CN113042669A - Rotor assembly for engine and preparation method thereof - Google Patents
Rotor assembly for engine and preparation method thereof Download PDFInfo
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- CN113042669A CN113042669A CN201911363500.0A CN201911363500A CN113042669A CN 113042669 A CN113042669 A CN 113042669A CN 201911363500 A CN201911363500 A CN 201911363500A CN 113042669 A CN113042669 A CN 113042669A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/002—Hybrid process, e.g. forging following casting
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/02—Die forging; Trimming by making use of special dies ; Punching during forging
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C14/00—Alloys based on titanium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
- C22F1/18—High-melting or refractory metals or alloys based thereon
- C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/174—Titanium alloys, e.g. TiAl
Abstract
The invention relates to a rotor assembly for an engine and a preparation method thereof. A method of preparing a rotor assembly for an engine, comprising: providing a titanium alloy raw material, heating the titanium alloy raw material to a temperature of 25-40 ℃ below a beta transformation point, then performing die forging on the titanium alloy raw material, and performing machining after die forging to obtain a rotor assembly blank; the rotor assembly blank comprises a blank disc part and a blank drum part, wherein the blank drum part is an annular flange protruding from one side surface of the blank disc part, and the protruding direction is the axial direction along the central rotation axis of the rotor assembly; heating the blank drum part to enable the blank drum part to reach a temperature 20-50 ℃ above a beta phase transformation point, and then carrying out ring rolling on the blank drum part, wherein the pressure direction of the ring rolling is in the radial direction; then solid solution and aging treatment are carried out.
Description
Technical Field
The invention relates to the field of materials, in particular to a rotor assembly for an engine and a preparation method thereof.
Background
At least some known rotating machinery, such as turbine engines, include various rotor assemblies, such as fan assemblies, compressors, and/or turbines, each of which includes a rotor assembly.
For compressors, it may include a drum and disc hybrid rotor assembly. As shown in fig. 1, the drum and disc hybrid rotor assembly includes a plurality of rotor assemblies 20 connected in series, the rotor assemblies 20 include a disc portion 200 and a drum portion 220, and the disc portion 200 and the drum portion 220 are rotatable about a central rotation axis 30. Further blades 240 may be mounted at the disk edge of the disk portion 200.
Disclosure of Invention
The inventor finds that the service environment of an aircraft engine is complex, and the stress conditions and the service environment of different parts are different for the same disc. Under some working conditions, the cruising working condition of the drum part of the rotor assembly exceeds 350 ℃, and the working stress exceeds 450MPa, so that the high-temperature and high-stress working condition puts higher thermal creep performance requirements on the drum part performance of a rotor disc of the high-pressure compressor.
The present disclosure provides a dual-performance rotor assembly and a method of making the same. The disk part and the drum part of the rotor assembly have different microstructures, and can meet the requirements of different working conditions. The rotor assembly is integrally formed, and the joint between the disk portion and the drum portion is free from welding or bolting.
In some aspects, a method of preparing a rotor assembly for an engine is provided, comprising:
(1) providing a titanium alloy raw material, and heating the titanium alloy raw material to a temperature T1Then, carrying out die forging on the titanium alloy raw material, and carrying out machining after die forging to obtain a rotor assembly blank, wherein T is T1Is 25-40 ℃ below the beta transformation point of the titanium alloy (for example, 30-35 ℃ below the beta transformation point);
the rotor assembly blank comprises a blank disc part and a blank drum part, wherein the blank drum part is an annular flange protruding from one side surface of the blank disc part, and the protruding direction is the axial direction along the central rotation axis of the rotor assembly;
(2) heating the blank drum part to make the temperature T of the blank drum part reach2Then carrying out ring rolling on the blank drum part, wherein the pressure direction of the ring rolling is radial, and T is2Is 20-50 ℃ above the beta transformation point of the titanium alloy (for example, 30-40 ℃ above the beta transformation point);
(3) heating the product of the previous step to a temperature T3Keeping the temperature for 0.5-1.5 h, and then cooling in air or at a slower speed, wherein T is3Is 10-50 ℃ below the beta transformation point (for example, 20-30 ℃ below the beta transformation point or 30-40 ℃ below the beta transformation point);
(4) heating the product of the previous step to a temperature T4Keeping the temperature for 6-10 h (for example, 7-8 h or 8-9 h), and then cooling in air or at a slower speed, wherein T4The temperature is 550 to 650 ℃ (for example, 600 ℃).
