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Optimal Design Method for Transition Channel of High and Low Pressure Compressor

A technology for transition flow channel and optimized design, which is applied in calculation, special data processing applications, instruments, etc., can solve the problem of large flow loss in the transition flow channel of the compressor, and achieve the effect of reducing flow loss and total pressure loss coefficient

Inactive Publication Date: 2018-02-02
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0005] In order to overcome the shortcomings of the large flow loss of the compressor transition channel designed by the existing compressor transition channel design method, the present invention provides an optimal design method for the high and low pressure compressor transition channel

Method used

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  • Optimal Design Method for Transition Channel of High and Low Pressure Compressor
  • Optimal Design Method for Transition Channel of High and Low Pressure Compressor
  • Optimal Design Method for Transition Channel of High and Low Pressure Compressor

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Embodiment Construction

[0033] refer to Figure 1-2 . The specific steps of the method for optimizing the design of the high and low pressure compressor transition channel of the present invention are as follows:

[0034] According to the given initial constraint conditions of one-dimensional design, the casing and hub profile of the compressor transition channel are respectively constructed by two 4th-order Bezier curves with 5 control points, and the parametric equation of each curve for

[0035]

[0036] In the formula, is the binomial coefficient, is the Bernstein polynomial; m is the order of the polynomial; t is the control parameter of the curve, and its value ranges from 0 to 1; x i is the abscissa of the control point; y i is the vertical coordinate of the control point.

[0037] Superimpose the designed support plate with the above-mentioned newly generated compressor transition flow channel.

[0038] Randomly change the coordinates of the control points within an appropriate ra...

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Abstract

The invention discloses an optimal design method for a high-low pressure compressor transition flow channel, which is used to solve the technical problem of large flow loss in the compressor transition flow channel designed by the existing compressor transition flow channel design method. The technical solution is to preliminarily determine the geometric shape of the transition flow channel of the compressor through the existing design method, and then use the Bezier curve to construct the end wall profile line equation that meets the initial design results, and further superimpose the constructed support plate on this basis . Then the geometric parameters of the casing and the hub are randomly generated, and a new profile is generated. Then the through-flow is used to solve the performance parameters of the flow field. Finally, taking the total pressure loss coefficient at the outlet of the support plate as the optimization objective function, and taking the gradient of the static pressure recovery coefficient along the hub as the constraint condition to be smaller than the gradient of the pressure recovery coefficient before optimization, the niche genetic algorithm is used to optimize until it evolves to a given generation until. Since the Bezier curve is used to construct the profile equation of the transition channel of the compressor, the flow loss of the designed transition channel of the compressor is reduced.

Description

technical field [0001] The invention relates to a method for designing a transitional channel of a compressor, in particular to an optimal design method for a transitional channel of a high-low pressure compressor. Background technique [0002] The compressor transition channel is an important part of the aero-engine compression system. The air compressed by the low-pressure compressor enters the high-pressure compressor through the compressor transition channel, and then is further compressed. Therefore, the quality of its design directly affects the performance of its downstream high-pressure compressor, and also affects the performance of its upstream low-pressure compressor. With the development of aero-engine design technology, the thrust-to-weight ratio and efficiency have been improved, the boosting capacity of aero-engine compressors has been continuously improved, and the axial offset between the low-pressure compressor and the high-pressure compressor has become la...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 吴虎侯朝山杨金广刘昭威
Owner NORTHWESTERN POLYTECHNICAL UNIV
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