Titanium Alloy Dual-Performance Integral Bladed Disk Differential Temperature Heat Treatment Furnace and Transition Zone Control Method

Abstract

This invention relates to a differential temperature heat treatment furnace for a titanium alloy dual-performance integral bladed disk, comprising upper and lower furnace bodies, and a differential temperature heat treatment chamber enclosed by the upper and lower furnace bodies for accommodating the integral bladed disk. The integral bladed disk is supported within the differential temperature heat treatment chamber by heat insulation cylinders, which are correspondingly positioned in the transition zone between the disk body and the blades of the integral bladed disk, thereby dividing the differential temperature heat treatment chamber into a central high-temperature zone corresponding to the disk body and an edge low-temperature zone corresponding to the blades. This invention also provides a method for controlling the transition zone of the integral bladed disk in this differential temperature heat treatment furnace. This invention achieves control over the target microstructure region of the bladed disk during differential temperature heat treatment of the titanium alloy dual-performance integral bladed disk, simplifies the operation of the differential temperature heat treatment process, and improves the controllability of the transition zone of the integral bladed disk.

Description

Technical Field

[0001] This invention relates to the field of titanium alloy heat treatment technology, specifically to a method for controlling the transition zone of an integral titanium alloy bladed disk. Background Technology

[0002] High-temperature titanium alloys, with their high specific strength and good thermal strength, have become the preferred material for integral bladed disks (IBDs) of aircraft engine compressors. The service environments of different parts of an IBD vary greatly, with large temperature and stress gradients along its radial direction. IBDs with a uniform microstructure often cannot simultaneously meet the varying requirements of heat and stress resistance in different parts, inevitably resulting in some performance loss for each part. To maximize efficiency and reliability, both the blades and the disk should possess microstructures and properties (dual performance) that match the service conditions. The blades primarily bear high-frequency, low-amplitude vibrations and should possess a dual-phase microstructure containing both primary equiaxed α phases and secondary lamellar α phases to ensure high-cycle fatigue, strength, and plasticity. The disk bears large centrifugal and thermal stresses and should possess a basketweave microstructure containing only secondary lamellar α phases to ensure high-temperature creep and fracture toughness. The transition zone between the blades and the disk should have a microstructure that gradually transforms from a dual-phase microstructure to a basketweave microstructure. Therefore, for dual-performance titanium alloy bladed disks, the width and location of the transition zone between the disk, blades, and microstructure are determined according to their service requirements. The key is how to obtain the desired microstructure type in the disk and blade areas through reasonable processing and manufacturing methods, and to achieve precise control over the location and width of the transition zone.

[0003] The concept and manufacturing technology of dual-performance disks were first applied to high-temperature alloy turbine disks. For high-temperature alloy disks, the principle of dual performance is achieved by changing or controlling the grain size in different regions, targeting a single type of microstructure and constituent phase. US patents with publication numbers 5527402, 6478896B1, and 6660110B1, and Chinese patents with publication numbers CN110788562B, CN102615284B, CN111187895B, and CN112464533B, have obtained high-temperature alloy dual-performance turbine disks through different technical means. However, titanium alloys are mostly two-phase materials (e.g., primary equiaxed α phase and secondary lamellar α phase), which involve complex phase transformations during hot working. The principle of achieving dual performance is to obtain different types of microstructures in different regions of the component by utilizing the phase transformation characteristics. Therefore, existing manufacturing technologies for high-temperature alloy dual-performance disks cannot be directly applied to titanium alloy components.

[0004] Patents with authorization announcement numbers CN107138924B, CN111570795B, and CN112296602B propose a method for preparing titanium alloy dual-performance bladed disks using dissimilar alloys. This involves connecting blades of another alloy to a titanium alloy disk body using additive manufacturing technology, thereby obtaining a dual-alloy dual-performance bladed disk. However, dual-alloy dual-performance bladed disks have the following drawbacks: First, the interface between the dissimilar alloys may be a "weak" region; second, if the elastic moduli of the dissimilar alloys differ significantly, it can lead to substantial thermal stress at the interface; third, using the same heat treatment process during subsequent heat treatment may compromise the mechanical properties of both alloys.

