A powder high-temperature alloy turbine disc for an aero-engine and a preparation method thereof

Abstract

The application belongs to the technical field of aviation materials, and relates to a powder high-temperature alloy turbine disc for an aero-engine and a preparation method thereof. The preparation method comprises the following steps: (1) alloy preparation powder filling; (2) hot isostatic pressing blank preparation; (3) forging blank preparation; (4) integral forging preparation; and (5) machining. The powder high-temperature alloy turbine disc for the aero-engine and the preparation method thereof can be used to prepare the powder high-temperature alloy turbine disc for the aero-engine at low cost, and the prepared turbine disc can have more excellent performance.

Description

Technical Field

[0001] This invention belongs to the field of aerospace materials technology, and relates to a powder high-temperature alloy turbine disk for aero-engines and its preparation method. Background Technology

[0002] Turbine disks are one of the most critical core hot-end components in aero-engines, requiring long-term stable operation under high temperature, high speed, high load, and complex oxidation and corrosion environments. Due to the high-temperature alloys prepared by powder metallurgy technology, characterized by high alloying degree, uniform microstructure, fine grains, and absence of macroscopic segregation, powder metallurgy high-temperature alloy turbine disks have become the preferred material for high thrust-to-weight ratio aero-engine turbine disks. Currently, the application of third-generation materials to powder metallurgy high-temperature alloy turbine disks has reached a point where these materials are being developed and applied. With the continuous increase in the thrust-to-weight ratio of advanced aero-engines, turbine inlet temperatures are constantly rising, correspondingly requiring powder metallurgy high-temperature alloy turbine disks to have higher temperature resistance. Identifying the temperature characteristics of the service environment of engine turbine disks reveals that the disk rim contacts high-temperature exhaust gases, resulting in a high operating temperature, thus requiring excellent high-temperature creep resistance; the disk core operates at a relatively lower temperature but bears greater centrifugal stress, therefore the core region requires higher strength.

[0003] To meet the performance requirements of different regions of turbine disk components, dual-performance turbine disk fabrication technology has emerged. Currently, research on dual-performance turbine disk fabrication technology mainly focuses on two techniques:

[0004] 1. Single-alloy dual-structure-dual-performance disk preparation technology: The disk blank is made from the same alloy. Then, by controlling the gradient heat treatment, a temperature gradient is established from the disk edge to the disk core during the solution treatment. This results in the disk edge region obtaining coarse grains, thus giving the disk edge region good creep performance; the disk core region obtaining fine grains, thus giving the disk core region good yield strength.

[0005] 2. Dual-alloy dual-structure dual-performance disk preparation technology: This involves selecting a durable, creep-resistant coarse-grained alloy for the disk rim and a high-strength fine-grained alloy for the disk core. The two alloys are then joined together by methods such as welding, hot isostatic pressing, or superplastic forging to create a dual-performance disk.

[0006] However, practical experience has revealed that the single-alloy dual-structure dual-performance disk preparation technology faces challenges in temperature gradient control, including high technical difficulty, complex process control, high cost, low repeatability, and grain mixing and uneven transition in the transition zone between coarse and fine grain regions. Furthermore, the dual-alloy dual-structure dual-performance disk preparation technology also suffers from the presence of a "weak connection" region in the bonding area between the two alloys, which makes this area highly susceptible to cracking, leading to turbine disk rupture and failure, and consequently affecting engine safety.

[0007] In order to ensure the quality and life of the turbine disk and reduce the introduction of large-sized particle inclusions, after research and testing, the upper limit of the particle size of high-temperature alloy powder is currently limited to 58μm. Due to the particle size distribution characteristics of the powder making technology, about 40% (by weight) of large coarse powder after sieving cannot be used, and ultimately form high-temperature alloy coarse powder return material, which further increases the production and manufacturing cost of powder high-temperature alloy turbine disks.

[0008] Based on the above analysis, due to the immaturity of the technological approach and the inability to effectively utilize idle coarse powder return materials, existing technologies cannot achieve low-cost and efficient preparation of dual-performance powder superalloy turbine disks. Therefore, exploring alloy composition design and inventing a dual-alloy single-structure dual-performance powder superalloy turbine disk for aero-engines and its low-cost preparation method has significant practical value and application significance. Summary of the Invention

[0009] The primary objective of this invention is to provide a method for preparing powder metallurgy high-temperature alloy turbine disks for aero-engines, so as to prepare powder metallurgy high-temperature alloy turbine disks for aero-engines at low cost and obtain turbine disks with superior performance.

