Optimal Design and Processing Method of Centrifugal Impeller Blade Inlet Leading Edge
A technology of optimized design and centrifugal impeller, which is applied in the field of mechanical processing, can solve the problems of unfavorable and rare leading edge of the blade inlet, and achieve the effects of small thickness, improved precision and efficiency, and large area
Active Publication Date: 2019-02-05
XI AN JIAOTONG UNIV
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Problems solved by technology
However, most of the research at this stage is focused on the design and processing of the entire blade surface, and the special research on the leading edge of the blade inlet is extremely rare. It is particularly unfavorable to improve the overall performance of the aircraft and improve the overall level of major equipment in the fields of aerospace, automobiles, ships, and petrochemicals.
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[0041] Taking the leading edge of the impeller blade of a centrifugal compressor as an example, the optimized design and processing method of the leading edge of the centrifugal impeller blade of the present invention will be described in detail with reference to the accompanying drawings:
[0042] 1. Build a blade model
[0043] See figure 1 As shown, the blade data is input into the computer to complete the modeling of the target impeller blade.
[0044] 2. Numerically express blades in the form of bicubic non-uniform rational B-spline matrix
[0045] Define the blade S(u,v) from the top to the root as the v direction and the blade inlet to the blade outlet as the u direction, then the blade S(u,v) is defined in the form of a bicubic non-uniform rational B-spline (NURBS) matrix as:
[0046] S(u,v)=vC i,1 (u)+(1-v)C i,n (u); (0≤u≤1,0≤v≤1,i=1,2,...,m)
[0047] Where U=(1,u,u 2 ,u 3 ); V=(1,v,v 2 ,v 3 ); C i,1 (u) and C i,n (u) is the space curve of the tip and root of the blade.
[0048...
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The invention discloses an optimization design and machining method of a centrifugal impeller blade inlet front edge. The method, based on the centrifugal compressor solid modeling and five-coordinate processing technology, designs different types of impeller blade inlet front edge molded lines and obtains the optimal blade inlet front edge curved surface through optimization; in the rough machining stage, the combined machining of the blade inlet front edge curved surface with the blade pressure surface and suction surface is realized by taking the machining efficiency as the primary and taking the safe tool feeding and the five-coordinate device reverse gap into account; and in the finishing stage, the rolling and milling of the blade inlet front edge curved surface is realized by taking the machining precision as the primary and taking the machining errors and blade vibration into account. The method combines the mathematic modeling and numerical control machining to realize the numerical control precision machining of complex components having large area, small thickness and distorted space such as the centrifugal compressor impeller blade inlet front edge curved surface, thereby greatly improving the precision and efficiency of the precision machining of power equipment in modern equipment industries.
Description
Technical field: [0001] The invention belongs to the field of mechanical processing, and specifically relates to an optimized design and a processing method of the inlet leading edge of a centrifugal impeller blade. Background technique: [0002] As an important equipment component widely used in aerospace, automobile, ship, petrochemical and other fields, the design, optimization and processing of centrifugal compressors are the key technologies for the power performance of equipment in these fields. The manufacturing technology level of these equipment products is a key indicator that reflects a country's manufacturing capability. [0003] The centrifugal compressor airflow channel composed of space-twisted centrifugal compressor impeller blades can control the airflow trajectory during the entire airflow passing through the centrifugal compressor impeller, and convert mechanical energy into controllable gas pressure, speed, etc. through rotation. Aerodynamics. At present, five...
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IPC IPC(8): G05B19/19
CPCG05B19/19G05B2219/35349Y02P90/02
Inventor 樊宏周席光王伟
Owner XI AN JIAOTONG UNIV