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Forming method of high-temperature alloy fairing with reinforcing rib structure

A superalloy and reinforcing rib technology is applied in the forming field of superalloy fairing parts to achieve the effects of controlling welding deformation, improving forming accuracy and qualification rate

Active Publication Date: 2019-12-13
BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP
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Problems solved by technology

[0004] The invention proposes a method for forming a high-temperature alloy fairing with a rib structure to solve the technical problem of how to form a high-temperature alloy fairing with a rib structure with high quality

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  • Forming method of high-temperature alloy fairing with reinforcing rib structure
  • Forming method of high-temperature alloy fairing with reinforcing rib structure
  • Forming method of high-temperature alloy fairing with reinforcing rib structure

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Embodiment Construction

[0029] In order to make the purpose, content and advantages of the present invention clearer, the specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0030] This embodiment proposes a method for forming a superalloy fairing with a ribbed structure, the forming method includes the following steps:

[0031] S1, such as figure 1 As shown, the materials of skin 1, longitudinal rib 2 and ring rib 3 are all high-temperature alloys with a thickness of 1mm. All longitudinal ribs 2 are designed as Ω-shaped, and ring rib 3 is divided into the left section of ring rib 2-1 , ring rib middle section 2-2, ring rib right section 2-3, ring rib angle piece 2-4 (four). In this split method, the ring rib is broken at the bottom fillet, but it does not affect the strengthening effect of the ring rib. Among them, the left, middle, and right sections of the ring reinforcement are U-shap...

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Abstract

The invention provides a forming method of a high-temperature alloy fairing with a reinforcing rib structure. For forming difficulties that a high-temperature alloy board is high in hardness, large inspringback, difficult in cold shape correcting and the like, through novel and reasonable longitudinal ring reinforcing rib design and dismounting, a ring rib forming tool is not needed, the main connecting manner of reinforcing ribs and a skin is changed into spot welding with small welding deforming, and spot welding with the small deforming is greatly applied to replace argon arc welding so asto ensure part precision. A cold pressing and hot correcting machining method is adopted for precisely forming the fairing outer skin, and the reinforcing rib structure in the fairing is wholly arranged. Through control over the spot welding sequence and the welding backward deformation method of adding supporting rods on portions, need to be subjected to argon arc welding connection, of parts, the welding deforming can be effectively controlled, the forming precision and the yield of the product can be obviously improved, and the high-temperature alloy fairing with the reinforcing rib structure is finally and precisely formed.

Description

technical field [0001] The invention belongs to the technical field of composite precision forming, and specifically relates to a structure with complex ribs suitable for forming skins of high-temperature alloys with variable cross-section arc segments, forming internal criss-cross ribs, skin spot welding, and argon arc welding. The forming method of superalloy fairing parts. Background technique [0002] With the development of hypersonic aircraft, the engine fairing not only bears the comprehensive environment of outflow aerodynamic force, heat, vibration and noise, but also bears the strong noise and vibration from the engine. Therefore, the control requirements for the shape accuracy of the fairing are high (generally, the contour is within 0.4mm); the heat resistance is high, and the material can only be high-temperature alloy; the strength and weight reduction are high, resulting in a thin outer skin at the same time. The inside of the fairing is densely covered with ...

Claims

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Application Information

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IPC IPC(8): B23P15/00B64C7/00
CPCB23P15/00B64C7/00
Inventor 马向宇朱冬妹高海涛王斌师利民刘章光
Owner BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP
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