[0005] The authorization announcement number CN115055696B proposes a method for manufacturing an integral titanium alloy bladed disk for aero-engines. The method involves connecting the finished disk and blades into a single unit using linear friction welding to obtain a semi-finished integral bladed disk. This semi-finished integral bladed disk is then machined to obtain the finished integral bladed disk. However, the linear friction welding process is highly dependent on equipment. The welding effect and precision largely depend on the capabilities of the equipment. Furthermore, the welding tooling is complex and costly. In addition, titanium alloys with poor plasticity are prone to welding cracks during linear friction welding.

[0006] US patents 5795413 and 6110302 propose a method for preparing titanium alloy dual-performance disks by local forging. First, an α+β titanium alloy preform is subjected to β heat treatment or β forging, and then heated to the temperature of the α+β two-phase region for local forging, so that the forged region and the unforged region form different microstructures.

[0007] The patent with authorization announcement number CN101629273B first obtains a full-layer structure by forging billet and preparing preforms, and then controls the different deformation amounts in each region by multiple local loadings, thereby obtaining different microstructures in different regions.

[0008] The literature (Cai Jianming, Tian Feng, Liu Dong, et al. Research progress on preparation technology of 600℃ high temperature titanium alloy dual-performance integral bladed disk forging [J]. Materials Engineering, 2018, 46(5):36-43.) proposes a similar zoned temperature-controlled forging method. The first forging is carried out by forging deformation in the β single-phase region to obtain a lamellar structure. Then, the second forging is carried out in the α+β two-phase region. Different microstructures are obtained by controlling the deformation amount of different regions in the second forging.

[0009] Authorized publication number CN114378233B proposes a manufacturing method for a Ti2AlNb-based alloy dual-performance integral bladed disk. First, a pre-formed billet of a certain shape and size is obtained through pre-forging. Then, the pre-formed billet undergoes solution treatment and aging to obtain a fully lamellar microstructure. Finally, the pre-formed billet with the fully lamellar microstructure is subjected to final forging to obtain the dual-performance bladed disk. This method controls the shape of the pre-formed billet, thereby controlling the deformation of the billet during final forging, achieving spheroidization of the microstructure in the blade region, and ultimately obtaining a dual-target microstructure: a lamellar microstructure for the disk and an equiaxed microstructure for the blades.

[0010] However, the drawback of the above-mentioned method of manufacturing dual-performance bladed disks by forging is that it is difficult to accurately control the microstructure at the transition between the forged and non-forged zones, and there may be a "weak connection" phenomenon of discontinuous microstructure properties.

[0011] Compared to the process of obtaining dual-performance bladed disks through forging, differential temperature heat treatment can avoid the formation of forging defects and is easier to achieve precise temperature control, thus becoming the preferred process for manufacturing titanium alloy dual-performance integral bladed disks.

[0012] The literature (Cai Jianming, Tian Feng, Liu Dong, et al. Research progress on preparation technology of 600℃ high temperature titanium alloy dual-performance integral bladed disk forging [J]. Materials Engineering, 2018, 46(5):36-43.) and the literature (Cai Jianming, Li Juan, Tian Feng, et al. Manufacturing of high temperature titanium alloy dual-performance integral bladed disk for advanced aero-engines [J]. Aviation Manufacturing Technology, 2019, 62(19):34-40.) proposed a zoned temperature control heat treatment method, which adds an air-cooled jacket to the blades of the titanium alloy integral bladed disk. The air-cooled jacket device and the forging are subjected to β-zone heat treatment together, and the disk body is exposed to the furnace. This allows the blades to be forcibly cooled to the α+β zone while the disk body is subjected to β-zone heat treatment, thereby achieving differential temperature heat treatment and obtaining a dual structure. Similar patents such as CN112143872B, CN102643958B, CN112080622B, CN113061709B, and CN113234914B provide gradient heat treatment devices and heat treatment methods for disc-shaped parts with different structures.

[0013] Existing methods for preparing dual-performance bladed disks focus on how to obtain different dual-performance microstructures in the disk body and blade parts; similarly, existing differential temperature heat treatment devices also focus on how to achieve different heat treatment temperatures in the disk body and blade parts to obtain dual-performance microstructures.

