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Two-dimensional blade modeling method for directly controlling channel

A technology for controlling channels and blades, applied in special data processing applications, instruments, electrical and digital data processing, etc., can solve problems such as poor effectiveness, low design efficiency, and poor channel shape control capabilities, to improve flexibility and design. The effect of efficiency

Active Publication Date: 2019-07-26
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0004] The purpose of the present invention is to overcome the technical defects that the existing modeling methods in the field of fan and compressor design are not strong in controlling the channel shape, resulting in low design efficiency and poor effectiveness. Dimensional cross-section modeling, a two-dimensional blade modeling method that directly controls the channel is proposed, starting from the flow characteristics of the channel, using the conventional multi-arc shape to construct the suction surface; based on the constructed suction surface, calculate and adjust the control channel width distribution law; Based on the suction surface, superimpose the thickness of the channel to construct part of the pressure surface; complete the pressure surface and the edge area profile, and construct the two-dimensional blade profile of the fan and compressor

Method used

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  • Two-dimensional blade modeling method for directly controlling channel
  • Two-dimensional blade modeling method for directly controlling channel
  • Two-dimensional blade modeling method for directly controlling channel

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Embodiment 1

[0052] This example describes the specific implementation of a two-dimensional blade modeling method using a direct control channel according to the present invention.

[0053] The application scenario of this embodiment is that in an axial-flow aeroengine whose design state is subsonic cruising, the two-dimensional span section design at the root of the first-stage moving blade of the compressor is designed, the inlet Mach number is 0.85, and the pressure ratio is 1.3. The original blade shape adopts the conventional design method of double-arc middle arc + thickness distribution, and does not pay attention to the shape of the channel between the blades and the flow performance of the channel. Multiple geometric shapes are required to obtain a cross-sectional shape with better aerodynamic performance. In this embodiment, according to the subsonic flow condition, the spanwise position of the blade and the input parameters, the airfoil is reconstructed from the perspective of di...

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Abstract

The invention relates to a two-dimensional blade modeling method for directly controlling channel, and belongs to the technical field of aviation impeller machine design. A two-dimensional blade modeling method for directly controlling channel is provided for two-dimensional spanwise section modeling of blades of an axial-flow aero-engine fan and a compressor part, the method comprises steps of constructing a suction surface and an edge area molded line by utilizing a conventional multi-arc model, and calculating and adjusting a channel width distribution rule from the channel flow characteristic; by taking the suction surface as a reference, superposing the channel thickness to construct a part of pressure surface; and then complementing the rest of the pressure surfaces by using a cubiccurve to complete the two-dimensional blade profile construction. According to the method, the problem of irregular distribution of a plurality of sections of channel areas in a blade modeling methodof a median camber line + thickness is solved; the flexibility of channel area control is improved; the design efficiency of two-dimensional blade profiles in the compressor and the fan is improved; the channel diffusion capability can be directly evaluated, and the circulation performance of the designed blade profile is pre-judged.

Description

technical field [0001] The invention relates to a two-dimensional blade modeling method for directly controlling passages, and belongs to the technical field of aviation turbine design. Background technique [0002] The increase in the thrust-to-weight ratio requirements of aero-engines puts forward higher requirements for the stage pressure ratio and stage efficiency of the core components of the fan and compressor. In order to improve the performance of the fan and compressor, it includes characteristics such as low loss and a large range of available angle of attack. , it is a feasible and effective way to improve the quality of two-dimensional airfoil design. The two-dimensional blade modeling method directly borrows from the outflow airfoil in the early stage, and uses the "middle arc + thickness" modeling method such as single arc, double arc, and multi-arc, and the controllable diffusion blade modeling method, all from the blade geometry Starting from the shape, dire...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/17G06F2119/06G06F30/20
Inventor 李鑫蒙童桐季路成
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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