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Powder high-temperature alloy horizontal extrusion integrated sheath and manufacturing method thereof

A high-temperature alloy and sheathing technology, which is applied to the supporting components of blades, engine components, machines/engines, etc., can solve the problems of wasting powder superalloy materials, increasing extrusion resistance, and cracking of extruded rods, and achieves reduction Small waste, reduced extrusion resistance, enhanced welding strength

Pending Publication Date: 2020-12-15
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In order to effectively reduce the extrusion resistance, the method of adding a jacket on the surface of the hot isostatic pressing billet is currently adopted, but this method requires a lot of processing of the hot isostatic pressing billet, and the subsequent added jacket is easy to be compared with the hot isostatic pressing billet. There are gaps in the billet, but the extrusion resistance increases because the gas cannot be removed, resulting in cracking of the extruded bar
At the same time, the processing of the hot isostatic pressing billet will not only waste the powder superalloy material, but also cause the prolongation of the process cycle

Method used

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  • Powder high-temperature alloy horizontal extrusion integrated sheath and manufacturing method thereof
  • Powder high-temperature alloy horizontal extrusion integrated sheath and manufacturing method thereof
  • Powder high-temperature alloy horizontal extrusion integrated sheath and manufacturing method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0043] (1) Process the parts of the integrated sheath according to the drawings, wherein the diameter of the upper cover of the sheath is Φ343mm, the outer diameter of the outer wall of the sheath is Φ360mm, the inner diameter of the outer wall of the sheath is Φ333mm, the height of the outer wall of the sheath is 730mm, the diameter of the tail pad of the sheath is Φ360mm, and the outer diameter of the sheath is Φ360mm. Tail pad height 100mm;

[0044] (2) Clean each part of the processed bag with gasoline first, and then use acetone to clean until there are no obvious impurities visible to the naked eye in the acetone;

[0045] (3) Argon arc welding is used to weld the parts of the integrated sheath;

[0046] (4) Vacuum annealing is carried out on the sheath after welding at 600°C, and the annealing time is 16h;

[0047] (5) After annealing, in order to ensure the tightness of the bag, a leak detector is used to test the tightness of the bag. The leak rate should be 3×10 in ...

Embodiment 2

[0050] (1) Process the parts of the integrated sheath according to the drawings, wherein the diameter of the upper cover of the sheath is Φ403mm, the outer diameter of the outer wall of the sheath is Φ420mm, the inner diameter of the outer wall of the sheath is Φ393mm, the height of the outer wall of the sheath is 620mm, the diameter of the tail pad of the sheath is Φ420mm, and the outer diameter of the sheath is Φ420mm. Tail pad height 150mm;

[0051] (2) Clean each part of the processed bag with gasoline first, and then use acetone to clean until there are no obvious impurities visible to the naked eye in the acetone;

[0052] (3) Argon arc welding is used to weld the parts of the integrated sheath;

[0053] (4) Vacuum annealing is carried out on the sheath after welding at 600°C, and the annealing time is 16h;

[0054] (5) After annealing, in order to ensure the tightness of the bag, a leak detector is used to test the airtightness of the bag. The leak rate should be 5×10 ...

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Abstract

The invention belongs to the technical field of powder high-temperature alloy, and relates to a powder high-temperature alloy horizontal extrusion integrated sheath and a manufacturing method thereof.The integrated sheath consists of a powder nozzle, a sheath upper cover, a sheath outer wall and a sheath tail pad, and all the components are made of stainless steel and are welded; and vacuum annealing is carried out after welding, so that the sealing performance of the sheath is guaranteed, and air leakage of the sheath in a powder treatment and hot isostatic pressing implementation process isprevented. The sheath can be used as a powder sheath, and hot isostatic pressing is carried out after treated powder is filled, so that densification of the high-temperature alloy powder is realized;the sheath can also be used as a sheath of a subsequent hot extrusion process, a heat preservation effect is achieved in the extrusion process, temperature drop of a high-temperature alloy ingot blank body is reduced, and the extrusion resistance is reduced; the sheath tail pad is additionally arranged, and can be used as an extrusion blank for pressing, so that the waste of the powder high-temperature alloy is reduced; and meanwhile, the integrated design is adopted to simplify the manufacturing process of the sheath, so that the cost is reduced, and meanwhile, the extrusion stability is improved.

Description

technical field [0001] The invention belongs to the technical field of powder superalloy, and relates to a powder superalloy powder molding and hot extrusion integrated sheath and a manufacturing method thereof. Background technique [0002] Turbine disk is one of the key parts of gas turbine engine. Its working conditions are very harsh. It works under high temperature, high speed, high stress, and high-speed airflow, and bears high centrifugal load, thermal load, aerodynamic load, vibration load, and corrosion and oxidation of environmental media. The combined effect of the mechanical stress of the cycle of starting, accelerating, cruising, decelerating, stopping, etc. and the thermal stress caused by the temperature difference. Each part of the turbine disk bears different alternating loads, and its working conditions directly affect the performance, reliability, safety and durability of the engine. With the development of engines with high thrust-to-weight ratio, high ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B22F7/08B22F3/15B22F3/24F01D5/02
CPCB22F7/08B22F3/15B22F3/24F01D5/02B22F2003/248
Inventor 彭子超汤悦王旭青
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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