Method of plastic working of the high-temperature resistant alloys bars used for production of gas-turbine engine compressor blades

FIELD: aircraft industry; mechanical engineering; methods of metals plastic working.

SUBSTANCE: the invention is pertaining to the methods of metals plastic working, in particular, to production of blanks for units of a gas turbine engine and may be used in production of aircraft engines and in mechanical engineering. The method includes heating of a high-temperature resistant alloy bar and its straining during several runs. For obtaining a homogeneity of the blank chemical composition and structure in the whole volume of the blank and for increasing the alloy mechanical properties during the blank subsequent machining at least one run is conducted at the temperature exceeding the temperature of the beginning of the alloy hardening inter-metallic phase dissolution. Then, they conduct a press forming in the interval of the temperatures from the temperature of a recrystallization process start to the temperature of the recrystallization process end for production of the uniform fine grained structure, that ensures a high level of general physical-mechanical properties of the blank and the item as a whole.

EFFECT: the invention ensures production of the uniform fine-grained structure and a high level of general physical-mechanical properties of the blank and the item as a whole.

2 ex

 

The invention relates to the processing of metals by pressure, namely the manufacturing of workpieces, for example, for the nodes of the CCD, and can be used in the aircraft engine industry and mechanical engineering.

There is a method of stamping blanks, comprising heating billets, forging and cooling for several transitions (see USSR author's certificate No. 660770, MKI 21 To 3/04, publ. 05.05.79 g) is similar.

However, this method does not allow to obtain the necessary macro - and microstructure of the workpiece, which negatively affects the quality of the products obtained.

There is a method of forming heat-resistant alloys, including heating billets and its deformation over several transitions (see RF patent №2134308, 22 F 1/18, publ. 10.08.1999,) prototype.

The disadvantages of this solution are the instability of the physico-mechanical properties of the product and the high complexity of the process.

The present invention solves the problem of improving such characteristics of the product as reliability and fatigue, by optimizing the structure and mechanical properties of the workpiece, while reducing the complexity of the process.

The problem is solved in that in the processing method of rods from HRSA to get the compressor blades of gas turbine engine, comprising heating the rod and its deformation over several switched the s, at least one transition performed at a temperature exceeding the temperature at which dissolution hardening intermetallic phase alloy, and then perform the forging in the temperature range from the temperature of the beginning of the recrystallization temperatures of the end of recrystallization.

For high-heat, such as Nickel and titanium, alloys temperature of the beginning of the dissolution of hardening intermetallic phases Ti3(Al, Sn), Ni3(Al, Ti), usually located in the range from 1040° With up to 1200° C. Heating the workpiece before surgery deformation temperatures of dissolution hardening intermetallic phase ensures the achievement of uniformity of chemical composition and structure of the harvest, improves the processing properties of the alloy during subsequent mechanical processing.

Performing at least one transition in the temperature range from the temperature of the beginning of the recrystallization temperatures of the end recrystallization allows one to obtain a homogeneous fine-grained structure, providing a high level of General physical and mechanical properties of the workpiece, and hence the product as a whole.

The temperature at which recrystallization heat-resistant alloys, typically above 900° s, and the specific values of the temperatures chosen depending on the given technical conditions led the ranks of grain, want to get in the finished product.

Transactions processing pressure at stated temperatures with strain rates (10-2- 10-3with-1allows you to achieve the effect of superplastic alloy and minimal deformation, for example by forging, which allows you to use less powerful hardware.

For example, for alloy VT3-1, the temperature at which recrystallization 880° and the temperature of the end of the recrystallization 930° C. When heated to a temperature 910-930° and conducting isothermal forging at low strain rates, such as 10-3with-1these temperatures correspond to the interval of the superplastic alloy (δ ≈ 350%, σ s ≈ 4 kg/mm2). Under these deformation parameters is a good filling of the dies in the manufacture of complex components, with the simultaneous formation of the optimal microstructure details.

Example 1

Consider the processing of Nickel alloy, for the manufacture of compressor blades of gas turbine engine alloy EP 718 ID for which (on the chart):

the temperature of the dissolution hardening intermetallic phase diagram is equal to 1080° C

the temperature at which recrystallization is equal to 880° C

the temperature is and the end of recrystallization 950° C.

Rod cut-to-length blanks with a diameter of 15 mm and a length of 20 mm and put them in an electric furnace for heating to a temperature of 1150° after which was carried out by extrusion of a billet on the press with the preliminary formation of the pen and the castle of the scapula.

Then again heated billet to a temperature of 1160° and was carried out by stamping. Then made trimming Burr, clearing, controlled harvesting and producing heated to a temperature of 900° after which was carried out by the punching blade to specified dimensions.

This has resulted in blades with the following mechanical properties:

σβ=126,5 (kg/mm2), σof 0.2=78,5 (kg/mm2), δ =26%, ψ =47,3%, XI=12,2 (kg× m/cm2);

when requirements:

σβ=115,0 (kg/mm2), σof 0.2=70,0 (kg/mm2), δ =12%, ψ =14,0%, KCU=3.5 (kg× m/cm2).

Example 2

Consider the process of manufacturing the blades of the low-pressure compressor of the gas turbine engine alloy VT3-1, for which the temperature of the dissolution hardening intermetallic phase alloy - 1080° C

the temperature at which recrystallization of the alloy - 880° C

the temperature of the end of the recrystallization of the alloy - 930° C.

Stamping carry out three operations: landing, punching at t is mperature, exceeding a temperature of the dissolution hardening intermetallic phase alloy and forging in the temperature range from the temperature of the beginning of the recrystallization temperatures of the end of the recrystallization of the alloy.

First made landing a round billet with a diameter of 13 mm and a length of 200 mm with two opposite sides with a set of metal under two shank blades. Local heating of the workpiece for the planting was carried out by the method of electrical resistance to a temperature of 950-980° C. After heating and kantowski planted two blanks with a diameter of 30 mm and a height of 20 mm, While the Central part of the rod was not heated, so after landing received the workpiece throughout the volume has a grain structure.

To align the last and complete dissolution hardening intermetallic phase Ti3(Al) heating billets for transitions stamping carried out at a temperature exceeding the temperature at which dissolution hardening intermetallic phase, produced to a temperature of 1100° C.

Then carried out the transitions punching in isothermal conditions, the heating of the workpiece was carried out to a temperature in the temperature range from TNR to TCR for this alloy, namely to a temperature of 920° C.

In the following results were obtained:

σβ= 105,2 (kg/mm2/sup> ), δ = 21,2%, ψ = 55,3%, KCU = 5,7 (kg× m/cm2);

when requirements:

σβ= 100,0-120,0 (kg/mm2), δ ≥ 12%, ψ ≥ 3,5%, KCU≥ 3.0 (kg× m/cm2).

The way to handle bars of heat-resistant alloys for receiving the compressor blades of gas turbine engine, comprising heating a rod of heat-resistant alloy and its deformation for several transitions, characterized in that at least one transition is carried out at a temperature exceeding the temperature at which dissolution hardening intermetallic phase alloy, followed by forging in the temperature range from the temperature of the beginning of the recrystallization temperatures of the end of recrystallization.



 

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1 ex

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