Double-wall air-cooled blade simulator and preparation method and preparation system thereof

Abstract

The invention discloses a double-wall air-cooled blade simulation piece and a preparation method and a preparation system thereof, and relates to the technical field of testing. According to the preparation method of the double-layer-wall air-cooled blade simulation piece, the single-crystal high-temperature alloy double-layer thin-wall turbulent flow column simulation piece with secondary orientation and controllable characteristic structure can be prepared. In practical application, by adjusting the assembling mode and the assembling structure of the casting intermediate, single-crystal high-temperature alloy double-layer thin-wall turbulent flow column castings with different primary orientation, secondary orientation, wall thicknesses and turbulent flow column sizes can be prepared, so that various service test requirements are met. The preparation system of the double-wall air-cooled blade simulation part is mainly used for implementing the preparation method of the double-wall air-cooled blade simulation part, and the prepared double-wall air-cooled blade simulation part fills the technical blank of simulation parts for turbine blades of a double-wall air-cooled structure at present; accurate service test data can be provided for optimizing the complex cooling structure of the turbine blade and prolonging the service life of the turbine blade structure.

Description

Technical Field

[0001] The present invention relates to the field of testing technology, and in particular to a method for preparing a double-walled air-cooled blade simulation component, a preparation system, and a double-walled air-cooled blade simulation component prepared by the preparation method. Background Art

[0002] Single crystal high temperature alloys are widely used in the field of turbine blades of advanced aircraft engines and gas turbines due to their excellent high temperature mechanical properties. With the continuous increase in engine thrust demand, the inlet temperature of the engine turbine has risen sharply. In order to improve the cooling efficiency of the blades, the turbine blades of advanced aircraft engines mostly use a complex hollow double-wall air-cooled structure. However, this structure causes the single crystal high temperature alloy blades to produce "thin wall effect", "structural stress concentration effect" and "thermal stress concentration effect", which have become important factors that need to be considered for the reliable service of advanced aircraft engines.

[0003] However, in the current blade development process, there is no work on material service tests (tensile, creep, durability, fatigue, etc.) for double-wall air-cooled structures, and there is a lack of disclosure of the service behavior and damage characteristics of materials under the coupling constraints of double-wall air-cooled structures. Based on this, the present invention proposes a preparation method and a preparation system for a double-wall air-cooled blade simulation part, and a double-wall air-cooled blade simulation part prepared by the preparation method, so as to fill the technical gap of blade simulation parts based on double-wall air-cooled structures. Summary of the invention

[0004] The purpose of the present invention is to provide a double-wall air-cooled blade simulation part preparation method, a preparation system and a double-wall air-cooled blade simulation part prepared by the preparation method. The simulation part can reflect the secondary orientation of the double-wall air-cooled structure of the real blade, and the characteristic structure is controllable. It can be used to study the service damage behavior of materials under different mechanical service tests and ensure the test accuracy. It fills the current technical gap in simulation parts for double-wall air-cooled structure turbine blades, and can provide accurate service test data for optimizing the complex cooling structure of turbine blades and improving the service life of turbine blade structures.

[0005] To achieve the above object, the present invention provides the following solutions:

[0006] The present invention provides a method for preparing a double-walled air-cooled blade simulation part, which is used for integrally casting a double-walled air-cooled blade simulation part, comprising the steps of:

[0007] S1, preparing a core that matches the shape and size of the target casting, wherein a middle section of the core is provided with a plurality of spoiler column forming holes for forming spoiler columns;

[0008] S2, cutting a seed crystal with a desired primary orientation and a desired secondary orientation from a single crystal high-temperature alloy sample, injecting wax around the periphery of the seed crystal to form a seed crystal amplifier, and connecting the seed crystal amplifier to a secondary amplifier to obtain a combined amplifier;

[0009] S3, attaching wax paper 1 to the surface of the ceramic sheet, wherein the lateral width and thickness of the wax paper 1 are the same as one of the inner and outer walls of the target casting, the middle section is arranged directly above the wax paper 1, and the length and lateral width of the wax paper 1 are respectively the same as the length and lateral width of the middle section;

[0010] S4, connecting wax paper 2 and wax paper 3 to the two ends of the length direction of wax paper 1 along the length direction of the ceramic sheet, respectively, the thickness of wax paper 2 and wax paper 3 are the same, and the thickness of wax paper 2 and wax paper 3 are both the sum of the thickness of wax paper 1 and the thickness of the middle section, and the lateral width of wax paper 2 and wax paper 3 is the same as the lateral width of the middle section;