[0010] To achieve this objective, in a basic implementation, the present invention provides a method for preparing a powder metallurgy high-temperature alloy turbine disk for aero-engines, the method comprising the following steps in sequence:

[0011] (1) Alloy preparation powder filling: The cylindrical casing is divided into three regions from the inside to the outside by two layers of partitions, and three different alloy preparation powders are filled in the innermost region 1 with a circular cross-section, the middle region 2 with a circular cross-section, and the outer region 3 with a circular cross-section. The alloy preparation powder filled in region 2 contains Re element, and the alloy preparation powder filled in region 3 contains Ru element.

[0012] (2) Preparation of hot isostatic pressing billet: The cladding after removing the partition is successively subjected to cladding sealing welding, preheating, hot isostatic pressing and mechanical processing to remove the cladding to obtain hot isostatic pressing billet;

[0013] (3) Preparation of forging blank: The hot isostatic pressing blank is heated and held at a certain temperature, and then forged and annealed to obtain the forging blank;

[0014] (4) Preparation of integral forgings: The forging blank is subjected to solution treatment and two-stage aging treatment to obtain integral forgings;

[0015] (5) Machining: The integral forging is machined to remove the area formed by hot isostatic pressing and heat preservation forging of the alloy powder filling in area 1, and finally obtain the powder high temperature alloy turbine disk for aero-engine.

[0016] In this invention, Re and Ru are both matrix elements. The main components of the powders filled in regions 2 and 3 are similar, with only Re and Ru being different. Therefore, after being processed by the same process, the alloy grains formed in regions 2 and 3 are consistent, and the transition at the region connection is smooth. Consequently, the addition of Re element powder will result in the prepared alloy having better yield strength in the disk core region, and the addition of Ru element powder will result in the prepared alloy having better creep performance in the disk edge region.

[0017] In a preferred embodiment, the present invention provides a method for preparing a powder metallurgy high-temperature alloy turbine disk for an aero-engine, wherein in step (1),

[0018] The alloy powder packed in Region 1 has a particle size of 58-1000 μm and a composition by mass percentage of: Cr 11.0%–13.0%, Co 19.0%–22.0%, Mo 3.5%–6.0%, Ta 2.4%–4.0%, W 2.1%–2.5%, Al 3.0%–5.0%, Nb 0.5%–1.0%, Ti 3.0%–4.5%, C 0.02%–0.08%, B 0.01%–0.07%, Zr 0.02%–0.08%, with the balance being Ni.

[0019] The alloy powder packed in Region 2 has a particle size ≤58μm and a composition by mass percentage as follows: Cr 11.0%–13.0%, Co 19.0%–22.0%, Mo 3.5%–6.0%, Ta 2.4%–4.0%, W 2.1%–2.5%, Al 3.0%–5.0%, Nb 0.5%–1.0%, Ti 3.0%–4.5%, C 0.02%–0.08%, B 0.01%–0.07%, Zr 0.02%–0.08%, Re 1.0%–4.0%, with the balance being Ni.

[0020] The alloy powder packed in region 3 has a particle size ≤58μm and a composition by mass percentage as follows: Cr 11.0%–13.0%, Co 19.0%–22.0%, Mo 3.5%–6.0%, Ta 2.4%–4.0%, W 2.1%–2.5%, Al 3.0%–5.0%, Nb 0.5%–1.0%, Ti 3.0%–4.5%, C 0.02%–0.08%, B 0.01%–0.07%, Zr 0.02%–0.08%, Ru 1.0%–4.0%, with the balance being Ni.

[0021] In a preferred embodiment, the present invention provides a method for preparing a powder metallurgy high-temperature alloy turbine disk for an aero-engine, wherein in step (1),

[0022] The alloy powder packed in Region 1 has a particle size of 58-1000 μm and a composition by mass percentage of: Cr 11.0%–13.0%, Co 19.0%–22.0%, Mo 3.5%–6.0%, Ta 2.4%–4.0%, W 2.1%–2.5%, Al 3.0%–5.0%, Nb 0.5%–1.0%, Ti 3.0%–4.5%, C 0.02%–0.08%, B 0.01%–0.07%, Zr 0.02%–0.08%, with the balance being Ni.

[0023] The alloy preparation powder packed in region 2 has a particle size ≤58μm and contains 1.0% to 4.0% Re by mass percentage, based on the composition of the alloy preparation powder packed in region 1.

[0024] The alloy preparation powder packed in region 3 has a particle size ≤58μm and contains Ru 1.0% to 4.0% by mass percentage, based on the composition of the alloy preparation powder packed in region 1.

[0025] In a preferred embodiment, the present invention provides a method for preparing a powder metallurgy high-temperature alloy turbine disk for an aero-engine, wherein in step (1),

[0026] The wall thickness of the sheath is 5-30mm;

[0027] The sleeve is made of stainless steel;

[0028] The package has powder inlet ports above regions 1, 2, and 3.

