Titanium alloy dual-performance blisk differential temperature heat treatment furnace and transition area control method

Abstract

The invention relates to a titanium alloy dual-performance blisk differential temperature heat treatment furnace which comprises an upper furnace body, a lower furnace body and a differential temperature heat treatment cavity defined by the upper furnace body and the lower furnace body and used for containing a blisk. The blisk is supported in the differential-temperature heat treatment cavity through the heat insulation cylinder, and the heat insulation cylinder is correspondingly supported in a transition area between a blisk body and blades of the blisk, so that the heat insulation cylinder divides the differential-temperature heat treatment cavity into a center high-temperature area corresponding to the blisk body and an edge low-temperature area corresponding to the blades. The invention further provides a control method of the differential temperature heat treatment furnace for the blisk transition area. By means of the method, control over the target structure area of the blisk through differential temperature heat treatment of the titanium alloy dual-performance blisk is achieved, simple operation of the differential temperature heat treatment technology is achieved, and controllability of the transition area of the blisk is improved.

Description

Technical Field

[0001] The present invention and the technical field of titanium alloy heat treatment particularly relate to a method for controlling a transition zone of a titanium alloy integral blade disk. Background Art

[0002] High-temperature titanium alloys have become the preferred material for aircraft engine compressor integral blades due to their high specific strength, good thermal strength and other advantages. The service environment of different parts of the integral blade is very different, and there are large temperature gradients and stress gradients along its radial direction; blades with uniform microstructures are often difficult to simultaneously meet the different requirements of heat and force capacity of different parts, and are bound to lose certain performance. In order to maximize high efficiency and high reliability, the blades and the disc body should have microstructures and performance (dual performance) that match the service conditions. The blades are mainly subjected to high-frequency and low-amplitude vibrations, and should have a dual-state structure containing primary equiaxed α phase and secondary lamellar α phase to ensure high-cycle fatigue, strength, plasticity, etc. The disk body is subjected to large centrifugal stress and thermal stress, and should have a basket-weave structure containing only secondary lamellar α phase to ensure high-temperature creep, fracture toughness, etc. The transition zone between the blades and the disk body should have a structure that gradually transforms from the dual-state structure to the basket-weave structure. Therefore, the width and position of the transition zone of the dual-performance blade of titanium alloy, the disk body, blades and the gradual transition zone of the structure have been determined according to its service requirements. The key is how to obtain the expected structure type in the disk body and blade parts through reasonable processing and manufacturing methods, and to achieve precise control of the position and width of the transition zone.

[0003] The concept of dual-performance disks and their manufacturing technology 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, and is aimed at a single type of microstructure and constituent phase. U.S. patents with publication numbers 5527402, US6478896B1 and US6660110B1 and Chinese patents with authorization announcement numbers CN110788562B, CN102615284B, CN111187895B and CN112464533B obtain high-temperature alloy dual-performance turbine disks through different technical means. However, titanium alloys are mostly dual-phase materials (e.g., primary equiaxed α phase and secondary lamellar α phase), which involve complex phase changes during hot working. The principle of achieving dual performance is to obtain different types of microstructures in different regions of the component using phase change characteristics. Therefore, the existing manufacturing technology 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 of using dissimilar alloys to prepare titanium alloy dual-performance blade disks. The blades of another alloy are connected to the disk body on a titanium alloy disk body through additive manufacturing technology, thereby obtaining a dual-alloy dual-performance blade disk. However, dual-alloy dual-performance blade disks have the following shortcomings: First, the connection interface of dissimilar alloys may be a "weak" area; second, if the elastic modulus of dissimilar alloys differ greatly, it will cause greater thermal stress on the interface; third, if the same heat treatment process is used for subsequent heat treatment, the mechanical properties of the two alloys will be compromised.

[0005] Authorization announcement number CN115055696B proposes a method for manufacturing an aircraft engine titanium alloy integral blade disk, that is, connecting the finished wheel disk and the finished blade into one by linear friction welding to obtain an integral blade disk semi-finished product, and machining the integral blade disk semi-finished product to obtain an integral blade disk finished product; however, the linear friction welding process is highly dependent on equipment, and the welding effect and accuracy depend to a large extent on the capacity of the equipment, and the welding tooling is complex and costly. At the same time, titanium alloys with poor plasticity are prone to welding cracks during linear friction welding.