[0011] S5, laminating and covering the surfaces of the middle section, the wax paper two and the wax paper three with wax paper four, to obtain a casting body adapted to the double-wall spoiler column structure of the target casting, wherein the thickness of the wax paper four is the same as the thickness of the other of the inner and outer walls of the target casting;

[0012] S6, combining and connecting the combined amplifier obtained in step S2 with the end surfaces of the wax paper 3 and the wax paper 4 to obtain a casting intermediate;

[0013] S7, assembling the casting intermediate onto a pouring plate, then slurry coating the casting intermediate to form a shell, and after dewaxing, obtaining a casting mold with seed crystals that matches the shape and size of the target casting;

[0014] S8. Casting the alloy melt into the casting mold to obtain a secondary oriented alloy double-layer thin-walled spoiler column casting, and then opening a plurality of impact holes on the inner wall of the secondary oriented alloy double-layer thin-walled spoiler column casting, and opening a plurality of air film holes on the outer wall of the secondary oriented alloy double-layer thin-walled spoiler column casting to form the double-layer wall air-cooled blade simulation part.

[0015] In one embodiment, the core is a ceramic core prepared by 3D printing technology.

[0016] In one embodiment, the middle section of the core is a rectangular flat plate structure, and the spoiler column forming hole is opened in the central area of ​​the middle section.

[0017] In one embodiment, positioning ribs are symmetrically provided at both lateral ends of the middle section, and the positioning ribs are used to cooperate and connect with the shell during the process of forming the shell in step S7.

[0018] In one embodiment, in step S4, the wax paper 2, the wax paper 3, the wax paper 1 and the middle section are aligned on both sides in the width direction; the wax paper 2 and the wax paper 3 have the same length, and when placed, one end of the wax paper 2 in the length direction is seamlessly connected to the wax paper 1 and the middle section, and one end of the wax paper 3 in the length direction is seamlessly connected to the wax paper 1 and the middle section; the sum of the lengths of the wax paper 2, the wax paper 3 and the wax paper 1 is not less than the length of the ceramic sheet.

[0019] In one implementation manner, the alloy melt in step S8 is a single crystal high temperature alloy melt.

[0020] The present invention proposes a double-wall air-cooled blade simulation component preparation system, which can implement the above-mentioned double-wall air-cooled blade simulation component preparation method. The double-wall air-cooled blade simulation component preparation system includes the core, the seed crystal amplifier, the secondary amplifier connected to the seed crystal amplifier, the ceramic sheet, the wax paper one, the wax paper two, the wax paper three and the wax paper four, wherein the middle section of the core is a rectangular flat plate structure, the spoiler column forming hole is opened in the central area of ​​the middle section, and positioning ribs are symmetrically arranged at the two lateral ends of the middle section, and the positioning ribs are used to cooperate and connect with the shell during the process of slurry coating to form the shell.

[0021] In one embodiment, the seed crystal amplifier includes a seed crystal and a transition amplifier wrapped around one end of the seed crystal, the transition amplifier includes a coaxially arranged cone and a cylinder, the large end of the cone is connected to one end of the cylinder, and the other end of the cylinder is connected to the secondary amplifier; the seed crystal is coaxially arranged with the transition amplifier.

[0022] In one embodiment, the secondary amplifier includes a coaxially arranged quadrangular pyramid and a quadrangular prism, the small end of the quadrangular pyramid is coaxially connected to the cylinder, the large end of the quadrangular pyramid is connected to one end of the quadrangular prism, and the other end of the quadrangular prism is connected to wax paper three and wax paper four.

[0023] The present invention proposes a double-walled air-cooled blade simulation component, which is prepared by the above-mentioned double-walled air-cooled blade simulation component preparation method, and the double-walled air-cooled blade simulation component includes an inner wall, an outer wall and a spoiler column, the inner wall and the outer wall are arranged in parallel and spaced apart, the interval between the inner wall and the outer wall is an intermediate cavity, and the inner wall and the outer wall are connected by a plurality of spoiler columns, a plurality of impact holes are opened on the inner wall, which are used to introduce external cold air into the intermediate cavity, and a plurality of air film holes are opened on the outer wall, and any one of the impact holes and any one of the air film holes are staggered.