[0029] The partition is a movable partition.

[0030] In a preferred embodiment, the present invention provides a method for preparing a powder metallurgy high-temperature alloy turbine disk for an aero-engine, wherein in step (1),

[0031] During the alloy powder filling process, the packaging is placed in a vacuum heating environment to ensure that the vacuum degree of the packaging is not less than 5 × 10⁻⁶. -3 Pa, temperature not lower than 150℃;

[0032] The alloy preparation powder loading speed in each area is 20-50 kg / h. After the alloy preparation powder loading is completed, a high-temperature alloy block plug is used to block the powder input port, and plasma arc welding is used to weld and seal the gap between the high-temperature alloy block plug and the powder input port.

[0033] In a preferred embodiment, the present invention provides a method for preparing a powder high-temperature alloy turbine disk for an aero-engine, wherein in step (2), the preheating temperature is 1000-1150℃, the heating rate is 100℃ / h-300℃ / h, and the holding time is 1-4h; the hot isostatic pressing temperature is 1100-1250℃, the heating rate is 100℃ / h-300℃ / h, the pressure is 100-250MPa, and the holding time is 1-8h.

[0034] In a preferred embodiment, the present invention provides a method for preparing a powder high-temperature alloy turbine disk for an aero-engine, wherein in step (3), the hot isostatic pressed billet is heated and held in a preheating furnace. The specific process is as follows: the temperature is raised to 400°C at a heating rate of 100°C / h to 300°C / h and held for 2 to 6 hours; the temperature is then raised to 1000 to 1150°C at a heating rate of 100°C / h to 300°C / h and held for 2 to 6 hours.

[0035] In a preferred embodiment, the present invention provides a method for preparing a powder high-temperature alloy turbine disk for an aero-engine, wherein in step (3), the forging temperature of the isothermal forging equipment is 1000-1150°C. After the hot isostatic pressing billet is heated and held at the temperature, the hot isostatic pressing billet is transferred to the isothermal forging equipment for isothermal forging. The transfer time does not exceed 30s, the average pressing rate is 0.1-0.5mm / s, and the total deformation is 50%-75%.

[0036] In a preferred embodiment, the present invention provides a method for preparing a powder high-temperature alloy turbine disk for an aero-engine, wherein in step (3), the forged billet is air-cooled, and after cooling, it is annealed. The annealing process is as follows: the temperature is raised to 750°C at a heating rate of 100°C / h to 300°C / h and held for 2 to 6 hours; the temperature is lowered to 250°C at a cooling rate of 100°C / h to 300°C / h and then air-cooled to room temperature.

[0037] In a preferred embodiment, the present invention provides a method for preparing a powder metallurgy high-temperature alloy turbine disk for an aero-engine, wherein in step (4),

[0038] The solution temperature is 1000–1200℃, the heating rate is 100℃ / h–300℃ / h, and the holding time is 1–4h.

[0039] After solution treatment, quench with quenching oil;

[0040] The temperature for the first-stage aging treatment is 800-1000℃, the heating rate is 100℃ / h-300℃ / h, the holding time is 1-4h, and the furnace is cooled after the holding time is completed.

[0041] The temperature for the secondary aging treatment is 500–800℃, the heating rate is 100℃ / h–300℃ / h, the holding time is 4–12h, and the furnace is cooled after the holding time is completed.

[0042] The second objective of this invention is to provide a powder metallurgy high-temperature alloy turbine disk for aero-engines, which can have superior performance.

[0043] To achieve this objective, in a basic implementation, the present invention provides a powder metallurgy high-temperature alloy turbine disk for an aero-engine, the turbine disk being prepared according to the aforementioned preparation method.

[0044] The beneficial effect of the present invention is that, by using the powder high-temperature alloy turbine disk for aero-engines and the preparation method of the present invention, powder high-temperature alloy turbine disks for aero-engines can be prepared at low cost, and the resulting turbine disks can have superior performance.

[0045] The method of this invention for preparing powder metallurgy high-temperature alloy turbine disks for aero-engines effectively solves the problem of idle and wasteful high-temperature alloy coarse powder return material (region 1) during turbine disk preparation. The resulting turbine disk exhibits better creep performance in the rim region and better yield strength in the core region, with a uniform transition between the rim and core regions, reducing the likelihood of cracking. Therefore, this invention can prepare high-performance, high-reliability powder metallurgy turbine disks, possessing significant practical application value.

[0046] The beneficial effects of this invention are specifically reflected in:

[0047] 1. This invention creatively adds Re and Ru elements to the powder used in the preparation of high-temperature alloy powder disks, which greatly improves the high-temperature creep resistance of the disk edge and the tensile strength of the disk core.