[0006] U.S. Patent Nos. 5,795,413 and 6,110,302 propose a method for preparing titanium alloy dual-performance disks by local forging. First, the α+β titanium alloy preform is subjected to β heat treatment or β forging, and then heated to the α+β two-phase region temperature for local forging, so that different microstructures are formed in the forged area and the unforged area.

[0007] The patent with authorization announcement number CN101629273B first obtains the full lamellar structure by forging the billet and preparing the prefabricated billet, and then controls the different deformation amounts in each area through multiple local loadings, thereby obtaining different microstructures in different areas.

[0008] The literature (Cai Jianming, Tian Feng, Liu Dong, et al. Research progress in the preparation technology of 600℃ high-temperature titanium alloy dual-performance integral blade forgings [J]. Materials Engineering, 2018, 46(5): 36-43.) proposed a similar zone temperature controlled forging method. The lamellar structure is obtained by forging deformation in the β single-phase zone in the first fire, and then the α+β two-phase zone forging is carried out in the second fire. Different microstructures are obtained by controlling the deformation amount of different areas in the second fire.

[0009] The authorization announcement number CN114378233B proposes a manufacturing method for a Ti2AlNb-based alloy dual-performance integral blade disk, which first obtains a preform of a certain shape and size through pre-forging, then performs a solid solution aging treatment on the preform to obtain a full lamellar structure, and finally performs a final forging on the preform with a full lamellar structure to obtain a dual-performance blade disk. This method controls the shape of the preform, thereby controlling the deformation of the blank during final forging, achieving spheroidization of the blade part structure, and finally obtaining a dual-target structure of a lamellar structure for the disk body and an equiaxed structure for the blade.

[0010] However, the disadvantage of the above-mentioned method of manufacturing dual-performance blades by forging is that it is difficult to accurately control the structure of the transition between the forging area and the non-forging area, and there is a high possibility of a "weak connection" phenomenon in which the structure and performance are discontinuous.

[0011] Compared with the process of obtaining dual-performance blades through forging, the differential temperature heat treatment process can avoid the formation of forging defects on the one hand; on the other hand, it is easy to achieve precise temperature control, thus becoming the preferred process for manufacturing titanium alloy dual-performance integral blades.

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

[0013] For the existing preparation method of dual-performance blade disk, the focus is on how to obtain different dual-performance structures in the disk body and blade parts; for the existing differential temperature heat treatment device, the focus is also on how to achieve different heat treatment temperatures in the disk body and blade parts to obtain dual-performance structures.

[0014] For titanium alloy dual-performance blades, not only the expected structures must be obtained in the blade body and blades, but also the width and position of the transition zone where the structure and performance 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 the present invention is to avoid the shortcomings of the prior art and provide a Ti6242S titanium alloy dual-performance integral blade disk transition zone control method that can be accurately controlled.

[0016] To achieve the above object, the technical solution adopted by the present invention is: a titanium alloy dual-performance integral blade disk differential temperature heat treatment furnace, comprising an upper furnace body and a lower furnace body, and a differential temperature heat treatment chamber surrounded by the upper and lower furnace bodies for accommodating the integral blade disk;

[0017] The integral blade disk is supported in the differential temperature heat treatment chamber by a heat insulation tube, and the heat insulation tube is correspondingly supported and arranged in the transition zone between the disk body and the blades of the integral blade disk, and the heat insulation tube 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;

[0018] The upper and lower furnace bodies, the differential temperature heat treatment chamber and the heat insulation tube are all cylindrical, and the cross section of the heat insulation tube is annular, so that the central high temperature zone and the edge low temperature zone are both areas with annular cross sections;

[0019] An air inlet and an air outlet are provided on the furnace body corresponding to the edge low-temperature zone, and the air inlet is connected to an air pump to adjust the flow rate of the cold air flow 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 on the circumference of the furnace body in the central part of the central high-temperature zone for positioning reference of the installation position of the heat insulation cylinder;

[0020] Temperature-controllable heating resistance wires are distributed on the upper and lower furnace bodies in the differential temperature heat treatment chamber to heat the integral blade disk.