[0024] Compared with the prior art, the present invention has achieved the following technical effects:

[0025] The method for preparing a double-walled air-cooled blade simulation component proposed in the present invention is simple to operate and can prepare a single-crystal high-temperature alloy double-layer thin-walled spoiler column simulation component with controllable secondary orientation and characteristic structure, wherein the characteristic structure includes but is not limited to the thickness of the inner and outer layers of the simulation component, the spoiler column structure, the spoiler column shape, the spoiler column size, the spoiler column structure arrangement, the volume of the intermediate cavity between the inner and outer walls, etc. In practical applications, by adjusting Figure 1 The assembly method and assembly structure of the casting intermediate shown can produce single crystal high temperature alloy double-layer thin-wall spoiler column castings with different primary orientations, secondary orientations, wall thicknesses and spoiler column sizes to meet various service test requirements. The double-layer air-cooled blade simulation part is prepared by the above-mentioned double-layer wall air-cooled blade simulation part preparation method, which fills the current simulation part technology gap for double-layer wall air-cooled structure turbine blades, and can provide accurate service test data for optimizing the complex cooling structure of turbine blades and improving the service life of turbine blade structures.

[0026] The double-walled air-cooled blade simulation component preparation system proposed in the present invention is used to implement the above-mentioned double-walled air-cooled blade simulation component preparation method, and can prepare a single crystal high-temperature alloy double-layer thin-walled spoiler column simulation component with controllable secondary orientation and characteristic structure.

[0027] The double-walled air-cooled blade simulation part proposed in the present invention is made by the above-mentioned double-walled air-cooled blade simulation part preparation method. The simulation part can reflect the secondary orientation of the double-walled air-cooled structure of the real blade, and the characteristic structure is controllable. It can be used to study the service damage behavior of materials under different mechanical service tests and ensure the test accuracy. It fills the current technical gap in simulation parts for double-walled air-cooled structure turbine blades, and can provide accurate service test data for optimizing the complex cooling structure of turbine blades and improving the service life of turbine blade structures. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0029] Figure 1 It is an overall perspective view of a casting intermediate formed in the preparation method disclosed in an embodiment of the present invention;

[0030] Figure 2 It is a front view of a casting intermediate formed in the preparation method disclosed in an embodiment of the present invention;

[0031] Figure 3 for Figure 2 Side view of

[0032] Figure 4 It is a schematic diagram of the structure of the core disclosed in an embodiment of the present invention.

[0033] In the figure, the reference numerals are: 100, casting intermediate; 1, core; 11, middle section; 111, spoiler column forming hole; 12, positioning rib; 2, seed crystal amplifier; 21, seed crystal; 22, transition amplifier; 3, secondary amplifier; 4, ceramic sheet; 5, wax paper one; 6, wax paper two; 7, wax paper three; 8, wax paper four. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] The purpose of the present invention is to provide a double-wall air-cooled blade simulation part preparation method, a preparation system and a double-wall air-cooled blade simulation part prepared by the preparation method. The simulation part can reflect the secondary orientation of the double-wall air-cooled structure of the real blade, and the characteristic structure is controllable. It can be used to study the service damage behavior of materials under different mechanical service tests and ensure the test accuracy. It fills the current technical gap in simulation parts for double-wall air-cooled structure turbine blades, and can provide accurate service test data for optimizing the complex cooling structure of turbine blades and improving the service life of turbine blade structures.

[0036] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0037] Example 1

[0038] like Figure 1 to Figure 4As shown, this embodiment provides a method for preparing a double-walled air-cooled blade simulation part. The double-walled air-cooled blade simulation part includes an inner wall, an outer wall, air film holes, impact holes and spoiler columns. The inner wall and the outer wall are arranged in parallel and spaced apart. The space between the two is the middle cavity of the simulation part, and the inner wall and the outer wall are connected by a plurality of spoiler columns. A plurality of impact holes are provided on the inner wall for introducing external cold air into between the inner wall and the outer wall. A plurality of air film holes are provided on the outer wall, and generally any impact hole and any air film hole are staggered. The above-mentioned double-walled air-cooled blade simulation part simulates a hollow double-walled air-cooled structure design with turbine blades. This embodiment preferably prepares the simulation part by integral molding. The following takes the process of casting a single crystal high-temperature alloy double-walled air-cooled blade simulation part as an example to specifically explain the method for preparing the above-mentioned double-walled air-cooled blade simulation part. The casting preparation method of a single crystal high-temperature alloy double-walled air-cooled blade simulation part includes the following steps:

[0039] S1. Prepare a core 1 that matches the shape and size of a target casting; the target casting is a single crystal high-temperature alloy double-walled air-cooled blade simulation part to be prepared.