[0048] 2. This invention creatively performs hot isostatic pressing and isothermal forging on different types of powders simultaneously, eliminating the "weak connection" area between the two alloys and avoiding cracks at the "weak connection" location. The turbine disk component has a uniform grain size and a significant grain boundary strengthening effect, thereby ensuring the safe and reliable use of the aero-engine.

[0049] 3. This invention achieves effective utilization of idle coarse powder through a technical method of adding coarse powder and removing it through controlled machining, which greatly reduces production and manufacturing costs;

[0050] 4. The turbine disks prepared by this invention have uniform microstructure, and the performance distribution of the disks can be customized in design, development, control and preparation according to the dimensions of the drawings. This makes it easier to meet the performance requirements of disks of various types and alloys, and at the same time better ensures the research and development and application of high-level aero engines. Attached Figure Description

[0051] Figure 1 The flowchart illustrates the preparation method of the powder superalloy turbine disk for aero-engines according to the present invention.

[0052] Figure 2 The following is a schematic diagram of the customizable packaging structure and filling principle of the present invention as an example. The diagram includes a packaging 1, a packaging annular partition 2, an annular partition sling 3, a packaging cover sling 4, a packaging cover 5, a powder feeding pipe 6, a powder receiving port 7, a vibrating packaging filling machine 8, a packaging vibrator 9, a region (1) 10, a region (2) 11, a region (3) 12, and a high-temperature alloy block plug 13.

[0053] Figure 3 This is an exemplary schematic diagram of the composition of the hot isostatic pressing billet of the present invention.

[0054] Figure 4 This is an exemplary schematic diagram of the isothermal forging blank and disc composition of the present invention.

[0055] Figure 5 The image shows the grain structure of different regions of the disk obtained in Example 1.

[0056] Figure 6 This is a comparison chart of the tensile and yield properties obtained in Example 3.

[0057] Figure 7 This is a comparison chart of the creep performance obtained in Example 3. Detailed Implementation

[0058] An exemplary process for preparing the powder superalloy turbine disk for aero-engines according to the present invention is as follows: Figure 1 As shown, it includes the following steps:

[0059] (1) Raw material preparation: Prepare three types of high-temperature alloy powders, namely Type 1, Type 2 and Type 3;

[0060] (2) Encasing design: Determine the final state turbine disk blank drawing size, use forging simulation software deform to fit the alloy forging deformation process, restore the deformation process and identify the size of the three types of high temperature alloy powder filling area, and design and manufacture the casing based on the size information;

[0061] (3) Packaging and Filling: The three types of high-temperature alloy powders are simultaneously vibrated and compacted using a vibratory packaging and filling machine (see packaging design and filling principle for details). Figure 2 After filling, the package is sealed by welding. The sealed package consists of three regions from the inside out: region 1, region 2, and region 3.

[0062] (4) Preheating and hot isostatic pressing of the cladding: The cladding after sealing and welding is preheated, and then the preheated cladding is hot isostatic pressing. After the hot isostatic pressing is completed, it is machined to remove the cladding's third-stage powder receiving port and the cladding skin, and a hot isostatic pressing billet of dual alloy single structure-dual performance powder high temperature alloy is obtained.

[0063] (5) Isothermal forging and annealing: The hot isostatic pressing billet of the dual alloy single structure-dual performance powder high temperature alloy is placed into the forging preheating furnace for heating and holding. After the holding is completed, the hot isostatic pressing billet is quickly transferred to the isothermal forging equipment for forging. After forging and cooling, annealing is performed to obtain the forging billet of the dual alloy single structure-dual performance powder high temperature alloy.

[0064] (6) Heat treatment: The annealed forging blank is subjected to solution treatment and two-stage aging treatment to obtain a single-structure-dual-performance powder superalloy integral forging;

[0065] (7) Machining: Combine the deformation size data of the forging simulation software to determine the size information of the deformed area 1. Then, the whole forging is machined to remove the area formed by the powder at the location of area 1 after hot isostatic pressing and isothermal forging. Finally, a single-structure-dual-performance powder high-temperature alloy turbine disk is obtained.