[0014] For titanium alloy dual-performance bladed disks, not only must the disk body and blades obtain the corresponding expected microstructure, but also the width and position of the transition zone where the microstructure and properties change need to be precisely controlled to meet service and design requirements. However, this aspect has not been addressed in existing work. Summary of the Invention

[0015] The purpose of this invention is to overcome the shortcomings of the prior art and provide a method for precisely controlling the transition zone of a Ti6242S titanium alloy dual-performance integral bladed disk.

[0016] To achieve the above objectives, the technical solution adopted by the present invention is as follows: a differential temperature heat treatment furnace for titanium alloy dual-performance integral bladed disk, comprising upper and lower furnace bodies, and a differential temperature heat treatment cavity formed by the upper and lower furnace bodies for accommodating the integral bladed disk;

[0017] The integral bladed disk is supported in the differential temperature heat treatment chamber by a heat insulation cylinder. The heat insulation cylinder is correspondingly supported in the transition area between the disk body and the blades of the integral bladed disk. The heat insulation cylinder divides the differential temperature heat treatment chamber into a high-temperature zone at the center of the furnace chamber and a low-temperature zone at the edge of the furnace chamber.

[0018] The upper and lower furnace bodies, the differential temperature heat treatment chamber, and the heat insulation cylinder are all cylindrical, and the heat insulation cylinder has a circular cross-section, so that the central high-temperature zone and the edge low-temperature zone are both annular regions.

[0019] An air inlet and an exhaust outlet are provided on the furnace body corresponding to the edge low-temperature zone. The air inlet is connected to an air pump to adjust the flow rate of cold air in the edge low-temperature zone, thereby adjusting the temperature of the low-temperature zone. At least one pair of reference holes are symmetrically provided around the center of the furnace body in the central high-temperature zone for positioning reference of the heat insulation cylinder installation position.

[0020] Temperature-controlled heating resistance wires are distributed on the upper and lower furnace bodies inside the differential temperature heat treatment chamber to heat the entire bladed disk.

[0021] Furthermore, the transition zone between the disc and the blade is the temperature gradient zone between the disc and the blade; simultaneously, the temperature gradient zone near one end of the disc, and within the high-temperature zone at the center of the furnace cavity, is a high-temperature nonlinear zone, accounting for 0.28-0.46% of the temperature gradient zone; the temperature gradient zone near the blade end, and within the low-temperature zone at the edge of the furnace cavity, is a low-temperature nonlinear zone, accounting for 0.3-0.48% of the temperature gradient zone; the heat insulation cylinder is located in the quasi-linear zone in the middle part of the temperature gradient zone.

[0022] Furthermore, the width G of the quasi-linear region s It is equal to the thickness b of the insulation cylinder.

[0023] Furthermore, the heat insulation cylinder is composed of an upper heat insulation cylinder and a lower heat insulation cylinder respectively disposed in the differential temperature heat treatment chambers of the upper and lower furnace bodies, and the upper heat insulation cylinder and the lower heat insulation cylinder are symmetrically disposed on both sides of the axial direction of the integral bladed disk.

[0024] Furthermore, at least two pairs of air inlets are symmetrically arranged around the furnace body, and are respectively located on the upper and lower furnace bodies, for uniform cooling of the edge low-temperature zone by the cold airflow; at least one pair of exhaust outlets are symmetrically arranged around the furnace body.

[0025] Furthermore, the heating resistance wires are symmetrically arranged in the upper and lower furnace bodies, and are multiple heating resistance wires arranged in a ring shape concentrically and uniformly in the axial direction of the furnace body.

[0026] Furthermore, the material of the heat insulation cylinder is aluminum silicate fiber.

[0027] The present invention also provides a method for controlling the transition zone of a titanium alloy dual-performance integral bladed disk using the aforementioned differential temperature heat treatment furnace, comprising the following steps:

[0028] Step 1: Calculate the thickness b of the heat insulation cylinder.