In some embodiments, step (3) is solution heat treatment.
In some embodiments, step (4) is an aging heat treatment.
And (3) selecting a ring rolling process to process the blank drum part in the step (2), which is very key for realizing the beneficial technical effects of the invention. In the ring rolling process, the drum part of the blank is exposed in the air, the cooling rate is air cooling, the cooling rate is very stable, and the product obtained after ring rolling has uniform tissue and stable performance.
In some embodiments, the die forging of step (1) is performed in a die at 300 to 400 ℃.
In some embodiments, further comprising the following steps between steps (2) and (3): and (3) machining the product of the step (2) according to the shape and size requirements of the rotor assembly product.
In some embodiments, the above method further comprises: and removing the area of the equivalent plastic strain value (e) > 2 of the blank disc part and the blank drum part in the ring rolling process by machining.
The inventors have found that the region of equivalent plastic strain value (e) > 2 during ring rolling is eventually unable to form the desired basket structure and is therefore removed by machining.
In some embodiments, the above method further comprises: and removing the areas with macroscopic defects (such as cracks and folds) on the blank disc part and the blank drum part by mechanical processing.
In some embodiments, after processing in steps (1) - (4), the blank disc portion or machined product thereof contains a bimodal structure.
In some embodiments, after processing in steps (1) - (4), the raw drum or its machined product contains basket weave.
In some embodiments, at any point of the blank disc portion in the radial direction, the blank disc portion is reserved with a machining allowance of more than 10% (e.g., more than 20%, e.g., more than 30%, e.g., more than 40%, e.g., more than 50%, e.g., more than 60%) in the axial direction.
In some embodiments, at any point of the blank drum portion in the axial direction, the blank disc portion is reserved with a machining allowance of more than 10% (e.g., more than 20%, e.g., more than 30%, e.g., more than 40%, e.g., more than 50%, e.g., more than 60%) in the radial direction.
In some embodiments, the allowance for machining allowance for a location is (the location blank size-the location end product size)/the location blank size. For example, the blank thickness is 100mm, the product thickness is 40mm, and the allowance of 60% in the thickness direction is reserved.
In some embodiments, in step (1), the titanium alloy feedstock is obtained as follows: heating the titanium alloy bar stock to a temperature T1And upsetting to obtain the pier cake.
In some embodiments, in step (2), the blank drum is heated using a heat source, and the heat source is not in contact with the blank disc.
In some embodiments, in step (2), the blank drum portion is heated using a heat source, and the blank disc portion is isolated from the heat source by a thermal shield layer.
In some embodiments, in step (2), the ring rolling is performed such that the equivalent plastic strain value of the drum portion of the blank is 0.7 or more.
In some embodiments, in step (2), the ring rolling is such that the minimum value of the equivalent plastic strain value of the blank drum is 0.7.
In some embodiments, the blank disc portion is machined to form a disc portion of the rotor assembly, the disc portion including a radially inner hub, a web extending radially outward from the hub, and a rim extending radially outward from the web.
In some embodiments, the blank drum portion is machined to form a drum portion of the rotor assembly, the drum portion projecting from the radial flange to form an annular flange, the direction of projection being axial along a central rotational axis of the rotor assembly.
In some aspects, a rotor assembly for an engine is provided, obtained by a method as described in any of the above.
In some aspects, a rotor assembly for an engine is provided, comprising a disk portion and a drum portion;
the rotor component is made of titanium alloy, the disc part is provided with a titanium alloy binary structure, and the drum part is provided with a titanium alloy basket structure;
the rotor assembly is integrally formed.
In some embodiments, the blank drum has a basket weave. The titanium alloy basket structure has higher high-temperature tensile property, higher fracture toughness and excellent thermal creep resistance, and is suitable for the working condition.