[0021] Furthermore, the transition zone between the disk and the blades is the temperature gradient zone between the disk and the blades; at the same time, the temperature gradient zone is close to one end of the disk and in the high temperature zone in the center of the furnace cavity is a high temperature nonlinear zone, and the high temperature nonlinear zone accounts for 0.28-0.46 of the temperature gradient zone; the low temperature nonlinear zone is close to the blade end and in the low temperature zone at the edge of the furnace cavity, and the low temperature nonlinear zone accounts for 0.3-0.48 of the temperature gradient zone; the insulation tube is arranged in the quasi-linear zone in the middle part of the temperature gradient zone.

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

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

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

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

[0026] Furthermore, the material of the thermal insulation tube is aluminum silicate fiber.

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

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

[0029] Define the temperature of the central high temperature zone corresponding to the disk as T h The temperature of the edge low temperature zone corresponding to the blade is T l , the thickness of the integral blade disk is t and the actual required width of the transition zone between the blade and the disk is G, and then substituted into the calculation formula of the thickness of the insulation tube b:

[0030]

[0031] That is, the value of the thickness b of the insulation tube is obtained;

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

[0033] The central high temperature zone temperature T h , edge low temperature zone temperature T l , the thickness of the disk t and the thickness of the insulation tube b obtained are substituted into the width G of the high temperature nonlinear zone h The calculation formula is:

[0034]

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

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

[0037] That is to determine the distance S between the midpoint X of the insulation tube thickness and the edge O of the disk body on the same radial straight line of the integral blade disk. OX , use the distance calculation formula between point X and point O:

[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 realizes the precise control of the gradual transformation of the bimodal structure in the transition zone of the entire blade disc to the basket structure.

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

[0041] The beneficial effects of the present invention are:

[0042] 1. Through the heat-insulating tube structure of the titanium alloy dual-performance integral blade disk differential temperature heat treatment furnace, the control of the titanium alloy dual-performance integral blade disk differential temperature heat treatment process and the blade disk temperature field is realized, thereby realizing the control of the blade disk target tissue area. It can be applied to a series of titanium alloy dual-performance blade disks with different sizes, specifications and design requirements. It is simple to operate, has strong controllability and a wide range of applications.

[0043] 2. The quantitative relationship between the thickness of the insulation tube and the width of the transition zone and high-temperature nonlinear zone of the Ti6242S titanium alloy dual-performance integral blade during differential temperature heat treatment is given. The width and position control of the transition zone can be accurately achieved by equation calculation, thus meeting the actual design requirements of the blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 Schematic diagram of the dual-performance blisk organizational requirements and differential temperature heat treatment of the present invention;

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

[0046] Figure 3 This is a schematic diagram of the differential temperature heat treatment process of the blade disk of the present invention;

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

[0048] Figure 5 This is another temperature distribution diagram of the transition zone of the heat treatment of the titanium alloy blade disk of the present invention. DETAILED DESCRIPTION

[0049] The principles and features of the present invention are described below in conjunction with the accompanying drawings. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention.

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

[0051] In order to make the titanium alloy dual-performance blade disk not only obtain the corresponding expected structure in the disk body and blades, but also for the transition zone where the structure and performance change, its width and position need to be accurately controlled to meet the service and design requirements. In order to achieve the above purpose, the present invention provides the following specific implementation methods:

[0052] Example 1: Figure 2 As shown, a titanium alloy dual-performance integral blade disk differential temperature heat treatment furnace comprises an upper furnace body 1 and a lower furnace body 1, and a differential temperature heat treatment chamber 11 surrounded by the upper furnace body 1 and used for accommodating the integral blade disk 7;

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

[0054] An air inlet 3 and an air 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 the cold air flow in the edge low temperature zone, thereby adjusting the temperature of the low temperature zone. Figure 2 As shown in the figure, at least two pairs of air inlets 3 are symmetrically provided in the circumference of the furnace body 1, and are respectively arranged on the upper furnace body and the lower furnace body, for uniform cooling of the edge low-temperature zone by the cold air flow; at least one pair of reference holes 5 are symmetrically provided in the circumference of the furnace body 1 in the central part of the central high-temperature zone, for positioning reference of the installation position of the insulation tube 2; at least one pair of exhaust ports 4 are symmetrically provided in the circumference of the furnace body 1.