[0029] The temperature of the central high-temperature zone corresponding to the disk body is defined as T. h The temperature of the low-temperature zone at the edge of the blade is T. l Substituting the integral bladed disk thickness t and the required width G of the transition zone between the disk and blades into the calculation formula for the insulation cylinder thickness b:

[0030]

[0031] This gives the value of the thickness b of the heat insulation cylinder;

[0032] Step 2: Calculate the width G of the high-temperature nonlinear region h ,

[0033] Temperature T of the central high-temperature zone h Temperature T in the edge low-temperature zone l Substituting the disk thickness t and the obtained insulation cylinder thickness b into the width G of the high-temperature nonlinear region... h The calculation formula is as follows:

[0034]

[0035] That is, the width G of the high-temperature nonlinear region is obtained. h The value;

[0036] Step 3: Determine the placement of the heat insulation cylinder.

[0037] That is, determining the distance S between point X, the midpoint of the insulation cylinder thickness along the radial straight line of the same integral bladed disk, and point O, the edge of the disk. OX The formula for calculating the distance between point X and point O is as follows:

[0038]

[0039] That is, the distance between point X and point O is obtained, where S OA It is the ring width of the disc body that enables precise control of the gradual transformation of the bi-state structure to the basket structure in the overall bladed disc transition zone.

[0040] Furthermore, the titanium alloy type of the titanium alloy dual-performance bladed disk is Ti6242S.

[0041] The beneficial effects of this invention are:

[0042] 1. By using the heat insulation cylinder structure of the differential temperature heat treatment furnace for titanium alloy dual-performance integral bladed disks, the differential temperature heat treatment process and the temperature field of the bladed disk can be controlled, thereby achieving control of the target microstructure area of ​​the bladed disk. It is applicable to a series of titanium alloy dual-performance bladed disks with different sizes, specifications and design requirements. It is simple to operate, highly controllable and has a wide range of applications.

[0043] 2. A quantitative relationship is given between the thickness of the heat insulation cylinder and the width of the transition zone and the high-temperature nonlinear zone of the Ti6242S titanium alloy dual-performance integral bladed disk during differential temperature heat treatment. The width and position of the transition zone can be accurately controlled by equation calculation, thus meeting the actual design requirements of the bladed disk. Attached Figure Description

[0044] Figure 1 This is a schematic diagram illustrating the microstructure requirements and differential temperature heat treatment of the dual-performance integral bladed disk of the present invention;

[0045] Figure 2 This is a schematic diagram of the differential temperature heat treatment furnace structure of the present invention;

[0046] Figure 3 This is a schematic diagram of the differential temperature heat treatment process for impeller disks according to the present invention.

[0047] Figure 4 This is a temperature distribution diagram of the transition zone during the heat treatment of the titanium alloy bladed disk of the present invention;

[0048] Figure 5 This is another temperature distribution diagram of the heat treatment transition zone of the titanium alloy bladed disk of the present invention. Detailed Implementation

[0049] The principles and features of the present invention are described below with reference to the accompanying drawings. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0050] The differential temperature heat treatment conditions and corresponding microstructure distribution of the α+β titanium alloy dual-performance bladed disk are shown in the following diagram. Figure 1 As shown, the disc body needs to undergo high-temperature heat treatment above the β phase transition point to obtain the high-temperature zone of the basket structure, while the blades need to undergo low-temperature heat treatment below the β phase transition point to obtain the low-temperature zone of the bimorphic structure; the temperature of the transition zone should be between the two and show a gradient change to obtain a gradual structure.

[0051] To achieve a dual-performance titanium alloy bladed disk, it is necessary not only to obtain the desired microstructure in the disk body and blades, but also to precisely control the width and position of the transition zone where microstructure and properties change to meet service and design requirements. To achieve the above objectives, the present invention provides the following specific implementation methods:

[0052] Example 1: As Figure 2 As shown, a titanium alloy dual-performance integral bladed disk differential temperature heat treatment furnace includes upper and lower furnace bodies 1, and a differential temperature heat treatment cavity 11 formed by the upper and lower furnace bodies 1 for accommodating the integral bladed disk 7.