In some embodiments, the blank disc portion has a bimodal texture. The blank disk part is in a low-temperature high-stress working condition area, and the two-state structure has higher fatigue performance and is suitable for the working condition.
In some embodiments, the titanium alloy is a near alpha titanium alloy.
In some embodiments, the titanium alloy is Ti6242 titanium alloy. The Ti6242 titanium alloy is a titanium alloy material having a composition substantially of Ti-6Al-2Sn-4Zr-2 Mo.
Ti6242 belongs to a near alpha titanium alloy having a nominal beta transus of about 1005 ℃.
The Ti6242 material is forged from alpha + beta to obtain a bimodal structure, and comprehensive properties such as room-temperature tensile strength, high-low cycle fatigue and the like can be obtained.
The Ti6242 material is forged on a beta phase transformation point to obtain a basket structure, and the comprehensive properties such as high-temperature tensile property, fracture toughness, creep property and the like are obtained.
In some embodiments, the rotor assembly of the present disclosure is a rotor assembly for a turbine.
In some embodiments, the rotor assembly of the present disclosure is a rotor assembly for a compressor (compressor).
Description of terms:
if the following terms are used in the present invention, they may have the following meanings:
various relative terms such as "front," "back," "top," and "bottom," "upper," "lower," "above," "below," and the like may be used to facilitate description of various embodiments. Relative terms are defined with respect to conventional orientations of the structure and do not necessarily indicate an actual orientation of the structure at the time of manufacture or use. The following detailed description is, therefore, not to be taken in a limiting sense. As used in the description and the appended claims, the singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise.
The terms "duplex", "basket" and "basket" are two microstructures of titanium alloys. The following documents describe in detail the definition of the two microstructures mentioned above, which are incorporated herein in their entirety. Technical research and development of a novel aviation high-performance titanium alloy material [ M ]. beijing: the aeronautical industry Press, 2013.12, pages 48-50. Or, zhao yongqing, chen yong nan weaving, titanium alloy phase change and heat treatment [ M ]. long sand: zhongnan university Press, 2012.01, pp 128-130.
The term "radial" is a direction substantially perpendicular to the central rotational axis of the rotor assembly.
The term "axial" is a direction substantially parallel to the central rotational axis of the rotor assembly.
The term "beta transus point" refers to the alpha + beta/beta transus temperature on the phase diagram of a titanium alloy.
Advantageous effects
One or more technical schemes of the present disclosure have one or more of the following beneficial effects:
(1) the rotor component is integrally formed, and the disc part and the drum part have different microstructures, so that the performances under respective use working conditions can be respectively met;
(2) the processing method is simple, fast and low in cost.
Drawings
FIG. 1 is a schematic view of a drum and disc hybrid rotor assembly.
Fig. 2 is a schematic view of a rotor assembly blank of example 1.
Fig. 3 is a schematic view of an isolated heating device.
Fig. 4 is a schematic view of machining a ring rolled rotor assembly blank.
Figure 5 is a photograph of a microstructure of a rim location of a disk portion of a rotor assembly.
Fig. 6 is a photograph of the microstructure of a drum portion of a rotor assembly.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to examples, but those skilled in the art will appreciate that the following examples are only illustrative of the present invention and should not be construed as limiting the scope of the present invention. The examples, in which specific conditions are not specified, were conducted under conventional conditions or conditions recommended by the manufacturer. The reagents or instruments used are not indicated by the manufacturer, and are all conventional products commercially available.
Example 1
The method of making the rotor assembly is as follows:
ti6242 titanium alloy bar stock with the length of 700mm and the diameter of 230mm is provided. And heating the bar stock to 35 ℃ below the beta transformation point, preserving heat for 1 hour, and then upsetting, wherein the upsetting deformation is controlled to be 40-60%. And carrying out 6-time forging modification after upsetting to obtain the pier cake. And (3) heating the pier cake to 35 ℃ below the beta transformation point, keeping the temperature for 1 hour, performing die forging, wherein the temperature of a die is 350 ℃, the transfer time (the practice for transferring a die forging object from a heating furnace to the die) is less than 45s, and performing air cooling. After swaging, the swaged product in the black skin condition was machined into a rotor assembly blank 10 as shown in fig. 2.
