Method for partial heat treatment of aero-engine large part after repair welding
An aero-engine, local heat treatment technology, applied in heat treatment furnaces, heat treatment equipment, heat treatment process control, etc., to achieve the effect of eliminating thermal stress, avoiding surface oxidation of parts, and avoiding excessive deformation
Active Publication Date: 2017-05-10
CHENGDU ENGINE GROUP
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Problems solved by technology
[0004] Aiming at the technical status and deficiencies of heat treatment after repair welding and repairing of large-scale parts of aero-engines, the purpose of this invention is to provide a new heat treatment method for local repair welding of large-scale parts of aero-engines to solve the problem of large-scale parts of aero-engines. Heat treatment after repair welding of local defects of components
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Embodiment 1
[0015] This embodiment provides the method for partial repair welding heat treatment of large parts of aero-engines, the heating equipment used in it is as attached figure 1 And attached figure 2 As shown, it consists of a vacuum furnace 1, a vacuum pump 3 connected to the vacuum furnace through pipelines, and a control cabinet 7. The housing of the vacuum furnace is provided with an argon input connection 6 and an exhaust connection 2 connected to an argon source. The vacuum furnace is provided with a stage 4 for placing parts 8 to be heat treated. The part 8 to be processed is an impeller disk. The treatment method is: place the parts to be heat treated on the stage in the vacuum furnace, and evacuate the pressure in the vacuum furnace to 6.65×10 -2 Below Pa, and maintain the vacuum degree, use the heating belt 2 to heat the partial repair welding area of the parts to be heat treated to 704°C, and control the heating area (11) to extend outward from the repair welding a...
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The invention discloses a method for partial heat treatment of an aero-engine large part after repair welding. The adopted technical measures comprise the following steps that the part to be subjected to the heat treatment is placed on an objective table in a vacuum furnace; pressure in the vacuum furnace is pumped below 6.65x10<-2>Pa, and the vacuum degree is maintained; a partial repair welding area of the part to be subjected to the heat treatment is heated to 620-720 DEG C for 120-480 minutes through an electrical heating belt, then cooled along with the furnace to the indoor temperature, and the heat treatment of partial repair welding of the part to be subjected to the treatment is finished; in the process of heating treatment, a temperature controlling galvanic couple, a load recording galvanic couple and a heat monitoring galvanic couple which are connected with a recording instrument are used for controlling the temperature of the repair welding area, recording a heating load and monitoring the temperature of an external heating area correspondingly; an overtemperature alarm galvanic couple connected with an overtemperature alarm instrument is used for conducting overtemperature alarming; and a temperature and heat controlling galvanic couple connected with the recording instrument and a controller is used for controlling the temperature of the repair welding area.
Description
technical field [0001] The invention relates to a repairing and remedial technology for local defects of large parts of aero-engines, and more specifically relates to a method for heat-treating repairing welding areas of local defects of large parts of aero-engines. Background technique [0002] The large parts of the aero-engine are all made of titanium alloy, which is machined from cast blanks. From time to time in the production practice of aero-engines, such a situation often occurs, that is, during the machining process of large parts, after finishing to the surface of the part with the size of the design drawing, local casting defects appear on the surface of the part. If the whole part is scrapped, it will Bringing tens of thousands of economic losses, in order to save the loss, the usual practice is to repair the defective parts, but repairing the defective parts of the parts will generate thermal stress in the repaired welding part area, and the thermal stress will ...
Claims
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IPC IPC(8): C21D9/50C21D1/773C21D11/00
CPCC21D1/773C21D9/50C21D11/00
Inventor 罗毅乔雷罗啸姜涛王宁
Owner CHENGDU ENGINE GROUP