Milling method of blade of high-temperature alloy whole blade ring

A high-temperature alloy, integral blade technology, applied in the field of aero-engines, can solve the problems of unreachable feed and design requirements, and achieve the effect of good surface quality

Active Publication Date: 2017-03-22
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to develop for the milling process of aero-engine superalloy integral leaf ring blades. For leaf ring parts, the blades are shielded from each other in the axial direction, and the distance between the blades is narrow. T

Method used

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  • Milling method of blade of high-temperature alloy whole blade ring
  • Milling method of blade of high-temperature alloy whole blade ring
  • Milling method of blade of high-temperature alloy whole blade ring

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Embodiment

[0029] The overall leaf ring part is made of superalloy material, the material grade is GH4169, the maximum outer diameter of the leaf ring part: Φ530mm; the minimum inner flow channel diameter: Φ460mm; the thickness of the part is 30mm; the maximum chord width of the blade: 40mm; the total number of blades: 130 pieces; the minimum distance between adjacent blades: about 9mm; the thickness of the inner and outer rings of the leaf ring is 2-5mm; the length of the blades is about 30-33mm; the connection between the blades and the inner and outer flow channels is RR2.5mm. The schematic diagram of the parts is shown in the figure below.

[0030] Follow the above steps to process:

[0031] Step 1: Formulate processing procedures

[0032] The milling process route of this type of integral leaf ring is: rough milling and slotting at the intake end → rough milling and slotting at the exhaust end → fine milling of the air inlet end profile and flow channel → fine milling of the exhaus...

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Abstract

The invention discloses a milling method of a blade of a high-temperature alloy whole blade ring. The method comprises following steps: firstly, a manufacturing procedure is selected, and the milling technology path of the whole blade ring comprises air inlet end rough milling slotting, exhaust end rough milling slotting, air inlet end blade type and flow way accurate milling and exhaust end blade type and flow way accurate milling; secondly, according to the length and the maximum thickness of the blade of the whole blade ring blade type, the machining allowance reserved for accurate milling after rough milling slotting is determined; thirdly, a tool is selected, wherein during rough milling, an end milling cutter of phi 6R0.5 to phi 6R1.5 is selected for machining, and during accurate milling, a taper ball head milling cutter with the shrinking neck is selected for machining; fourthly, cutting parameters are selected; fifthly, the accurate milling step is selected. Machining of the blade of the high-temperature alloy blade ring part is effectively achieved, the method can ensure that the machined part has the good surface quality and meets the design required form and location tolerance, and the method also can be applied to milling of complex curve deep cavities.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a milling method for high-temperature alloy integral leaf ring blades. Background technique [0002] Integral leaf ring parts are new structural parts used in aero-engines. The high-temperature alloy integral leaf ring parts are composed of three parts: inner ring, outer ring and blade. The inner ring and outer ring of the part are thin-walled structures, and the blade part is a typical The cavity structure, and the blades are shielded from each other when viewed in the axial direction, the space between the blades is narrow, the fillet radius R of the inlet and outlet edges of the blades is 0.1-0.2mm, the size and shape and position tolerance requirements of the blades and runners Strict, the processing process must adopt a suitable process method to ensure the part design requirements. This integral leaf ring blade milling method is aimed at this type of integral leaf rin...

Claims

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Application Information

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IPC IPC(8): B23C3/18
CPCB23C3/18B23C2215/44
Inventor 韩德印徐一鸣杨楠张莹吴军
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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