CN101920392A - Mechanically-machining rib/diffusion connecting process for titanium alloy rudders and wing members - Google Patents

Abstract

The invention discloses a mechanically-machining rib/diffusion connecting process for titanium alloy rudders and wing members, which comprises the following steps of: 1, mechanically machining the rudders, the wing members and the ribs according to drawings; 2, performing acid washing; 3, folding the two halves of mechanically-machined rudders, the two halves of mechanically-machined wing members and the two halves of mechanically-machined ribs and welding the peripheries and a ventilation pipe; 4, mold-filling, namely, placing the rudders and the wing members coated with a parting agent in the centre of a cavity of superplastic forming equipment; 5, raising the temperature and introducing a protective gas; 6, forming, namely, (1) introducing one liter of gas with a pressure equal to 3 barometric pressures into the cavity of the parts for 5 minutes, (2) introducing one liter of gas with the pressure equal to 3 barometric pressures into the cavity of the parts for 60 minutes and (3) introducing one liter of gas with the pressure equal to 1.2 barometric pressures into the cavity of the parts for 5 minutes; 7, reducing the temperature and performing stripping; and 8, milling the external forms of the rudders and the wing members. The process has the advantages of high forming success rate, stable member quality, accurate rib position, stable gravity center position and short forming time which is only 1 to 2 hours.

Description

Titanium alloys rudder, wing member machining rib/diffusion connecting process

Technical field:

The present invention is machining titanium alloy system rudder, wing member machining rib/diffusion connecting process.

Background technology:

In aviation, the spacecraft centered rudder, wing member is normal to adopt four layers of titanium alloy plate through superplastic forming/diffusion connecting process processing, four layers of superplastic forming/diffusion connecting process of titanium alloy are: forming temperature is meant shaping dies is warming up to 910 ℃～950 ℃, at two-way shaping gas circuit input argon gas, two-layer vacuumizing simultaneously, this two-layer not separant coating position is diffused into together, in former, keep certain pressure and after the regular hour, to intermediate layer input argon gas, the air pressure of two outside layers reduces gradually, and two-layer rising was moulded shape and is connected with the diffusion of outside in the middle of this process had realized.

Rise and be moulded shape/diffusion connecting process flow process: (1) blanking: press the blanking of figure paper size, following four titanium alloy plates, monolateral high-volume 50mm requires perimeter alignment, otherwise is difficult to close grave envelope between each laminate when welding, tolerance+0.25mm; (2) location, line: by locator tabs, model line; (3) mill air channel: milling pore groove, width are 3mm～4mm, and the degree of depth is about 40%～50% of sheet thickness, a polishing flash removed after the milling; (4) pickling: plate is placed in the descaling bath, and the surface acid-washing oil removing is to guarantee panel surface cleaning, free from admixture and oxide skin; Pickling prescription: every premium on currency contains 200 milliliters～300 milliliters in 500 milliliters～550 milliliters in nitric acid and hydrofluoric acid; (5) separant coating: apply interleaving agent according to the non-diffusion join domain of drawing outline line on plate, and apply interleaving agent at pore groove and gas channels place; The interleaving agent main component is: yittrium oxide or boron nitride; (6) vent line preparation: prepare the part vent line with reference to the equipment platform size, pipeline length is placed on platform central authorities with part and is advisable, and can not there be defectives such as crackle, fracture pipeline bending position; (7) welding: adopt the argon arc welding manner to weld plate border and pipeline, check pipeline and pocket air-tightness after welding is finished; (8) dress mould: cleaning die surface, guarantee profile part free from admixture, be convenient to molding at blank outer surface and die surface separant coating, mould is put in superplastic forming equipment (Loire FSP400T titanium alloy hot former) furnace chamber middle position, underlay insulation asbestic blanket on the mould, connecting line and temperature thermocouple are closed fire door, heat up; (9) heat up: be warming up to and be shaped temperature required (the titanium alloy forming temperature is 910 ℃～950 ℃), during part to fill high purity argon protection; (10): be shaped: on superplastic forming equipment, form by facility control program.Its deficiency is: 1, superplastic forming/Diffusion Welding four-layer structure the trigonum defective occurs easily in that internal layer is super when moulding outer diffusing procedure, makes the easy groove of part appearance, causes part to scrap.2, during superplastic forming/Diffusion Welding stud, local gapped, do not have in the diffusion welding (DW), the bearing capacity of stud is reduced.3, formation of parts thickness is thin more, titanium alloy superplastic forming/Diffusion Welding four-layer structure part forming was poor more when the part forming area was big more.4, the rib of superplastic forming easily departs from, and makes the position inaccuracy of internal structure, easily influences the intensity of structure, and is bigger to the center of gravity influence of structure.5, whole manufacturing is longer the same period, and the hot forming time is long, needs 6～9 hours.。For avoiding above deficiency on four layers of superplastic forming of titanium alloy/diffusion connecting process basis, improve at the technology of making titanium alloy rudder, wing structure and to develop titanium alloys rudder, wing member machining rib/diffusion connecting process.