As shown in fig. 1, the rotor assembly blank 10 includes a blank disc portion 100 and a blank drum portion 120. The blank disk portion 100 includes a radially inner blank hub 112, a blank web 114 extending radially outward from the blank hub 112, and a blank rim 116 extending radially outward from the blank web 114. The blank drum portion 120 is an annular flange projecting from one side of the blank disc portion 100 in an axial direction along the central rotational axis 30 of the rotor assembly.
As shown in FIG. 1, the inner diameter d1 of the blank disk portion 100 is
An outer diameter d4 of
Inner diameter d2 of blank drum portion 120 is
An outer diameter d3 of
The thickness h1 of the blank hub 112 is 32mm + -2 mm, the thickness h2 of the blank web 114 is 25mm + -2 mm, and the thickness h3 of the blank rim 116 is
The thickness h4 of the blank drum part is 32mm + -2 mm.
The rotor assembly blank 10 is placed into the isolated heating apparatus of fig. 3, and the blank drum portion 120 is heated in isolation. Specifically, the isolation heating device includes a heat source 41 and a heat insulating layer 42, the heat source 41 contacts only the blank drum part 120 and does not contact the blank tray part 100, and the heat insulating layer 42 separates the blank tray part 100 from the heat source 41. The blank drum 120 is heated to 40 c above the beta transus point and held at temperature for one hour.
After heating, the blank drum 120 is banded with a pressure direction along the radial direction of the rotor assembly. Before ring rolling, a finite element simulation method is used for simulating a ring rolling deformation process and determining an equivalent plastic strain value e of each area. The ring rolling process parameters are regulated and controlled to make the equivalent plastic strain value of the blank drum part 120 more than or equal to 0.7 (the minimum value is 0.7). Meanwhile, the area with equivalent plastic strain value larger than 2 after ring rolling is determined according to the simulation result.
And (5) machining the ring-rolled product. As shown in fig. 4, the region 31 removed by machining is outlined by a dashed line. The region 31 includes a defective region 33 (e.g., crack, wrinkle) caused by ring rolling and a region 32 where an equivalent plastic strain value (e) > 2 occurs in the ring rolling.
Fig. 4 shows a rotor assembly. As shown in FIG. 4, the blank disc portion 100 is machined to form the disc portion 200 of the rotor assembly, the disc portion 200 including a radially inner hub portion 212, a web 214 extending radially outward from the hub portion 212, and a rim 216 extending radially outward from the web 214. The blank drum portion 120 is machined to form a drum portion 220 of the rotor assembly, the drum portion 220 being an annular flange projecting from the radial flange 216 in an axial direction along the central rotational axis 30 of the rotor assembly. The inner diameter of the drum part 220 is
An outer diameter of
The web 214 has a thickness h5 of 19mm and the drum 200 has a thickness h6 of 58mm 2 mm.
And carrying out solid solution heat treatment on the product obtained in the last step, wherein the heat treatment temperature is 50 ℃ below the beta transformation point, keeping the temperature for 1 hour, and cooling by air.
And (3) carrying out aging heat treatment on the product obtained in the last step, wherein the heat treatment temperature is about 600 ℃, keeping the temperature for 8 hours, and then cooling the product in air.
Dissecting the integrally formed blank, and observing the microstructure of the integrally formed blank by using an optical microscope. The observation results show that:
(1) the hub 212, web 214 and rim 216 are typically alpha + beta phase bimodal, and the microstructure of the rim 216, see fig. 5, is typically alpha + beta phase bimodal.
(2) The drum portion 200 is a typical beta-phase basket structure, and the microstructure is shown in fig. 6, which is a typical basket structure.
From the above, it can be seen that the embodiment 1 indeed obtains the titanium alloy rotor assembly with dual performance through the integral molding process.
While specific embodiments of the invention have been described in detail, those skilled in the art will understand that: various modifications may be made in the details within the teachings of the disclosure, and these variations are within the scope of the invention. The full scope of the invention is given by the appended claims and any equivalents thereof.