[0066] in:

[0067] In step (1), the high-temperature alloy powder of type 1 has a particle size of 58-1000 μm, and its composition (mass percentage) is: Cr 11.0%~13.0%, Co 19.0%~22.0%, Mo 3.5%~6.0%, Ta 2.4%~4.0%, W 2.1%~2.5%, Al 3.0%~5.0%, Nb 0.5%~1.0%, Ti 3.0%~4.5%, C 0.02%~0.08%, B 0.01%~0.07%, Zr 0.02%~0.08%, and the balance Ni; the high-temperature alloy powder of type 2 has a particle size ≤58 μm, and its composition (mass percentage) is: Cr 11.0%~13.0%, Co The high-temperature alloy powder of type 3 used has a particle size ≤58μm, and its composition (mass percentage) is: Cr 11.0%–22.0%, Mo 3.5%–6.0%, Ta 2.4%–4.0%, W 2.1%–2.5%, Al 3.0%–5.0%, Nb 0.5%–1.0%, Ti 3.0%–4.5%, C 0.02%–0.08%, B 0.01%–0.07%, Zr 0.02%–0.08%, Re 1.0%–4.0%, and balance Ni; 3.0%–5.0%, Nb 0.5%–1.0%, Ti 3.0%–4.5%, C 0.02%–0.08%, B 0.01%–0.07%, Zr 0.02%–0.08%, Ru 1.0%–4.0% and balance Ni;

[0068] In step (2), the overall shape of the casing is a multi-level cylindrical shape. Region 1 is cylindrical with an outer diameter of D1. Region 2 is a cylindrical shape that surrounds Region 1 with a maximum outer diameter of D2. Region 1 and Region 2 are separated by a movable partition. Region 3 is a cylindrical shape that surrounds Region 2 with a maximum outer diameter of D3. Region 2 and Region 3 are separated by a movable partition. The dimensions of each region can be designed and adjusted according to the dimensions of the turbine disk drawing, and D3 > D2 > D1. The casing material is 304 stainless steel, the casing wall thickness is 5-30mm, and the casing has a powder input port above each of Region 1, Region 2 and Region 3.

[0069] In step (3), the packaging is placed in a vacuum heating environment during the packaging process, with a vacuum degree of not less than 5×10⁻⁶. -3Pa, temperature not lower than 150℃, powder filling speed of powder inlet in each area is 20-50Kg / h, after filling, remove movable partition, use high temperature alloy block plug to block powder inlet, and use plasma arc welding to weld and seal the gap between high temperature alloy block plug and powder inlet.

[0070] In step (4), the preheating temperature of the cladding is 1000~1150℃, the heating rate is 100℃ / h~300℃ / h, and the holding time is 1-4h; the hot isostatic pressing temperature of the cladding is 1100~1250℃, the heating rate is 100℃ / h~300℃ / h, the pressure is 100~250MPa, and the holding time is 1~8h.

[0071] In step (5), the heating process of the hot isostatic pressing billet in the preheating furnace is as follows: the temperature is raised to 400℃ at a heating rate of 100℃ / h to 300℃ / h and held for 2 to 6 hours; the temperature is further raised to 1000 to 1150℃ at a heating rate of 100℃ / h to 300℃ / h and held for 2 to 6 hours; the temperature of the isothermal forging equipment is 1000 to 1150℃. After the preheating treatment of the hot isostatic pressing billet is completed, the hot isostatic pressing billet is transferred to the isothermal forging furnace. Isothermal forging is performed using die forging equipment, with a transfer time not exceeding 30 seconds, an average reduction rate of 0.1–0.5 mm / s, and a total deformation of 50%–75%. The forged billet is then air-cooled, followed by annealing. The annealing process is as follows: the temperature is raised to 750℃ at a heating rate of 100℃ / h–300℃ / h and held for 2–6 hours; then the temperature is lowered to 250℃ at a cooling rate of 100℃ / h–300℃ / h, and subsequently air-cooled to room temperature.

[0072] In step (6), the solution temperature is 1000-1200℃, the heating rate is 100℃ / h-300℃ / h, the holding time is 1-4h, and then quenching is performed with quenching oil; the first-stage aging temperature is 800-1000℃, the heating rate is 100℃ / h-300℃ / h, the holding time is 1-4h, and furnace cooling is performed after the holding time is completed; the second-stage aging temperature is 500-800℃, the heating rate is 100℃ / h-300℃ / h, the holding time is 4-12h, and furnace cooling is performed after the holding time is completed.

[0073] In step (7), the obtained single-structure-dual-performance powder high-temperature alloy turbine disk has a uniform overall grain size and a significant grain boundary strengthening effect. The turbine disk edge has good high-temperature creep performance, and the turbine disk core has high tensile strength.

[0074] The following are examples of applications of the above-described exemplary method for preparing powder high-temperature alloy turbine disks for aero engines.