[0053] The integral bladed disk 7 is supported in the differential temperature heat treatment chamber 11 by the heat insulation cylinder 2. The heat insulation cylinder 2 is composed of an upper heat insulation cylinder 21 and a lower heat insulation cylinder 22 respectively set in the differential temperature heat treatment chamber 11 of the upper and lower furnace bodies 1, and the upper heat insulation cylinder 21 and the lower heat insulation cylinder 22 are symmetrically arranged on both sides of the axial direction of the integral bladed disk 7. The heat insulation cylinder 2 is correspondingly supported in the transition area 73 between the disk body 71 and the blades 72 of the integral bladed disk 7. The heat insulation cylinder divides the differential temperature heat treatment chamber into a high temperature zone in the center of the furnace chamber and a low temperature zone at the edge of the furnace chamber. The upper and lower furnace bodies 1, the differential temperature heat treatment chamber 11 and the heat insulation cylinder 2 are all cylindrical, and the cross-section of the heat insulation cylinder 2 is annular, so that both the high temperature zone in the center and the low temperature zone at the edge are annular areas. The material of the heat insulation cylinder 2 is aluminum silicate fiber.

[0054] An air inlet 3 and an exhaust outlet 4 are provided on the furnace body 1 corresponding to the edge low temperature zone. The air inlet 3 is connected to an air pump to adjust the flow rate of cold air in the edge low temperature zone, thereby adjusting the temperature of the low temperature zone. Figure 2 As shown, at least two pairs of air inlets 3 are symmetrically arranged around the furnace body 1, and are respectively located on the upper and lower furnace bodies, for uniform cooling of the edge low-temperature zone by cold airflow; at least one pair of reference holes 5 are symmetrically arranged around the furnace body 1 in the center of the high-temperature zone, for positioning reference of the installation position of the heat insulation cylinder 2; at least one pair of exhaust ports 4 are symmetrically arranged around the furnace body 1.

[0055] Temperature-controlled heating resistance wires 6 are distributed on the upper and lower furnace bodies 1 within the differential temperature heat treatment chamber 11 to heat the entire bladed disk. The heating resistance wires 6 are symmetrically arranged on the upper and lower furnace bodies 1, and are multiple heating resistance wires arranged in a ring shape concentrically and uniformly in the axial direction of the furnace body 1.

[0056] like Figure 5As shown, in the differential temperature heat treatment furnace for titanium alloy dual-performance integral bladed disks, the transition zone 73 between the disk body 71 and blades 72 of the processed integral bladed disk is the temperature gradient zone between the disk body 71 and blades 72. Simultaneously, the temperature gradient zone near the end of the disk body 71, within the high-temperature zone at the center of the furnace cavity, is a high-temperature nonlinear zone, accounting for 0.28-0.46% of the temperature gradient zone; the temperature gradient zone near the end of the blades 72, within the low-temperature zone at the edge of the furnace cavity, is a low-temperature nonlinear zone, accounting for 0.3-0.48% of the temperature gradient zone. The heat insulation cylinder 2 is located in the quasi-linear zone in the middle part of the temperature gradient zone. The width G of the quasi-linear zone... s It is equal to the thickness b of the heat insulation cylinder 2.

[0057] Example 2: Figures 3-5 When using the heat insulation cylinder 2 to perform differential temperature heat treatment on the impeller, although the heat insulation cylinder 2 can divide the furnace cavity into a high-temperature zone at the center and a low-temperature zone at the edge, and both the high-temperature and low-temperature zones can reach the set temperature, due to the temperature difference between the high-temperature and low-temperature zones and the heat conduction effect of the impeller itself, the impeller temperature in the high-temperature zone at the center and the low-temperature zone at the edge of the furnace cavity cannot completely reach the set temperature of the furnace cavity respectively. Specifically, as follows... Figure 3 As shown, although the AB region on the bladed disk is entirely within the high-temperature zone at the center of the furnace cavity, its temperature is lower than the set temperature T of the high-temperature zone at the center of the furnace cavity. h Similarly, the temperature in the CD area is higher than the temperature T set in the low-temperature zone at the edge of the furnace cavity. l This is because the temperature field distribution of the impeller itself is continuous, and the temperature cannot change abruptly. Therefore, a temperature range from T is formed in the heat insulation cylinder 2 and on both sides. h To T l The gradually changing temperature gradient zone (AD zone) is a characteristic of the bladed disk temperature distribution during differential temperature heat treatment using the insulation cylinder 2. Therefore, the temperature gradient zone formed on the bladed disk during differential temperature heat treatment must correspond to the transition zone required by the bladed disk design to obtain a bladed disk that meets the actual design requirements. The transition zone includes both the temperature gradient zone of the bladed disk during differential temperature heat treatment and the resulting transition zone in the bladed disk structure.