Claims (13)
1. A method of preparing a rotor assembly for an engine, comprising:
(1) providing a titanium alloy raw material, and heating the titanium alloy raw material to a temperature T1Then, the titanium alloy raw material is subjected to die forging, and the die forging is followed by machining to obtain a rotor assembly blank (10), wherein T is1Is 25-40 ℃ below the beta transformation point of the titanium alloy;
the rotor assembly blank (10) comprises a blank disc part (100) and a blank drum part (120), wherein the blank drum part (120) is an annular flange protruding from one side surface of the blank disc part (100) in the axial direction of a central rotating axis (30) of the rotor assembly;
(2) heating the blank drum part (120) to make the blank drum part (120) reach the temperature T2Then the blank drum part (120) is ring-rolled, the pressure direction of the ring-rolling is radial, wherein T2Is 20-50 ℃ above the beta transformation point of the titanium alloy;
(3) heating the product of the previous step to a temperature T3Keeping the temperature for 0.5-1.5 h, and then cooling in air or at a slower speed, wherein T is3Is 10-50 ℃ below the beta transformation point of the titanium alloy;
(4) heating the product of the previous step to a temperature T4Keeping the temperature for 6-10 h, and then cooling in air or at a slower speed, wherein T4Is 550 to 650 ℃.
2. The method of claim 1, further comprising, between steps (2) and (3), the steps of: and (3) machining the product of the step (2) according to the shape and size requirements of the rotor assembly product.
3. The method of claim 2, further comprising one or more of:
-removing by machining the areas of the blank disc part (100) and the blank drum part (120) where the equivalent plastic strain e > 2 is during ring rolling;
-removing by machining the areas of the blank disc part (100) and the blank drum part (120) where macro-defects are present.
4. A method according to any one of claims 1 to 3, characterised by one or more of the following:
after the processing of the step (4), the blank disc part (100) or the mechanically processed product thereof contains a bimodal structure;
after the processing of the step (4), the blank drum part (120) or the machined product thereof contains basket tissues.
5. A method according to any one of claims 1 to 3, having one or more of the following characteristics:
-reserving more than 10% of machining allowance in the axial direction at any point of the blank disc part (100) along the radial direction of the rotor assembly;
-reserving more than 10% of machining allowance in the radial direction at any point of the blank drum portion (120) in the axial direction of the rotor assembly.
6. The method of claim 1, wherein in step (1), the titanium alloy feedstock is obtained by: heating the titanium alloy bar stock to a temperature T1Upsetting, wherein the upsetting deformation amount is controlled to be 40-60%, and thus obtaining the upsetting cake.
7. The method of claim 1, wherein in step (2), the blank drum portion (120) is heated using a heat source, and the heat source is not in contact with the blank disc portion (100).
8. The method according to claim 7, wherein in step (2), the blank drum portion (120) is heated using a heat source, and the blank disc portion (100) is isolated from the heat source by a thermal insulating layer.
9. The method according to claim 1, wherein in step (2), the ring rolling is performed so that the equivalent plastic strain value of the blank drum (120) is not less than 0.7.
10. The method according to any one of claims 2 to 4,
the blank disc portion (100) is machined to form a disc portion 200 of the rotor assembly, the disc portion 200 including a radially inner hub portion (212), a web (214) extending radially outward from the hub portion (212), and a rim (216) extending radially outward from the web (214);
the blank drum part (120) is machined to form a drum part (220) of the rotor assembly, the drum part (220) protrudes from the radial flange (216) to form an annular flange, and the protruding direction is the axial direction of the central rotating axis (30) of the rotor assembly.
11. The method of claim 1, the titanium alloy being a near-alpha titanium alloy.
12. A rotor assembly for an engine, obtained by the method of any one of claims 1 to 11.
13. A rotor assembly for an engine includes a disc portion and a drum portion;
the rotor assembly is made of titanium alloy, the disc part is provided with a titanium alloy binary structure, and the drum part is provided with a titanium alloy basket structure;
the rotor assembly is integrally formed.
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