[0075] Example 1: Preparation Example

[0076] Step 1: Select high-temperature alloy powder of type 1 with a particle size of 105-1000 μm, and its composition (mass percentage) is: Cr 11.0%, Co 19.0%, Mo 3.5%, Ta 2.4%, W 2.1%, Al 3.0%, Nb 0.5%, Ti 3.0%, C 0.02%, B 0.01%, Zr 0.02%, and balance Ni; select high-temperature alloy powder of type 2 with a particle size of 0.01-53 μm, and its composition (mass percentage) is: Cr 11.0%, Co 19.0%, Mo 3.5%, Ta 2.4%, W 2.1%, Al 3.0%, Nb 0.5%, Ti 3.0%, C 0.02%, B 0.01%, Zr 0.02%, Re The high-temperature alloy powder of type 3, with a particle size of 0.01-53 μm, was selected. Its composition (mass percentage) was: Cr 11.0%, Co 19.0%, Mo 3.5%, Ta 2.4%, W 2.1%, Al 3.0%, Nb 0.5%, Ti 3.0%, C 0.02%, B 0.01%, Zr 0.02%, Ru 1.9%, and the balance Ni. A total of 100 kg of type 1 high-temperature alloy powder, 200 kg of type 2 high-temperature alloy powder, and 300 kg of type 3 high-temperature alloy powder, totaling 600 kg, were prepared and stored in a vibratory packaging and filling machine. Subsequent packaging and filling were carried out through independent conveying pipelines.

[0077] Step 2: Design and process the sleeve, sleeve cover and sleeve annular partition, where D1 is 100mm, D2 is 200mm, D3 is 400mm, and the sleeve wall thickness is 15mm.

[0078] Step 3: Pre-install the cover and annular partition of the packaging sleeve in the telescopic sling. Install and fix the packaging sleeve in the designated position of the vibratory packaging filling machine. Control the telescopic sling to lower the packaging sleeve cover into the designated position of the packaging sleeve vibrator. Move the powder feeding pipe to align it with the powder receiving port of the packaging sleeve cover. Control the telescopic sling to lower the annular partition of the packaging sleeve into the designated position, thus physically isolating the three areas. Turn on the vibratory packaging filling machine to transport powder by area. Type 3 high-temperature alloy powder enters area 3 through the powder feeding pipe and the powder receiving port, Type 2 high-temperature alloy powder enters area 2 through the powder feeding pipe and the powder receiving port, and Type 1 high-temperature alloy powder enters area 1 through the powder feeding pipe and the powder receiving port. Set the powder conveying rate to 30 kg / h and the vacuum degree to 5 × 10⁻⁶. -4Pa, temperature 200℃; the shroud vibrator works continuously during powder feeding; after all areas of the shroud are filled, powder feeding is stopped, and the shroud vibrator works for an additional 30 minutes before being turned off. The connection between the shroud cover and the shroud cover sling is disconnected, the shroud cover is tightened, and the annular partition is moved up by the sling to separate it from the shroud; then, plasma arc welding is used to weld and seal the high-temperature alloy block plug and the gap at the powder inlet, as well as the connection between the shroud and the shroud cover.

[0079] Step 4: Preheat the sealed cladding to 1000℃ at a heating rate of 100℃ / h and hold for 4 hours. Then, perform hot isostatic pressing (HIP) on the preheated cladding at 1100℃ at a heating rate of 100℃ / h, a pressure of 180MPa, and a holding time of 4 hours. After HIP and cooling, machine the cladding, removing the third-stage powder receiving port and the outer skin to obtain a bi-alloy single-structure, bi-performance powder superalloy HIP billet. The billet contains three regions: region 3 is formed by filling with type 3 superalloy powder, region 2 by filling with type 2 superalloy powder, and region 1 by filling with type 1 superalloy powder. Specific zoning can be found in the reference [reference needed]. Figure 3 .

[0080] Step 5: The hot isostatic pressed billet is subjected to isothermal forging. The heating process in the preheating furnace is as follows: the temperature is increased to 400℃ at a heating rate of 100℃ / h and held for 2 hours; the temperature is further increased to 1150℃ at a heating rate of 100℃ / h and held for 6 hours; the temperature of the isothermal forging equipment is 1150℃. After the preheating treatment of the hot isostatic pressed billet is completed, the hot isostatic pressed billet is transferred to the isothermal forging equipment for isothermal forging. The transfer time is 20 seconds, the average reduction rate is 0.5 mm / s, and the total deformation is 75%. The forged billet is transferred out of the isothermal forging equipment and air-cooled to room temperature. After cooling, annealing is performed. The annealing process is as follows: the temperature is increased to 750℃ at a heating rate of 100℃ / h and held for 2 hours; the temperature is decreased to 250℃ at a cooling rate of 100℃ / h, and then air-cooled to room temperature. The resulting isothermal forging billet and the composition of each region are shown in the figure. Figure 4 .

[0081] Step 6: Perform solution treatment and two-stage aging on the isothermal forging blank. Set the solution temperature to 1100℃, the heating rate to 100℃ / h, and the holding time to 4h. Then quench it with quenching oil to room temperature. Set the first-stage aging temperature to 800℃, the heating rate to 100℃ / h, and the holding time to 4h. After holding, furnace cool to room temperature. Set the second-stage aging temperature to 500℃, the heating rate to 100℃ / h, and the holding time to 8h. After holding, furnace cool to room temperature.

