-mentioned embodiment 2 (as Figure 10 shown), it proves that this evaluation method meets the calculation requirements;

[0134] (2) Utilize the parameter setting described in this method to simulate the result value of entropy distribution, as can be seen, when the meridian flow surface, casing processing and meridian flow channel area in the calculation domain divided by the present invention are working, Such as Figure 12 As shown, all of them produced entropy increase, through Figure 12 It can be seen from the simulation res...

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Abstract

The invention discloses a gas turbine compressor casing anti-surge structure and a surge margin evaluation method thereof. The gas turbine compressor casing anti-surge structure comprises a compressorcasing, wherein a casing treatment section is arranged on the front portion of the compressor casing, the casing treatment section comprises an anti-flow-loss section inner cavity, an anti-flow-losssection inner ring is arranged on the inner side of the anti-flow-loss section inner cavity, an axial chute is formed in the anti-flow-loss section inner ring and communicates with a backflow cavity in the anti-flow-loss section inner cavity, and a radial baffle is arranged in the anti-flow-loss section inner cavity; the axial chute rotates by 90 degrees along the radius line of the circle where the axial chute is located, is parallel to the blade chord line of a rotor blade, and rotates by 45 degrees along the axis of the circle where the axial chute is located; by changing the structure of the axial chute, the air inlet amount and the air inlet flowing condition are changed; and meanwhile, an exhaust section is optimized, the axial speed is increased, the flow coefficient is increased, the flowing state with the too large top attack angle is improved, stability expansion is effectively carried out, and the beneficial effects of effectively reducing the increased air amount, reducingthe attack angle at the blade tip of a movable blade and reducing the flow of a stall point are achieved.

Description

technical field [0001] The invention relates to the technical field of fluid mechanical compressors, in particular to a gas turbine compressor casing anti-surge structure and a surge margin evaluation method thereof. Background technique [0002] Axial fan / compressor, as a widely used fluid machine, how to improve its working stability has always been a hot and difficult point of calculation. Internationally, various explorations have been made on the stability expansion measures to improve the stability margin, mainly including adjustable Blades, casing treatment (circumferential grooves and axial slots), tip jets, large and small blades, etc.; casing treatment, as an effective passive stabilization measure, appeared in the 1960s because of its simple structure and easy installation , the expansion effect is good, and it has been widely calculated and applied; for many years, the expansion mechanism and design method of casing processing have been a hot and difficult proble...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/52F04D29/66G06F30/23
CPCF04D29/522F04D29/526F04D29/667G06F30/23
Inventor 李钰洁贺星刘永葆余又红邹凯凯张筠松
Owner NAVAL UNIV OF ENG PLA
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