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Method for improving blade profile correcting and machining precision of integrally cast impeller of gas compressor

A technology of overall casting and machining accuracy, applied in the direction of climate sustainability, efficient propulsion technology, sustainable transportation, etc., can solve the problems of cumulative error, the inability to accurately calibrate a single blade shape, and the inability to quantify the comparison and calibration, etc. Achieve the effect of improving calibration and machining accuracy

Active Publication Date: 2022-02-15
SICHUAN AEROSPACE ZHONGTIAN POWER EQUIP CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Existing solutions generally use templates to find out, compare and calibrate one by one. Due to the limited number of samples, the comparison and calibration cannot be quantified, so a single leaf type cannot be accurately calibrated, and there is still the problem of cumulative errors.

Method used

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  • Method for improving blade profile correcting and machining precision of integrally cast impeller of gas compressor
  • Method for improving blade profile correcting and machining precision of integrally cast impeller of gas compressor
  • Method for improving blade profile correcting and machining precision of integrally cast impeller of gas compressor

Examples

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Embodiment 1

[0039] Such as figure 1 As shown, the present invention discloses a method for improving the type correction and machining accuracy of integrally cast impeller blades of a compressor, including:

[0040] Step S1: Adopting the airfoil shape of precision cast impeller castings without margin to ensure that the airfoil shape meets the requirements of the blade blank;

[0041] Step S2: According to the conventional method of aligning the impeller according to the template, roughly machine the journal, inner hole, and hub end face of the impeller as a rough reference, and then roughly machine the axial length of the impeller, the inner hole of the hub, and the end face of the hub, and reserve them on the impeller. Out of the corresponding processing allowance;

[0042] Step S3: Machining anchor points and scoring lines for positioning at the part of the machining allowance;

[0043] Step S4: Use a high-precision 3D scanner to scan the impeller obtained in step S3 to obtain 3D poi...

Embodiment 2

[0062] Such as Figure 2 to Figure 3 As shown, a specific embodiment,

[0063] The compressor of a micro engine is an integral impeller, the design requires that the error of the profile is less than 0.05mm, and it adopts precision investment casting.

[0064] Process the impeller according to the processing method in Example 1,

[0065] Preliminary machining is performed on the impeller length, inner hole of the hub, end face of the hub and other dimensions, and the corresponding allowance is reserved.

[0066] A hole with a depth of about 1mm and a diameter of about 2mm is machined on the end surface of the inlet side of the pre-processed hub (after the completion of the blade shape calibration and polishing, the hole is finally processed and removed), and the hole is used as a positioning anchor point; the origin of the coordinate system O is The intersection point of the inlet side end surface of the hub and the axis of the impeller, the X-axis is the axis of the impelle...

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Abstract

The invention discloses a method for improving blade profile correcting and machining precision of an integrally cast impeller of a gas compressor, and relates to the technical field of machining of integrally cast impellers of aviation gas compressors, wherein the method comprises the steps: performing rough machining by adopting a conventional method of allowance-free precision casting and blade profile alignment according to a sample plate, and machining anchor points and scribed lines for positioning on an impeller blank; scanning three-dimensional point cloud data of the impeller, importing the three-dimensional point cloud data into three-dimensional software, comparing the three-dimensional point cloud data with a coordinate system established by a theoretical impeller three-dimensional solid model as a reference, finding out offsets of anchor points and scribed lines and blade profile deviation distribution, identifying the blade through the anchor points and the scribed lines, correcting the blade needing to be corrected according to the comparison result, polishing and repairing the blade, and reducing blade profile deviation; and mounting the impeller blank in a machining center, machining a shaft or a hole of a hub, and then performing fine reference machining. According to the method, the blade profile of the integrally cast impeller of the gas compressor is closer to a theoretical blade profile, and meanwhile, the dynamic unbalance amount generated by blade shape difference and uneven blade distribution is reduced, so that the overall performance of an engine is improved.

Description

technical field [0001] The invention relates to the technical field of machining an integral cast impeller of an aviation compressor, in particular to a method for improving the profile and machining accuracy of an integral cast impeller of an air compressor. Background technique [0002] As the power of unmanned aerial vehicle, ground power (such as distributed gas turbine power station), auxiliary power (such as starter), micro-miniature aero-engine has been widely used in many fields of military and civilian use. [0003] The integral cast impeller of the compressor is a key part of the miniature aero-engine, and the manufacturing accuracy of the blade profile has a great influence on the performance of the engine. Even for the integral impeller produced by precision casting, the error between the profile of the blade profile and the theoretical profile is usually not less than 0.1mm. If the precision of the blade profile is improved by improving the casting mold, the cos...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/02
CPCB23P15/02Y02T50/60
Inventor 李子华刘颖肖志强刘瓒何国忠龚方楷
Owner SICHUAN AEROSPACE ZHONGTIAN POWER EQUIP CO LTD
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