[0082] Step 7: Based on the deformation dimension data from the forging simulation software, determine the dimensional information of region 1 after deformation. Then, machine the entire forging, removing the area formed by the powder deformation of region 1 through hot isostatic pressing and isothermal forging. The final product is a single-structure, dual-performance powder superalloy turbine disk. The machining area and the disk's regional composition within the blank are illustrated in the diagram. Figure 4 .

[0083] Example 2: Controlled Preparation Example

[0084] The composition (mass percentage) of the high-temperature alloy powders of types 1, 2, and 3 is as follows: Cr 11.0%, Co 19.0%, Mo 3.5%, Ta 2.4%, W 2.1%, Al 3.0%, Nb 0.5%, Ti 3.0%, C 0.02%, B 0.01%, Zr 0.02%, and the balance Ni. The particle size of the high-temperature alloy powder of type 1 is 105-1000 μm, that of type 2 is 0.01-53 μm, and that of type 3 is 0.01-53 μm. The rest is the same as in Example 1.

[0085] Example 3: Detection Example

[0086] Metallographic, core tensile yield, and edge creep properties tests were performed on the turbine disks prepared in Examples 1 and 2, respectively (tensile yield property test according to GB / T 228.2 Metallic materials, tensile testing—Part 2: High temperature test method; creep property test according to GB / T 2039), and the resulting grain structures were as follows. Figure 5 As shown, the tensile yield properties are as follows Figure 6 As shown in Table 1, the creep properties are as follows: Figure 7 As shown.

[0087] Figure 5 The left image shows the grain structure of region 1 (filled with powder without Re or Ru) of the disk obtained in Example 1, the middle image shows the grain structure of region 2 (filled with powder with Re added), i.e., the disk core region, of the disk obtained in Example 1, and the right image shows the grain structure of region 3 (filled with powder with Ru added), i.e., the disk edge region, of the disk obtained in Example 1. Figure 5 This indicates that the grains prepared by adding Re and Ru fine powders respectively have the same grain size and the grain boundaries are coarsened.

[0088] Figure 6 Table 1 shows that the tensile strength and yield strength of the disk core alloy formed by adding Re to the powder (Example 1) are higher than those of the disk core alloy formed by not adding Re to the powder (Example 2).

[0089] Table 1

[0090]

[0091] Figure 7 The results show that the creep resistance of the disk rim alloy formed by adding Ru to the powder (Example 1) is higher than that of the disk rim alloy formed by not adding Ru to the powder (Example 2). Specifically, the disk rim alloy formed by adding Ru to the powder (Example 1) reaches 0.2% strain in 223 hours, while the disk rim alloy formed by not adding Ru to the powder (Example 2) reaches 0.2% strain in 158 hours. Thus, adding Ru to the disk rim will extend the time to reach the same creep deformation by 41.1% compared to not adding Ru to the disk rim.

[0092] In summary, the turbine disk prepared by this invention is a single-structure, dual-performance powder high-temperature alloy turbine disk with uniform grains, coarsened grain boundaries, better high-temperature creep performance at the disk edge, and higher strength at the disk core.

[0093] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims and their equivalents, this invention is also intended to include these modifications and variations. The above embodiments or implementations are merely illustrative examples of this invention, and it can also be implemented in other specific ways or forms without departing from its gist or essential characteristics. Therefore, the described embodiments should be considered illustrative rather than limiting in any respect. The scope of this invention should be defined by the appended claims, and any changes equivalent to the intent and scope of the claims should also be included within the scope of this invention.

