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Machining device and method for double-layer casing of aero-engine

A technology for aero-engines and processing devices, applied to aircraft parts, manufacturing tools, transportation and packaging, etc., can solve the problems of increased processing costs, low processing efficiency, and difficulty in realization, and achieve improved processing efficiency, convenient operation, and higher pass rate Effect

Inactive Publication Date: 2020-02-11
CHINA HANGFA GUIZHOU LIYANG AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The processing of double-layer casings, especially thin-walled barrel-type double-layer casings, is difficult to achieve by traditional machining methods, and the processing efficiency is low
For this kind of parts, although the processing requirements can be met by ordinary processing methods, this will inevitably increase the processing cost, the efficiency is low, and a series of problems caused by the deformation of the parts cannot be avoided.

Method used

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  • Machining device and method for double-layer casing of aero-engine
  • Machining device and method for double-layer casing of aero-engine
  • Machining device and method for double-layer casing of aero-engine

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Embodiment Construction

[0033] The technical solution of the present invention will be further described below in conjunction with the accompanying drawings, but the claimed protection scope is not limited to the description.

[0034] Such as Figure 1 ~ Figure 3 As shown, the aero-engine double-layer casing processing device includes an end face gland 1, an outer shell 2, an inner sleeve 3, a movable tension block 4, an air bag 5, a support rod 6, a support arm nut 7, a support arm 8, a connecting seat, a ball Head guide rod 9, inner hole fixed claw 10, outer column 11, transverse plug 12 and pressing plate 13.

[0035] Specifically, the shell 2 includes a cylindrical first shell, the lower end of the first shell is connected to the cylindrical second shell, the first shell is coaxial with the second shell and the outer diameter of the second shell is Greater than the outer diameter of the first casing, the outer diameter of the first casing is slightly smaller than the inner diameter of the double...

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Abstract

The invention discloses a machining device and method for a double-layer casing of an aero-engine. The device comprises an end surface gland, a shell, an inner sleeve, movable tensioning blocks, an air bag, a supporting rod, supporting arm nuts, supporting arms, a connecting seat, a ball head guiding rod, an inner hole fixing claw, an outer stand column, a transverse top head and a pressing plate.A turning and milling compound machining method is adopted, when an inner hole and an end surface are turned, the mode that an outer supporting is matched with the air bag for tensioning is adopted,and when an outer boss is milled, the mode that an inner supporting is matched with the air bag for tensioning is adopted; and according to the machining device, the high-quality and high-efficiency machining of the similar thin-wall double-layer casing can be achieved, and it is ensured that the circular degree of the casing meets the requirement.

Description

technical field [0001] The invention relates to a manufacturing method and device for a thin-walled double-layer casing in an aero-engine, in particular to a clamping and supporting method and device in casing processing. Background technique [0002] As the main component of the aero-engine, the casing is divided into integral ring casing, split ring casing, radial plate ring casing, etc. according to the structure. According to the material, it is divided into superalloy casing, titanium alloy casing, stainless steel casing, Aluminum alloy casings, etc., are divided into forging casings, casting casings, welding casings, sheet metal casings, etc. according to the manufacturing process; due to the complex structure, thin wall, and difficult processing of materials of advanced aero-engine casings, the structure is double-layer , the welding process is difficult, and the machining allowance is large. After the casing is processed, there are different degrees of residual stres...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P23/02B23P15/00
CPCB23P15/00B23P23/02B23P2700/01
Inventor 胡鹏唐源蔚
Owner CHINA HANGFA GUIZHOU LIYANG AVIATION POWER CO LTD
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