[0040] S2. Cut a seed crystal with the required primary orientation and secondary orientation from the single crystal high temperature alloy sample, and place the seed crystal in a specific wax mold and inject wax to form a seed crystal amplifier 2. Connect the seed crystal amplifier 2 to the secondary amplifier 3 to obtain a combined amplifier; the secondary amplifier 3 is made of wax.

[0041] S3, attach the wax paper 5 to the middle position of the surface of the ceramic sheet 4, the wax paper 5 is located directly below the middle section 11 of the core 1, and the lateral width and thickness of the wax paper 5 are the same as one of the inner and outer walls of the target casting, the length and lateral width of the wax paper 5 are respectively consistent with the length and lateral width of the middle section 11 of the core 1 (that is, the length of the wax paper 5 is consistent with the length of the middle cavity section of the target casting), after the casting is demolded, the location of the middle section 11 is the middle cavity between the inner and outer walls of the simulation. The width of the ceramic sheet 4 should be wider than the overall lateral width of the core 1, and the two ends of the length direction of the ceramic sheet 4 are also long enough to be longer than the two ends of the length direction of the middle section 11.

[0042] S4, connect wax paper 2 6 and wax paper 3 7 to the two ends of the length direction of the wax paper 1 5 along the length direction of the ceramic sheet 4, the thickness of wax paper 2 6 and wax paper 3 7 are the same, and preferably the thickness of wax paper 2 6 and wax paper 3 7 are the sum of the single-layer wall thickness of the target casting (i.e. the thickness of wax paper 1 5) and the height of the middle cavity (the height of the middle cavity is the thickness of the middle section 11 of the core 1). Wax paper 2 6 and wax paper 3 7 have the same transverse width, and are consistent with the casting width size of the target casting, that is, the transverse width of wax paper 2 6 and wax paper 3 7 is the same as the transverse width of the middle section 11, and when placed, the width directions of wax paper 2 6, wax paper 3 7, wax paper 1 5 and the middle section 11 are aligned on both sides. The lengths of wax paper 2 6 and wax paper 3 7 are consistent, and when placed, one end of wax paper 2 6 in the length direction is seamlessly connected to one end of wax paper 1 5 and the middle section 11 in the length direction, and one end of wax paper 3 7 in the length direction is seamlessly connected to the other end of wax paper 1 5 and the middle section 11 in the length direction. The sum of the lengths of wax paper 2 6, wax paper 3 7 and the above-mentioned wax paper 1 5 is not less than the length of the above-mentioned ceramic sheet 4.

[0043] After the above-mentioned wax paper 2 6, wax paper 3 7 and wax paper 1 5 are spliced ​​and combined, a groove with wax paper 1 5 as the bottom is formed between wax paper 2 6 and wax paper 3 7, and the length, width and groove depth (or thickness) of the groove are respectively adapted to the length, width and thickness of the above-mentioned middle section 11 (that is, after the middle section 11 of the core 1 is aligned and placed into the groove, the size of the middle section 11 is completely consistent with the size of the groove), the bottom surfaces of wax paper 2 6, wax paper 3 7 and wax paper 1 5 are flush, and after the middle section 11 of the core 1 is placed on wax paper 1 5, the bottom surface of the middle section 11 is seamlessly fitted with the upper surface of wax paper 1 5, and at the same time, the upper surface of the middle section 11 is flush with the upper surfaces of wax paper 2 6 and wax paper 3 7.

[0044] S5. Fit and cover the wax paper four 8 on the upper surfaces of the above-mentioned middle section 11, wax paper two 6 and wax paper three 7. The length and lateral width of the wax paper four 8 are the same as the target dimensions of the target double-wall spoiler column simulation part, and the thickness of the wax paper four 8 is the same as the thickness of the other of the inner and outer walls of the target casting. After fitting, the length direction of the wax 8 should be aligned on both sides of the length direction of the whole after the above-mentioned wax 6, core 1, wax paper one 5, and wax paper three 7 are combined, so as to obtain a casting molding body that is compatible with the double-wall spoiler column structure of the target casting.