Claims

1. A method of making a powder metallurgy high temperature alloy turbine disk for an aeroengine, characterized in that, The preparation method comprises the following steps in sequence: (1) alloy preparation powder filling: a cylindrical can is divided into three regions by two partitions from inside to outside, and three kinds of alloy preparation powder with different compositions are filled in the first region with circular cross section, the second region with circular ring cross section and the third region with circular ring cross section respectively, and the alloy preparation powder filled in the second region contains Re element, and the alloy preparation powder filled in the third region contains Ru element; (2) hot isostatic pressing blank preparation: the can without the partitions is subjected to can sealing, preheating, hot isostatic pressing and machining to remove the can in sequence, and a hot isostatic pressing blank is obtained; (3) forging blank preparation: the hot isostatic pressing blank is heated and kept, and then subjected to forging and annealing treatment, and a forging blank is obtained; (4) integral forging preparation: the forging blank is subjected to solid solution and two-stage aging treatment, and an integral forging is obtained; (5) machining: the integral forging is subjected to machining, and the region formed by the alloy preparation powder filled in the first region after hot isostatic pressing and heat preservation forging deformation is removed, and finally the powder high-temperature alloy turbine disc for an aero-engine is obtained, wherein: in step (1), the particle size of the alloy preparation powder filled in the first region is 105-1000 μm, and the mass percentage composition is: Cr 11.0%-13.0%, Co 19.0%-22.0%, Mo 3.5%-6.0%, Ta 2.4%-4.0%, W 2.1%-2.5%, Al 3.0%-5.0%, Nb 0.5%-1.0%, Ti 3.0%-4.5%, C 0.02%-0.08%, B 0.01%-0.07%, Zr 0.02%-0.08%, and the balance is Ni; the particle size of the alloy preparation powder filled in the second region is 0.01-53 μm, and the mass percentage composition is: Cr 11.0%-13.0%, Co 19.0%-22.0%, Mo 3.5%-6.0%, Ta 2.4%-4.0%, W 2.1%-2.5%, Al 3.0%-5.0%, Nb 0.5%-1.0%, Ti 3.0%-4.5%, C 0.02%-0.08%, B 0.01%-0.07%, Zr 0.02%-0.08%, Re 1.0%-4.0%, and the balance is Ni; the particle size of the alloy preparation powder filled in the third region is 0.01-53 μm, and the mass percentage composition is: Cr 11.0%-13.0%, Co 19.0%-22.0%, Mo 3.5%-6.0%, Ta 2.4%-4.0%, W 2.1%-2.5%, Al 3.0%-5.0%, Nb 0.5%-1.0%, Ti 3.0%-4.5%, C 0.02%-0.08%, B 0.01%-0.07%, Zr 0.02%-0.08%, Ru 1.0%-4.0%, and the balance is Ni.

2. The method of claim 1, wherein: in step (1), the wall thickness of the can is 5-30 mm; The material of the sleeve is stainless steel. The sleeve is provided with a powder input port above each of the area 1, area 2 and area 3. The partition is a movable partition.

3. The method of claim 2, wherein: In step (1), During the powder loading process for alloy preparation, the capsule is placed in a vacuum heating environment, so that the vacuum degree of the capsule is not less than 5x10 -3 Pa, and the temperature is not less than 150℃. The filling speed of the alloy preparation powder in each area is 20-50 Kg / h, and after the filling of the alloy preparation powder is completed, a high-temperature alloy block is used to plug the powder input port, and the gap between the high-temperature alloy block and the powder input port is welded and sealed by plasma arc welding.

4. The method of claim 1, wherein: In step (2), the preheating temperature is 1000-1150℃, the heating rate is 100℃ / h-300℃ / h, and the holding time is 1-4h; the temperature of the hot isostatic pressing is 1100-1250℃, the heating rate is 100℃ / h-300℃ / h, the pressure is 100-250MPa, and the holding time is 1-8h.

5. The method of claim 1, wherein: In step (3), the hot isostatic pressing blank is heated and held in a preheating furnace, and the specific process is as follows: heated to 400℃ at a heating rate of 100℃ / h-300℃ / h, and held for 2-6h; then continuously heated to 1000-1150℃ at a heating rate of 100℃ / h-300℃ / h, and held for 2-6h.

6. The method of claim 1, wherein: In step (3), the temperature for forging by the isothermal die forging equipment is 1000-1150℃, after the hot isostatic pressing blank is heated and held, the hot isostatic pressing blank is transferred to the isothermal die forging equipment for isothermal forging, the transfer time is not more than 30s, the average pressing speed is 0.1-0.5mm / s, and the total deformation is 50%-75%.

7. The method of claim 1, wherein: In step (3), the forged blank is air-cooled, and after cooling, annealing treatment is performed, and the annealing process is as follows: heated to 750℃ at a heating rate of 100℃ / h-300℃ / h, and held for 2-6h; then cooled to 250℃ at a cooling rate of 100℃ / h-300℃ / h, and then air-cooled to room temperature.

8. The method of claim 1, wherein: In step (4), The solution temperature is 1000-1200℃, the heating rate is 100℃ / h-300℃ / h, and the holding time is 1-4h; After solution, quenching oil is used for quenching; The temperature for the first aging treatment is 800-1000℃, the heating rate is 100℃ / h-300℃ / h, the holding time is 1-4h, and after the holding is completed, furnace cooling is performed; The temperature for the second aging treatment is 500-800℃, the heating rate is 100℃ / h-300℃ / h, the holding time is 4-12h, and after the holding is completed, furnace cooling is performed.

9. A powder metallurgy superalloy turbine disk for an aeroengine, characterized in that: The turbine disc is prepared by the preparation method according to any one of claims 1-8.

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