[0058] Further research revealed that the transition region with a width of G can be divided into three sub-regions, namely the high-temperature nonlinear region with a width of G. h The quasi-linear region width is G s and the width of the low-temperature nonlinear region is G l The schematic diagram of its temperature distribution curve is shown below. Figure 4 , Figure 5 As shown, the width G of the quasi-linear region s The thickness b of the insulation cylinder 2 is equal to the temperature T in the high-temperature zone. h Temperature T in the low-temperature zone lThe thickness t of the transition zone disc and the thickness b of the insulation cylinder 2 have a significant impact on the width and position of the overall transition zone. Furthermore, T... h T l There is a certain mathematical relationship between t, b and the width G of the transition zone, namely G = f(T) h T l , t, b). When T h T l When t is determined by actual production conditions and design requirements, the width of the transition zone can be controlled by controlling the thickness of the insulation cylinder 2.

[0059] Furthermore, when the width G of the transition zone is determined by design requirements, the thickness b of the insulation cylinder 2 can be determined by mathematical inverse calculation. In addition, T h T l , t, b and the width G of the high-temperature nonlinear region h There is also a certain mathematical relationship between them, namely G h =f(T) h T l When the thickness b of the insulation cylinder 2 is determined, the width G of the high-temperature nonlinear region is... h Therefore, since the position of the heat insulation cylinder 2 is close to the high-temperature nonlinear region, the placement of the heat insulation cylinder 2 can be determined. This is the basic principle for controlling the width and position of the transition zone of the Ti6242S titanium alloy dual-performance integral bladed disk through the heat insulation cylinder 2. Based on this basic principle, the present invention also provides a method for controlling the transition zone of the titanium alloy dual-performance integral bladed disk using a differential temperature heat treatment furnace, including the following steps:

[0060] Step 1: Calculate the thickness b of the heat insulation cylinder 2.

[0061] Define the temperature of the central high-temperature zone corresponding to disk body 71 as T. h The temperature of the edge low-temperature zone corresponding to blade 72 is T. l Substituting the integral bladed disk thickness t and the required width G of the transition zone between the disk and the blades into the calculation formula for the insulation cylinder thickness b:

[0062]

[0063] That is, the value of the thickness b of the heat insulation cylinder 2 is obtained;

[0064] Step 2: Calculate the width G of the high-temperature nonlinear region h ,

[0065] Temperature T of the central high-temperature zone h Temperature T in the edge low-temperature zone l Substituting the plate thickness t and the obtained insulation cylinder 2 thickness b into the width G of the high-temperature nonlinear region... h The calculation formula is as follows:

[0066]

[0067] That is, the width G of the high-temperature nonlinear region is obtained. h The value;

[0068] Among them, the width G of the low-temperature nonlinear region l The calculation and G h The calculations are all based on the same principle. After determining the thickness b of the insulation cylinder 2, the placement of the insulation cylinder 2 will definitely be in the transition zone 73, such as... Figure 3 As shown, the transition zone 73 is the interval distance between points AD on the radial straight line of the entire bladed disk. Therefore, as long as G is determined... h and G l One of them, the distance between points AD is determined by the length of the segments AB, BC and CD, which are then divided into segments, and thus the placement of the heat insulation cylinder 2 is determined.

[0069] Step 3: Determine the placement of heat insulation cylinder 2.

[0070] That is, determining the distance S between point X, the midpoint of the thickness of the insulation cylinder 2 on the radial straight line of the same integral bladed disk, and point O, the edge of the disk. OX The formula for calculating the distance between point X and point O is as follows:

[0071]

[0072] That is, the distance between point X and point O is obtained, where S OA It is the ring width of the disc body that enables precise control of the gradual transformation of the bi-state structure to the basket structure in the overall bladed disc transition zone.