Summary of the invention:

The purpose of the invention provides a kind of titanium alloys rudder, wing member is shaped as the power height, titanium alloys rudder, wing member machining rib/diffusion connecting process that forming quality is stable; The purpose of the invention is to realize by following technical scheme: titanium alloys rudder, wing member machining rib/diffusion connecting process, and its step is as follows:

1), machining rudder, wing member and rib: map interlinking paper conversion;

2), pickling: rudder, wing member and rib that machining is intact carry out pickling;

3), involutory welded perimeter of rudder, wing member and rib and the vent line that two halves machining is finished;

4), dress mould: rudder, wing member outer surface and die surface separant coating after welding before the dress mould is contained in superplastic forming equipment inner chamber middle position, underlay insulation asbestic blanket on mould with rudder, the wing member of separant coating;

5), intensification and input protection gas;

6), be shaped: order is as follows:

(1) when mold temperature is raised to the assigned temperature temperature, be 1 liter gas to inner cavity of component input 1～3 atmospheric pressure, volume, 5 minutes duration;

(2) to 3 atmospheric pressure of inner cavity of component input, volume is 1 liter a gas, the continuous 60 minutes time;

(3) to inner cavity of component input 1.2 atmospheric pressure, volumes be 1 liter gas, 5 minutes duration;

7), cooling molding: mold temperature is reduced to molding below 500 ℃;

8), milling rudder, wing member profile.

The advantage of the invention: part forming success rate height, part quality is stable, groove can not occur, and the rib position is accurate, and position of centre of gravity is stable.

Description of drawings:

Fig. 1 is titanium alloys rudder, wing member inner surface structure schematic diagram;

Fig. 2 is processing the rib on rudder, the wing member inner surface and the structural representation of air channel on the titanium alloy plate.

The specific embodiment: for for example shown in Figure 1, the wing member gross thickness is 10mm according to certain wing member, and length dimension is 200mm, and width dimensions is 900mm, and titanium alloys rudder, wing member machining rib/diffusion connecting process are described in detail in detail, and its step is as follows:

1), machining rudder, wing member and rib: map interlinking paper conversion; Get two 5.1mm uniform thickness titanium alloy plates as blank, adopt the mode of digital control milling, be processed into symmetrical two, utilize CAD software CATIA to carry out the rib shape of numerical control programming processing parts inside, adopt vacuum cup and pressing plate pressing dual mode that plate is fixed in the process, guarantee machining accuracy.

Machined parameters: roughing: the speed of mainshaft is 1500 rev/mins

The tool feeding amount is 150mm/ minute

Excision amount 0.8mm

Fine finishining: the speed of mainshaft is 1000 rev/mins

The tool feeding amount is 200mm/ minute

Excision amount 0.2mm

2), pickling: rudder, wing member and rib that machining is intact carry out pickling; Pickling prescription: every premium on currency contains 200 milliliters～300 milliliters in 500 milliliters～550 milliliters in nitric acid and hydrofluoric acid; The surface acid-washing oil removing is to guarantee panel surface cleaning, free from admixture and oxide skin.

3), involutory welded perimeter of rudder, wing member and rib and the vent line that two halves machining is finished; The member of two symmetries that machining rudder, wing member and rib are processed is involutory according to benchmark, with argon arc welding soldering and sealing periphery and vent line, makes member form the pocket of a sealing;

Welding parameter: arc current: 110A

Arc voltage 10V

Welding gun argon gas charge 10L/min

After finishing, welding checks pipeline and member air-tightness.

4), dress mould: before the dress mould, the cleaning die surface is removed impurity, rudder after welding, wing member outer surface and die surface separant coating, purpose is to be convenient to molding, and the interleaving agent main component is: yittrium oxide or boron nitride are contained in superplastic forming equipment with rudder, the wing member of separant coating

(adopting ACB company to make) inner chamber middle position, underlay insulation asbestic blanket on mould; Connecting line and temperature thermocouple are closed fire door, heat up.

5), intensification and input protection gas; Shaping dies is warming up to 945 ℃, the input high purity argon.

6), be shaped: order is as follows:

(1) to inner cavity of component input 1～3 atmospheric pressure, volume is 1 liter gas, 5 minutes duration;

(2) to 3 atmospheric pressure of inner cavity of component input, volume is 1 liter a gas, the continuous 60 minutes time;

(3) to inner cavity of component input 1.2 atmospheric pressure, volumes be 1 liter gas, 5 minutes duration.

7), cooling molding: mold temperature is reduced to molding below 500 ℃;

8), milling rudder, wing member profile.Utilize CAD software CATIA to carry out numerical control programming, milling part profile.

Advantage: part forming success rate height, part quality is stable, groove can not occur, and the rib position is accurate, and position of centre of gravity is stable, and the hot forming time is short, only needs 1～2 hour.

Claims (1)

1. titanium alloys rudder, wing member machining rib/diffusion connecting process, its step is as follows:

1), machining rudder, wing member and rib: map interlinking paper conversion;

2), pickling: rudder, wing member and rib that machining is intact carry out pickling;

3), involutory welded perimeter of rudder, wing member and rib and the vent line that two halves machining is finished;

4), dress mould: rudder, wing member outer surface and die surface separant coating after welding before the dress mould is contained in superplastic forming equipment inner chamber middle position, underlay insulation asbestic blanket on mould with rudder, the wing member of separant coating;

5), intensification and input protection gas;

6), be shaped: order is as follows:

(1) to inner cavity of component input 1～3 atmospheric pressure, volume is 1 liter gas, 5 minutes duration;

(2) to 3 atmospheric pressure of inner cavity of component input, volume is 1 liter a gas, the continuous 60 minutes time;

(3) to inner cavity of component input 1.2 atmospheric pressure, volumes be 1 liter gas, 5 minutes duration;

7), cooling molding: mold temperature is reduced to molding below 500 ℃;

8), milling rudder, wing member profile.

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