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Modeling method of single-stage fan/compressor hub with double wave structure

A wave structure, compressor technology, applied in the direction of machine/engine, mechanical equipment, liquid fuel engine, etc., can solve the problem of consuming large computing resources and time

Active Publication Date: 2018-11-23
成都飞擎航空科技有限公司
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  • Claims
  • Application Information

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Problems solved by technology

These two methods start purely with mathematical methods. The shape of the hub designed by the constructor method may not be able to achieve the optimal effect, while the optimization method of adjusting the control lattice needs to consume a lot of computing resources and time, and neither can be established from the physical essence. reasonable design method

Method used

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  • Modeling method of single-stage fan/compressor hub with double wave structure
  • Modeling method of single-stage fan/compressor hub with double wave structure
  • Modeling method of single-stage fan/compressor hub with double wave structure

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Embodiment Construction

[0031] The following is an example to illustrate the specific implementation of the present invention. The above-mentioned method is used to redesign the shape of the hub of a stage in a certain compressor, and the effect of the optimization method is verified by numerical simulation.

[0032] The compressor is the first stage of a high-pressure compressor, the design speed is 14359rpm, the design flow rate is 88kg / s, the design pressure ratio is 1.92, the design efficiency is 0.90, the number of rotor blades is 53, the number of stator blades is 88, and the number of blades The geometry and shape of the flow channel are known.

[0033] 1. Calculate the new radial coordinates according to step (1)

[0034] Starting from the front edge of the rotor, a cross section is divided every 2mm axial distance to obtain the shape of the cross section, and a total of 45 independent closed section profiles are obtained. The 22nd section is now used to illustrate the calculation method of ...

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Abstract

The invention relates to a double-wave-structure hub modeling method for a single-stage fan / air compressor. The metal blockage effect of a rotor blade row and a stator blade row of the single-stage fan / air compressor is considered in the design process of a hub. The control parameters such as the blade tip weighting function, the blade root weighting function, the maximum concave position forward movement amount, the front end magnification ratio, the rear end magnification ratio and the smoothness parameter are introduced. A double-wave structure hub shape is formed after modeling. The control parameters are adjusted through an overall optimization algorithm in the modeling process. The hub curve when the heat insulation efficiency is highest is the optimized hub curve. The end area flow of the hub after optimization is improved. The flow capacity is increased. The work range of the fan / air compressor is widened. The overall performance of the fan / air compressor is improved.

Description

technical field [0001] The invention relates to a single-stage fan / compressor double-wave structure hub molding method, which belongs to the field of optimized design of the end wall of the aviation gas turbine compression system. Background technique [0002] The improvement of the thrust-to-weight ratio of the engine is the main symbol of the improvement of the technical level of the engine, which can be realized mainly through the following two technical approaches: one is to increase the thrust of the engine under the premise of keeping the total weight unchanged; the other is to increase the engine thrust under the premise of keeping the total thrust unchanged. Reduce engine weight. Either way, it all boils down to a significant increase in the aerodynamic load on the compression system. With the increase of the compressor stage load, the phenomenon of flow separation and end blockage will be more prominent under the higher reverse pressure gradient, which will lead to...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/26
CPCF04D29/26F04D29/329
Inventor 李秋实李志平潘天宇张亚飞
Owner 成都飞擎航空科技有限公司
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