[0055] Temperature-controllable heating resistors 6 are provided on the upper and lower furnace bodies 1 in the differential temperature heat treatment chamber 11 to heat the integral blade disk. The heating resistors 6 are symmetrically arranged on the upper and lower furnace bodies 1 and are multiple heating resistors arranged uniformly and concentrically in a ring shape in the axial direction of the furnace body 1.

[0056] like Figure 5As shown, in the titanium alloy dual-performance integral blade disk differential temperature heat treatment furnace, the transition zone 73 between the disk body 71 and the blade 72 of the processed integral blade disk is the temperature gradient zone between the disk body 71 and the blade 72; at the same time, the temperature gradient zone is close to one end of the disk body 71 and in the high temperature zone in the center of the furnace cavity is a high temperature nonlinear zone, and the proportion of the high temperature nonlinear zone in the temperature gradient zone is 0.28-0.46; close to the end of the blade 72 and in the low temperature zone at the edge of the furnace cavity is a low temperature nonlinear zone, and the proportion of the low temperature nonlinear zone in the temperature gradient zone is 0.3-0.48; the insulation tube 2 is set in the quasi-linear zone in the middle part of the temperature gradient zone. The width G of the quasi-linear zone s Equal to the thickness b of the insulation tube 2.

[0057] Example 2: Figure 3-Figure 5 When using the insulation tube 2 to perform differential temperature heat treatment on the blade disk, although the insulation tube 2 can divide the furnace cavity into a high temperature zone in the center of the furnace cavity and a low temperature zone at the edge of the furnace cavity, both the high temperature zone and the low temperature zone can reach the set temperature. However, due to the temperature difference between the high temperature zone and the low temperature zone and the heat conduction of the blade disk itself, the temperature of the blade disk in the high temperature zone in the center of the furnace cavity and the low temperature zone at the edge of the furnace cavity cannot fully reach the set temperature of the furnace cavity. Figure 3 As shown in the figure, although the AB area on the blade disk is completely in the high temperature area in the center of the furnace cavity, its temperature is lower than the set temperature T of the high temperature area in the center of the furnace cavity. h Similarly, the temperature of the CD zone is higher than the temperature T set at the low temperature zone at the edge of the furnace cavity. l This is because the temperature field distribution of the blade disk itself is continuous and the temperature cannot suddenly change. Therefore, the insulation tube 2 and the two sides will form a temperature from T h To T l The gradually changing temperature gradient zone AD is a characteristic of the temperature distribution of the blade disk when the heat insulation tube 2 is used for differential temperature heat treatment. Therefore, the temperature gradient zone formed on the blade disk during the differential temperature heat treatment must correspond to the transition zone required by the blade disk design, so that a blade disk that meets the actual design requirements can be obtained. The transition zone includes the temperature gradient zone of the blade disk during the differential temperature heat treatment and the blade disk tissue transition zone generated by it.

[0058] Further research found that the transition zone width G can be divided into three sub-regions, namely, the high temperature nonlinear zone width G h , the width of the quasi-linear region is G s and the low temperature nonlinear region width is G l The temperature distribution curve is shown in the figure below: Figure 4 , Figure 5 As shown, the width G of the quasi-linear region s Equal to the thickness b of the insulation tube 2. High temperature zone temperature T h , low temperature zone temperature T l, the thickness of the transition zone disk t, and the thickness of the insulation tube 2 b have a significant impact on the width and position of the overall transition zone. 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 according to actual production conditions and design requirements, the width of the transition zone can be controlled by controlling the thickness of the insulation tube 2.

[0059] When the width G of the transition zone is determined according to design requirements, the thickness b of the insulation tube 2 can be determined by inverse mathematical relationship. h , T l , t, b and the width of the high temperature nonlinear region G h There is also a certain mathematical relationship between them, namely, G h =f(T h , T l , t, b). When the thickness b of the heat insulation tube 2 is determined, the width G of the high temperature nonlinear zone h It is also determined accordingly, and because the position of the heat insulation tube 2 is close to the high-temperature nonlinear zone, the placement position of the heat insulation tube 2 can be determined. This is the basic principle of controlling the width and position of the transition zone of the Ti6242S titanium alloy dual-performance integral blade disk by the heat insulation tube 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 blade disk using a differential temperature heat treatment furnace, comprising the following steps:

[0060] Step 1: Calculate the thickness b of the insulation tube 2,

[0061] Define the temperature of the central high temperature area corresponding to the disk 71 as T h , the edge low temperature area temperature corresponding to blade 72 is T l , the thickness of the integral blade disk is t and the actual required width of the transition zone between the blade and the disk is G, and the calculation formula of the thickness b of the insulation tube 2 is substituted into:

[0062]

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

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

[0065] The central high temperature zone temperature T h , edge low temperature zone temperature T l , the thickness of the disk t and the thickness b of the insulation tube 2 are substituted into the width G of the high temperature nonlinear zone h The calculation formula is:

[0066]

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

[0068] Among them, the width of the low temperature nonlinear region G l Calculation and G h The calculation of is the same in principle. After the thickness b of the heat insulation tube 2 is determined, the placement position of the heat insulation tube 2 must be in the transition zone 73. Figure 3 As shown in , the transition zone 73 is the interval distance of the AD point on the radial straight line of the integral blade disk, so as long as G is determined h and G l In one of them, the interval distance of point AD is determined by the length of the divided AB segment, BC segment and CD segment, and then the placement position of the insulation tube 2 is determined.

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

[0070] That is, determine the distance S between the midpoint X of the thickness of the heat insulation tube 2 and the edge O of the disk body on the same radial straight line of the integral disk. OX , use the distance calculation formula between point X and point O:

[0071]

[0072] That is, we get the distance between point X and point O, where S OA It is the ring width of the disc body that realizes the precise control of the gradual transformation of the bimodal structure in the transition zone of the entire blade disc to the basket structure.

[0073] Furthermore, the titanium alloy type of the titanium alloy dual performance blade is Ti6242S.

[0074] In order to further understand the content and features of the present invention, the following examples are given: According to the design requirements, the thickness t of a Ti6242S titanium alloy dual-performance integral blade disk is 50 mm, the transition zone width G required by the blade disk is 200 mm, the distance between the blade edge point O and the starting position A of the transition zone is 30 mm, and the high temperature zone temperature T during differential heat treatment is 100 mm. h is 1020℃, the low temperature zone temperature T l The temperature is 960° C. The thickness b of the heat insulation tube 2 and its placement position are determined so that the width and position of the transition zone of the Ti6242S titanium alloy dual-performance blade disk obtained after heat treatment meet the actual design requirements.

[0075] Step 1: Calculate the thickness b of the insulation tube 2; h , T l, the thickness of the plate t and the transition zone width G required by the design are substituted into the following formula to calculate the thickness b of the heat insulation tube 2;

[0076]

[0077] Step 2: Calculate the width G of the high temperature nonlinear region h ; T h , T l , the thickness of the plate t and the thickness b of the heat insulation tube 2 determined in step 2 are substituted into the following formula to calculate the width G of the high temperature nonlinear zone h :

[0078]

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

[0080]

[0081] Therefore, the required thickness of the heat insulation tube 2 is 19.2 mm, and the placement position of the heat insulation tube 2 is 127.2 mm from the center point X of the heat insulation tube 2 to the edge point O of the disk body. So far, the width and position of the transition zone of the Ti6242S titanium alloy dual-performance blade disk under the design requirements have been achieved, that is, the heat insulation tube 2 with a determined thickness is placed as required, so that the width and position of the transition zone of the Ti6242S titanium alloy dual-performance blade disk obtained after heat treatment can meet the actual design requirements.

[0082] The above are only 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 in the protection scope of the present invention.

Claims

1. A titanium alloy dual-performance integral blade differential heat treatment furnace, characterized in that: It comprises an upper furnace body (1) and a lower furnace body (1), and a differential temperature heat treatment chamber (11) formed by the upper furnace body (1) and used for accommodating an integral blade disk (7); The integral blade disk (7) is supported in the differential temperature heat treatment chamber (11) by means of a heat insulation tube (2), the heat insulation tube (2) is correspondingly supported and arranged in a transition zone (73) between the disk body (71) and the blades (72) of the integral blade disk (7), and the heat insulation tube (2) divides the differential temperature heat treatment chamber (11) 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 tube (2) are all cylindrical, and the cross section of the heat insulation tube (2) is annular, so that the central high temperature zone and the edge low temperature zone are both areas with a ring-shaped cross section; An air inlet (3) and an air outlet (4) are provided on the furnace body (1) corresponding to the edge low-temperature zone, and the air inlet (3) is connected to an air pump and is used to adjust the flow rate of the cold air flow 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 in the circumferential direction of the furnace body (1) in the central part of the central high-temperature zone, which are used for positioning reference of the installation position of the heat insulation tube (2); Temperature-controllable heating resistor wires (6) are distributed on the upper and lower furnace bodies (1) in the differential temperature heat treatment chamber (11) to heat the entire blade disk.