[0045] S6. After the casting body is obtained, the amplifier formed by combining the seed crystal amplifier 2 and the secondary amplifier 3 is combined and connected to the end surfaces of the wax paper 3 7 and the wax paper 4 8. It is best to maintain central symmetry during the connection. After the combination, the following is obtained: Figure 1 to Figure 3The casting intermediate body 100 shown. In the casting intermediate body 100, the longitudinal axis of the wax paper 3 7 and the wax paper 4 8 are parallel to the central axis of the amplifier formed by the seed crystal amplifier 2 and the secondary amplifier 3 (also the axis of the seed crystal 21); in actual situations, the casting body can be regarded as a solid cuboid, and the longitudinal axis of the solid cuboid preferably coincides with the central axis of the amplifier formed by the seed crystal amplifier 2 and the secondary amplifier 3.

[0046] S7, assembling the obtained casting intermediate 100 onto the pouring plate, and then slurry coating the casting intermediate 100 to form a shell, and after dewaxing, obtaining a casting mold with seed crystals and the same shape as the target casting. It should be noted that the "dewaxing" process here adopts a dewaxing process known in the art, and the dewaxing object includes all wax materials such as wax paper 1, 2, 3, 4, transition amplifier 22, and secondary amplifier 3.

[0047] S8. Casting the single crystal high-temperature alloy melt into a casting mold with a seed crystal to obtain a secondary oriented single crystal high-temperature alloy double-layer thin-walled spoiler column casting; finally, opening a plurality of impact holes on the inner wall set on the above casting, and opening a plurality of air film holes on the outer wall to form the final product, i.e., a single crystal high-temperature alloy double-layer wall air-cooled blade simulation part.

[0048] In one embodiment, the core 1 is preferably a ceramic core prepared by 3D printing technology. A plurality of spoiler column forming holes 111 are provided on the middle section 11 of the core 1, and any spoiler column forming hole 111 is preferably arranged perpendicular to the thickness direction of the middle section 11. During casting, the molten metal fills the spoiler column forming hole 111 to form a spoiler column. Figure 4 As shown, the cross-sectional shape, cross-sectional size and arrangement of the spoiler column forming holes 111 on the middle section 11 of the core 1 are the same as the spoiler column structure of the target casting. The core 1 is prepared by 3D printing technology, and the preparation process is simple. In practical applications, cores 1 of various specifications can be prepared according to the different specifications of the target casting. The hole cross-sectional shape, hole cross-sectional size, hole axial length, and distribution form and distribution area of ​​the spoiler column forming holes 111 on the cores 1 of different specifications are different, which can realize the flexible regulation and multi-specification design of the spoiler column structure in the simulation part, thereby also realizing the controllable preparation of the simulation part including but not limited to the wall thickness, spoiler column structure, and the volume of the intermediate cavity.

[0049] In one embodiment, the middle section 11 of the core 1 is preferably rectangular in shape, such as Figure 4As shown, the middle section 11 is a rectangular plate with uniform thickness as a whole, and its length and thickness can be flexibly adjusted according to the test requirements, and its lateral width is consistent with the width of the inner and outer plates of the target casting. Positioning ribs 12 are symmetrically arranged at both lateral ends of the middle section 11 of the core 1. The aforementioned "lateral width" generally refers to the width value of the middle section 11 between the two positioning ribs 12 (that is, the interval between the two positioning ribs 12). When assembling to form the aforementioned casting molding body, the inner sides of the two positioning ribs 12 are fitted with the two sides of the wax paper 2 6 and the wax paper 3 7 in the width direction. The main function of the positioning ribs 12 is to be tightly connected with the mold shell during the process of slurry coating to form the mold shell, so as to ensure that the core 1 and the mold shell are relatively fixed during the casting process, ensure the shape accuracy of the casting in the mold shell, and then ensure the molding accuracy and molding quality of the target casting.

[0050] In one embodiment, the length, width and thickness of the middle section 11 of the core 1 are respectively adapted to the length, width and height of the middle cavity of the target casting, and the size and arrangement of the spoiler column forming holes 111 of the middle section 11 are the same as the column diameter and spoiler column arrangement of the target casting. In a feasible solution: the width of the middle section 11 can be set to 37mm and the thickness to 1mm; the length of the positioning ribs 12 on both sides of the core 1 is set to 54mm, the thickness is set to 5mm, and the width is set to 5mm to 10mm; the material of the 3D printed core 1 is selected from aluminum oxide or silicon oxide-zirconia.