[0073] Furthermore, the titanium alloy type for the titanium alloy dual-performance bladed disk is Ti6242S.

[0074] To further understand the invention's content and features, the following embodiment is provided: According to design requirements, the thickness t of a Ti6242S titanium alloy dual-performance integral bladed disk is 50mm, the required transition zone width G is 200mm, the distance from the edge O point of the bladed disk to the starting position A point of the transition zone is 30mm, and the temperature T of the high-temperature zone during differential heat treatment is... h The temperature is 1020℃, and the temperature in the low-temperature zone is T. l The temperature is 960℃. The thickness b of the heat insulation cylinder 2 and its placement position are determined so that the width and position of the transition zone of the Ti6242S titanium alloy dual-performance bladed disk obtained after heat treatment meet the actual design requirements.

[0075] Step 1: Calculate the thickness b of the insulation cylinder 2; [The text abruptly ends here, likely due to an incomplete sentence or a formatting error.] h T lSubstitute the plate thickness t and the required transition zone width G into the following formula to calculate the thickness b of the heat insulation cylinder 2;

[0076]

[0077] Step 2: Calculate the width G of the high-temperature nonlinear region h ; T h T l Substituting the plate thickness t and the insulation cylinder thickness b determined in step two into the following formula, the width G of the high-temperature nonlinear region can be calculated. h :

[0078]

[0079] Step 3: Determine the placement of the heat insulation cylinder 2; that is, determine the distance between the center point X of the heat insulation cylinder 2 and the edge point O of the plate. The distance between point X and point O can be calculated using the following formula:

[0080]

[0081] Therefore, the required thickness of the heat insulation cylinder 2 is 19.2 mm, and the placement of the heat insulation cylinder 2 is such that the distance from the center point X of the heat insulation cylinder 2 to the edge point O of the disk body is 127.2 mm. Thus, the width and position of the transition zone of the Ti6242S titanium alloy dual-performance bladed disk under the design requirements have been achieved. By placing the heat insulation cylinder 2 of the determined thickness according to the requirements, the width and position of the transition zone of the Ti6242S titanium alloy dual-performance bladed disk obtained after heat treatment will meet the actual design requirements.

[0082] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for controlling the transition zone of a titanium alloy dual-performance integral bladed disk, characterized in that, Includes the following steps: Step 1: Calculate the thickness of the insulation cylinder (2) b , Define the temperature of the central high-temperature zone corresponding to the disk body (71) as follows: T h The temperature of the edge low-temperature zone corresponding to blade (72) is T l The overall thickness of the impeller disc is t The actual required width of the transition zone between the disk and the blades. G Substitute the thickness of the heat insulation cylinder (2) b The calculation formula is as follows: ， That is, the thickness of the heat insulation cylinder (2) is obtained. b The value; Among them, the thickness of the heat insulation cylinder (2) b The unit is mm; the width of the transition zone between the disc and the blades. G The unit is mm; the temperature of the central high-temperature zone T h and edge low temperature zone temperature T l All units are °C; disk thickness t The unit is mm; Step 2: Calculate the width of the high-temperature nonlinear region G h , Temperature of the central high-temperature zone T h Temperature of the edge low-temperature zone T l , disk thickness t and the thickness of the obtained heat insulation cylinder (2) b Substituting the width of the high-temperature nonlinear region G h The calculation formula is as follows: ， That is, the width of the high-temperature nonlinear region is obtained. G h The value; Among them, the width of the high-temperature nonlinear region G h The unit is mm; Step 3: Determine the placement of the heat insulation cylinder (2). That is, determining the midpoint of the thickness of the insulation cylinder (2) on the radial straight line of the same integral blade disk. X Points and the edge of the disk O Distance between points S OX ,use X Point and O The formula for calculating the distance between points: ， That is, the above is obtained X Point and O Distance between points S OX The unit is millimeters (mm), where, S OA It is the ring width of the disc body that enables precise control of the gradual transformation of the dual-state structure to the basket structure in the overall bladed disc transition zone; The control method of the transition zone of the titanium alloy dual-performance integral bladed disk is achieved by the control of the differential temperature heat treatment furnace, which includes an upper and lower furnace body (1) and a differential temperature heat treatment cavity (11) formed by the upper and lower furnace bodies (1) for accommodating the integral bladed disk (7). The integral bladed disk (7) is supported in the differential temperature heat treatment chamber (11) by the heat insulation cylinder (2). The heat insulation cylinder (2) is correspondingly supported in the transition area (73) between the disk body (71) and the blade (72) of the integral bladed disk (7). The heat insulation cylinder (2) divides the differential temperature heat treatment chamber (11) into a high temperature zone in the center of the furnace cavity and a low temperature zone at the edge of the furnace cavity. The transition area (73) between the disk body (71) and the blade (72) is the temperature gradient zone between the disk body (71) and the blade (72). The temperature gradient zone is close to one end of the disk body (71), and the high temperature nonlinear zone is located in the high temperature zone in the center of the furnace cavity. The upper and lower furnace bodies (1), the differential temperature heat treatment chamber (11), and the heat insulation cylinder (2) are all cylindrical, and the cross-section of the heat insulation cylinder (2) is annular, so that the central high temperature zone and the edge low temperature zone are both annular regions. An air inlet (3) and an exhaust outlet (4) are provided on the furnace body (1) corresponding to the edge low temperature zone. The air inlet (3) is connected to an air pump and is used to adjust the flow rate of cold air in the edge low temperature zone, thereby adjusting the temperature of the low temperature zone. At least one pair of reference holes (5) are symmetrically provided around the furnace body (1) in the center of the central high temperature zone for positioning reference of the heat insulation cylinder (2). Temperature-controlled heating resistance wires (6) are distributed on the upper and lower furnace bodies (1) inside the differential temperature heat treatment chamber (11) to heat the entire bladed disk.