2. The titanium alloy dual-performance integral blade differential heat treatment furnace according to claim 1, characterized in that: The transition zone (73) between the disk (71) and the blade (72) is the temperature gradient zone between the disk (71) and the blade (72); at the same time, the temperature gradient zone is close to one end of the disk (71) and is in the high temperature zone in the center of the furnace cavity. It is a high temperature nonlinear zone, and the proportion of the high temperature nonlinear zone in the temperature gradient zone is 0.28-0.46; the temperature gradient zone is close to the end of the blade (72) and is in the low temperature zone at the edge of the furnace cavity. It is a low temperature nonlinear zone, and the proportion of the low temperature nonlinear zone in the temperature gradient zone is 0.3-0.48; the insulation tube (2) is arranged in the quasi-linear zone in the middle part of the temperature gradient zone.

3. The titanium alloy dual-performance integral blade differential heat treatment furnace according to claim 2, characterized in that: The width G of the quasi-linear region s Equal to the thickness b of the insulation tube (2).

4. The titanium alloy dual-performance integral blade differential heat treatment furnace according to claim 1, characterized in that: The insulation tube (2) is composed of an upper insulation tube (21) and a lower insulation tube (22) which are respectively arranged in the differential temperature heat treatment chamber (11) of the upper and lower furnace bodies (1), and the upper insulation tube (21) and the lower insulation tube (22) are symmetrically arranged on both axial sides of the integral blade disk (7).

5. The titanium alloy dual-performance integral blade differential heat treatment furnace according to claim 1, characterized in that: At least two pairs of the air inlets (3) are symmetrically arranged around the furnace body (1), and are respectively arranged on the upper furnace body and the lower furnace body, for uniformly cooling the low-temperature zone at the edge by the cold air flow; at least one pair of the exhaust ports (4) are symmetrically arranged around the furnace body (1).

6. The titanium alloy dual-performance integral blade differential heat treatment furnace according to 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 that are arranged in a ring-like shape and are concentrically and evenly arranged in sequence in the axial direction of the furnace body (1).

7. The titanium alloy dual-performance integral blade differential heat treatment furnace according to any one of claims 1 to 6, characterized in that: The material of the heat insulation cylinder (2) is aluminum silicate fiber.

8. A method for controlling the transition zone of a titanium alloy dual-performance integral blade disk using the differential temperature heat treatment furnace as described in claims 1-7, characterized in that: The following steps are involved: Step 1: Calculate the thickness b of the thermal insulation tube (2). The temperature of the central high temperature zone corresponding to the disk (71) is defined as T h The temperature of the edge low temperature zone corresponding to the blade (72) is T l , the thickness of the integral blade disk is t and the actual required width of the transition zone between the blade and the disk is G, and the calculation formula of the thickness b of the insulation tube (2) is substituted as follows: That is, the value of the thickness b of the heat insulation tube (2) is obtained; Step 2: Calculate the width G of the high temperature nonlinear region h , The central high temperature zone temperature T h , edge low temperature zone temperature T l , the thickness of the disk t and the thickness b of the insulation tube (2) are substituted into the width G of the high temperature nonlinear zone h The calculation formula is: That is, the width G of the high temperature nonlinear region is obtained. h The value of Step 3: Determine the placement of the heat insulation tube (2). That is, the distance S between the midpoint X of the thickness of the heat insulation tube (2) and the edge O of the disk body on the same radial straight line of the integral disk is determined. OX , use the distance calculation formula between point X and point O: 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 realizes the precise control of the gradual transformation of the bimodal structure in the transition zone of the entire blade disc to the basket structure.

9. The control method of the transition zone of the titanium alloy dual-performance integral blade disk according to claim 8, characterized in that: The titanium alloy type of the titanium alloy dual-performance blade disk is Ti6242S.

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