[0051] In one embodiment, the seed crystal amplifier 2 includes a seed crystal 21 and a transition amplifier 22, and the seed crystal 21 is connected to the secondary amplifier 3 via the transition amplifier 22. Specifically, the seed crystal amplifier 2 is formed by opening a wax mold, in which wax material is wrapped around the seed crystal 21 to form the transition amplifier 22; the primary orientation and secondary orientation of the seed crystal 21 can be cut from a single crystal high-temperature alloy substrate according to test needs; generally, the seed crystal 21 is in the shape of a quadrangular prism with a square cross section. As a feasible preferred solution, the side length of the cross section is set to 2mm to 4mm, and the overall axial length of the seed crystal 21 is 18mm to 30mm. Figure 1 to Figure 3 As shown, the transition amplifier 22 is composed of a truncated cone and a cylinder coaxially connected, and the overall axial length of the transition amplifier 22 is 15mm to 20mm, wherein the outer diameter of the cylinder is 15mm, the diameter of the large end of the truncated cone is 15mm, and it is connected to the cylinder, and the diameter of the small end of the truncated cone is 5mm, and one end of the seed crystal 21 is inserted into the truncated cone from the small end of the truncated cone and penetrates into the cylinder, and the seed crystal 21 is coaxial with the entire transition amplifier 22. In a feasible solution, the length of the seed crystal 21 extending into the transition amplifier 22 is preferably 6mm to 10mm.

[0052] In one embodiment, the secondary amplifier 3 is composed of a quadrangular pyramid and a quadrangular prism coaxially combined, such as Figure 1 to Figure 3As shown, the cross-section of the large end of the quadrangular pyramid is a rectangle with a length (the length extending in the direction corresponding to the lateral width of the middle section 11) of 50 mm and a width (the width extending in the direction corresponding to the thickness of the middle section 11) of 10 mm, and the cross-section of the small end of the quadrangular pyramid is a rectangle with a length (the length extending in the direction corresponding to the lateral width of the middle section 11) of 5 mm to 6 mm and a width (the width extending in the direction corresponding to the thickness of the middle section 11) of 5 mm to 6 mm. The small end of the quadrangular pyramid is coaxially connected to the end of the cylinder of the aforementioned transition amplifier 22 that is away from the truncated cone. The overall axial length of the quadrangular pyramid is 20 mm to 40 mm. The large end of the quadrangular pyramid is connected to one end of a quadrangular prism. The shapes and sizes of the two end faces of the quadrangular prism are exactly the same as those of the large end of the quadrangular pyramid. The axial length of the quadrangular prism is generally greater than 5 mm. The other end of the quadrangular prism is connected to wax paper three 7 and wax paper four 8, and the cast body is coaxial with the quadrangular prism.

[0053] In one embodiment, the thickness of wax paper 1 5 and wax paper 4 8 is adjusted according to the thickness of the inner and outer walls of the target casting, generally 0.5mm to 2mm, and the thickness of the inner and outer walls of the target casting is generally the same, and the inner and outer walls are preferably rectangular. The thickness of wax paper 2 6 and wax paper 3 7 is the sum of the single-layer wall thickness of the target casting and the height of the middle cavity, and the thickness of wax paper 2 6 and wax paper 3 7 is generally set to 1.5mm to 3mm; the lateral width of wax paper 1 5, wax paper 2 6, wax paper 3 7 and wax paper 4 8 is consistent with the lateral width of the middle section 11 of the core 1, preferably 37mm.

[0054] In one embodiment, the Al2O3 content of the ceramic sheet 4 is greater than 99%, and the thickness is preferably 0.3mm to 1mm; the lateral width of the ceramic sheet 4 is larger than the width of the middle section 11 (i.e., the lateral width of wax paper 1 5, wax paper 2 6 and wax paper 3 7), and is generally similar to the overall lateral width of the core 1 (i.e., the sum of the lateral widths of the middle section 11 and the two positioning ribs 12) or 1mm to 5mm larger than the overall lateral width of the core 1.

[0055] In practical applications, there are no special requirements for the fixing methods of wax paper 1 5, wax paper 2 6, wax paper 3 7 and wax paper 4 8, and a fixing method well known in the art can be used, such as pasting; there are no special requirements for the assembly method of the casting intermediate 100, and an assembly method well known in the art can be used; there are no special requirements for the process of slurry dipping and shell coating, and a process well known in the art can be used. During the slurry dipping and shell coating process, a shell is formed around the casting molding body. In a feasible embodiment, the thickness of the shell is preferably 10 mm to 20 mm.