2. The method for controlling the transition zone of a titanium alloy dual-performance integral bladed disk as described in claim 1, characterized in that, The high-temperature nonlinear region accounts for 0.28-0.46% of the temperature gradient region; the low-temperature nonlinear region is located near the blade (72) end and in the low-temperature region at the edge of the furnace cavity. The low-temperature nonlinear region accounts for 0.3-0.48% of the temperature gradient region. The heat insulation cylinder (2) is located in the quasi-linear region in the middle part of the temperature gradient region.

3. The method for controlling the transition zone of a titanium alloy dual-performance integral bladed disk as described in claim 2, characterized in that, The width of the quasi-linear region G s Equal to the thickness of the heat insulation cylinder (2) b。 4. The method for controlling the transition zone of a titanium alloy dual-performance integral bladed disk as described in claim 1, characterized in that, The heat insulation cylinder (2) is composed of an upper heat insulation cylinder (21) and a lower heat insulation cylinder (22) respectively installed in the differential temperature heat treatment chamber (11) of the upper and lower furnace bodies (1), and the upper heat insulation cylinder (21) and the lower heat insulation cylinder (22) are symmetrically arranged on both sides of the integral bladed disk (7).

5. The method for controlling the transition zone of a titanium alloy dual-performance integral bladed disk as described in claim 1, characterized in that, The air inlets (3) are provided symmetrically in two pairs around the furnace body (1), and are respectively located on the upper furnace body and the lower furnace body, for uniform cooling of the edge low temperature zone by the cold airflow; the exhaust ports (4) are provided symmetrically in one pair around the furnace body (1).

6. The method for controlling the transition zone of a titanium alloy dual-performance integral bladed disk as described in claim 1, characterized in that, The heating resistance wires (6) are symmetrically arranged on the upper and lower furnace bodies (1), and are multiple heating resistance wires arranged in a ring shape in a concentric and uniform manner along the axial direction of the furnace body (1).

7. The method for controlling the transition zone of a titanium alloy dual-performance integral bladed disk as described in any one of claims 1-6, characterized in that, The material of the heat insulation cylinder (2) is aluminum silicate fiber.

8. The method for controlling the transition zone of a titanium alloy dual-performance integral bladed disk as described in any one of claims 1-6, characterized in that, The titanium alloy used in the aforementioned dual-performance titanium alloy bladed disk is Ti6242S.

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