[0056] It can be seen that the above-mentioned double-wall air-cooled blade simulation preparation method is easy to operate and can prepare a single crystal high-temperature alloy double-layer thin-wall spoiler column simulation with controllable secondary orientation and characteristic structure, wherein the characteristic structure includes but is not limited to the inner and outer wall thickness of the simulation, spoiler column structure, spoiler column shape, spoiler column size, spoiler column structure arrangement, and the volume of the intermediate cavity between the inner and outer walls. In practical applications, by adjusting Figure 1 The assembly method and assembly structure of the casting intermediate 100 shown can produce single crystal high-temperature alloy double-layer thin-walled spoiler column castings with different primary orientations, secondary orientations, wall thicknesses and spoiler column sizes to meet various service test requirements.

[0057] Example 2

[0058] like Figure 1 to Figure 4 As shown, this embodiment proposes a double-wall air-cooled blade simulation preparation system, which is mainly used to implement the double-wall air-cooled blade simulation preparation method in Example 1 and prepare the expected double-wall air-cooled blade simulation. The double-wall air-cooled blade simulation preparation system mainly includes a core 1 matching the shape and specifications of the target casting, a seed crystal amplifier 2, a secondary amplifier 3 connected to the seed crystal amplifier 2, a ceramic sheet 4, wax paper 1 5, wax paper 2 6, wax paper 3 7 and wax paper 4 8, and also includes some conventional casting equipment.

[0059] In this embodiment, the specific structures and dimensional designs of the core 1, seed crystal amplifier 2, secondary amplifier 3, ceramic sheet 4, wax paper 1 5, wax paper 2 6, wax paper 3 7 and wax paper 4 8, as well as the combination of the components are all referred to in Example 1 and will not be repeated here.

[0060] Example 3

[0061] This embodiment proposes a double-walled air-cooled blade simulation part, which is prepared by the preparation method of the double-walled air-cooled blade simulation part in Embodiment 1. The double-walled air-cooled blade simulation part adopts a double-walled structure arrangement of inner and outer layers. After the cooling airflow enters the middle cavity between the inner and outer walls from the impact hole of the inner wall, it first hits the inner wall surface of the outer wall to form jet impact cooling, and then the cooling airflow bypasses the spoiler column and flows out from the air film holes distributed on the outer wall, and forms a thin air film on the outer surface of the outer wall; this air-cooling flow mode is combined with external gas impact to realize the simulation test of the double-walled air-cooled structure under the approximate service conditions, and meet the service test requirements of the double-walled air-cooled structure simulation part of the turbine blade under the close to actual working conditions.

[0062] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. A method for preparing a double-walled air-cooled blade simulation component, characterized in that: The method is used for integrally casting a double-wall air-cooled blade simulation part, comprising the steps of: S1, preparing a core that matches the shape and size of the target casting, wherein a middle section of the core is provided with a plurality of spoiler column forming holes for forming spoiler columns; S2, cutting a seed crystal with a desired primary orientation and a desired secondary orientation from a single crystal high-temperature alloy sample, injecting wax around the periphery of the seed crystal to form a seed crystal amplifier, and connecting the seed crystal amplifier to a secondary amplifier to obtain a combined amplifier; S3, attaching wax paper 1 to the surface of the ceramic sheet, wherein the lateral width and thickness of the wax paper 1 are the same as one of the inner and outer walls of the target casting, the middle section is arranged directly above the wax paper 1, and the length and lateral width of the wax paper 1 are respectively the same as the length and lateral width of the middle section; S4, connecting wax paper 2 and wax paper 3 to the two ends of the length direction of wax paper 1 along the length direction of the ceramic sheet, respectively, the thickness of wax paper 2 and wax paper 3 are the same, and the thickness of wax paper 2 and wax paper 3 are both the sum of the thickness of wax paper 1 and the thickness of the middle section, and the lateral width of wax paper 2 and wax paper 3 is the same as the lateral width of the middle section; S5, laminating and covering the surfaces of the middle section, the wax paper two and the wax paper three with wax paper four, to obtain a casting body adapted to the double-wall spoiler column structure of the target casting, wherein the thickness of the wax paper four is the same as the thickness of the other of the inner and outer walls of the target casting; S6, combining and connecting the combined amplifier obtained in step S2 with the end surfaces of the wax paper 3 and the wax paper 4 to obtain a casting intermediate; S7, assembling the casting intermediate onto a pouring plate, then slurry coating the casting intermediate to form a shell, and after dewaxing, obtaining a casting mold with seed crystals that matches the shape and size of the target casting; S8. Casting the alloy melt into the casting mold to obtain a secondary oriented alloy double-layer thin-walled spoiler column casting, and then opening a plurality of impact holes on the inner wall of the secondary oriented alloy double-layer thin-walled spoiler column casting, and opening a plurality of air film holes on the outer wall of the secondary oriented alloy double-layer thin-walled spoiler column casting to form the double-layer wall air-cooled blade simulation part.

2. The method for preparing a double-walled air-cooled blade simulation component according to claim 1, characterized in that: The core is a ceramic core prepared by 3D printing technology.

3. The method for preparing a double-walled air-cooled blade simulation according to claim 1 or 2, characterized in that: The middle section of the core is a rectangular flat plate structure, and the spoiler column forming hole is opened in the central area of ​​the middle section.

4. The method for preparing a double-walled air-cooled blade simulation component according to claim 3, characterized in that: Positioning ribs are symmetrically arranged at both transverse ends of the middle section, and the positioning ribs are used to cooperate and connect with the mold shell during the process of forming the mold shell in step S7.

5. The method for preparing a double-walled air-cooled blade simulation component according to claim 1 or 2, characterized in that: In step S4, the two sides of the width direction of the wax paper 2, the wax paper 3, the wax paper 1 and the middle section are aligned; the wax paper 2 and the wax paper 3 have the same length, and when placed, one end of the wax paper 2 in the length direction is seamlessly connected to the wax paper 1 and the middle section, and one end of the wax paper 3 in the length direction is seamlessly connected to the wax paper 1 and the middle section; the sum of the lengths of the wax paper 2, the wax paper 3 and the wax paper 1 is not less than the length of the ceramic sheet.

6. The method for preparing a double-walled air-cooled blade simulation component according to claim 1 or 2, characterized in that: The alloy melt in step S8 is a single crystal high temperature alloy melt.

7. A double-walled air-cooled blade simulation preparation system, characterized in that: The method for preparing a double-walled air-cooled blade simulation component according to claim 1 can be implemented, and the double-walled air-cooled blade simulation component preparation system includes the core, the seed crystal amplifier, the secondary amplifier connected to the seed crystal amplifier, the ceramic sheet, the wax paper one, the wax paper two, the wax paper three and the wax paper four, wherein the middle section of the core is a rectangular flat plate structure, the spoiler column forming hole is opened in the central area of ​​the middle section, and positioning ribs are symmetrically arranged at both lateral ends of the middle section, and the positioning ribs are used to cooperate and connect with the shell during the process of forming the shell by slurry coating.

8. The double-walled air-cooled blade simulation preparation system according to claim 7, characterized in that: The seed crystal amplifier includes a seed crystal and a transition amplifier wrapped around one end of the seed crystal, the transition amplifier includes a coaxially arranged frustum and a cylinder, the large end of the frustum is connected to one end of the cylinder, and the other end of the cylinder is connected to the secondary amplifier; the seed crystal and the transition amplifier are coaxially arranged.

9. The double-walled air-cooled blade simulation preparation system according to claim 8, characterized in that: The secondary amplifier includes a coaxially arranged quadrangular pyramid and a quadrangular prism, the small end of the quadrangular pyramid is coaxially connected to the cylinder, the large end of the quadrangular pyramid is connected to one end of the quadrangular prism, and the other end of the quadrangular prism is connected to wax paper three and wax paper four.

10. A double-walled air-cooled blade simulation, characterized in that: The double-walled air-cooled blade simulation component is prepared by the preparation method of any one of claims 1 to 6, wherein the double-walled air-cooled blade simulation component comprises an inner wall, an outer wall and spoiler columns, wherein the inner wall and the outer wall are arranged in parallel and spaced apart, the space between the inner wall and the outer wall is an intermediate cavity, and the inner wall and the outer wall are connected by a plurality of spoiler columns, a plurality of impact holes are provided on the inner wall for introducing external cold air into the intermediate cavity, a plurality of air film holes are provided on the outer wall, and any one of the impact holes and any one of the air film holes are staggered.

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