Calibration test assembly, device and method

Abstract

The application provides a calibration test assembly. In the docking test piece of the calibration test assembly, two fan-shaped segments are used to simulate one of the docking cassettes. The fan segment of each fan-shaped segment simulates a fan-shaped part of the barrel of the corresponding cassette. The docking flange is arranged at the docking end of the fan segment and is provided with a plurality of docking holes, which are uniformly distributed with the bolt holes of the corresponding mounting edge. The external flange is arranged at the connecting end of the fan segment and is provided with a plurality of external holes. The docking test piece has a symmetry plane, each fan-shaped segment is connected to a loading tool or a fixing tool through external bolts passing through the external holes, and the two fan-shaped segments are docked with each other through docking bolts passing through the respective docking holes. The span of the circumferentially distributed external bolts is larger than that of the docking bolts. The application also provides a calibration test device and method using the above calibration test assembly. The calibration test assembly is used for the high-temperature calibration test of the axial force of the cassette, and the calibration test can be efficiently and low-costly performed.

Description

TECHNICAL FIELD

[0001] The present application relates to a calibration test assembly, and relates to a calibration test device and a calibration test method for high-temperature calibration test of casing axial force. BACKGROUND

[0002] In order to ensure the safety of the aero-engine test, the axial force borne by the installation edge of the casing needs to be measured to avoid the failure of the bolts of the installation edge. The simple and feasible measurement scheme for measuring the casing axial force currently includes using a clamping measurement device or a lever measurement device to measure the casing axial force, and the measurement device needs to be calibrated before being measured by using the above measurement device.

[0003] Generally, the calibration test of the measurement device needs to be performed on a complete casing. However, there are many problems in performing the calibration test on the complete casing. First, the size of the actual aero-engine complete casing is large, with a diameter of 600-700 mm, and the production and manufacturing cycle is long. Second, the structure of the complete casing is complex, and the processing cost is high. Third, in order to simulate the working environment of the complete casing, the complete casing needs to be heated during the calibration test, and the corresponding high-temperature environment box is large in size and high in heating equipment cost.

[0004] Therefore, it is necessary to provide a calibration test assembly, which can efficiently and at low cost perform the high-temperature calibration test of the casing axial force. SUMMARY

[0005] The purpose of the present application is to provide a calibration test assembly for high-temperature calibration test of casing axial force, which can efficiently and at low cost perform the calibration test.

[0006] The present application provides a calibration test assembly for high-temperature calibration test of casing axial force. The calibration test assembly includes a docking test piece, and the docking test piece includes two fan-shaped segments, a plurality of external connection bolts, and a plurality of docking bolts. Each of the two fan-shaped segments is used for simulating one of the casings to be docked, and each fan-shaped segment includes a fan segment, a fan-shaped docking flange, and a fan-shaped external connection flange. The fan segment extends along the axial direction and has a docking end and a connecting end, and simulates a part of the barrel of the corresponding casing in a fan shape. The docking flange is arranged at the docking end of the fan segment, the docking flange is distributed with a plurality of docking holes in the circumferential direction, and the plurality of docking holes are consistent with the distribution of the bolt holes of the corresponding installation edge of the corresponding casing. The external connection flange is arranged at the connecting end of the fan segment, and the external connection flange is distributed with a plurality of external connection holes in the circumferential direction. The docking test piece has a symmetry plane parallel to the axial direction, each fan-shaped segment is connected to a loading tool or a fixing tool by the plurality of external connection bolts passing through the external connection holes of the external connection flange, the two fan-shaped segments are docked with each other by the plurality of docking bolts passing through the docking holes of the respective docking flanges, and the span of the external connection bolts distributed in the circumferential direction is greater than the span of the docking bolts distributed in the circumferential direction.

[0007] In one embodiment, the docking test piece is a first docking test piece. The calibration test assembly further comprises a second docking test piece, which is symmetrically arranged with the first docking test piece relative to a second plane, and the second plane is perpendicular to the symmetry plane.

[0008] In one embodiment, the outer connection hole of the outer connection flange is axially aligned with the docking hole of the docking flange.

[0009] In one embodiment, the number of outer connection bolts of the outer connection flange is two more than the number of docking bolts of the docking flange.

[0010] In one embodiment, the number of docking bolts is at least six. And the number of outer connection bolts is at least eight.

[0011] In one embodiment, the number of outer connection holes of the outer connection flange is consistent with the number of outer connection bolts.

[0012] In one embodiment, the fan-shaped segment is provided with a reinforcing rib at the axial middle position of the fan-shaped segment.

[0013] In one embodiment, the axial length of the fan-shaped segment is more than 1.5 times the height of the docking flange.

[0014] The present application also provides a calibration test device for high-temperature calibration test of engine case axial force. The calibration test device comprises the calibration test assembly, a fixing tool and a loading tool. The fixing tool is connected to the outer connection flange of one of the two fan-shaped segments of the calibration test assembly. The loading tool is connected to the outer connection flange of the other of the two fan-shaped segments of the calibration test assembly, thereby loading the calibration test assembly with simulated axial force.

[0015] The present application also provides a calibration test method for high-temperature calibration test of engine case axial force, which uses the calibration test device. The calibration test method comprises: S1, installing an engine case axial force measuring device to the calibration test assembly of the calibration test device; S2, placing the calibration test assembly with the installed engine case axial force measuring device into an environmental box, setting a certain gradient of temperature, and then gradually loading simulated axial force through the loading tool of the calibration test device to obtain a relationship curve between the strain output of the engine case axial force measuring device and the simulated axial force under different temperatures; S3, repeating step S2 several times, and then obtaining the final relationship curve between the strain output of the engine case axial force measuring device and the engine case axial force under different temperatures after averaging.

[0016] When the calibration test assembly, the calibration test device and the calibration test method are used, the fan-shaped segment is used to simulate the complete casing, the bolt holes of the butt joint hole of the butt flange and the butt joint installation edge of the butt joint casing are consistent, the calibration test assembly including the fan-shaped segment, the external bolt and the butt bolt is symmetrically arranged as a whole, the circumferential distribution span of the external bolt of the external flange is larger than the circumferential distribution span of the butt bolt at the butt flange, the influence of the loading end and the fixed end boundary on the calibration test can be reduced, and thus the complete casing test piece can be replaced, the casing axial force high-temperature calibration test can be efficiently and low-costly carried out. BRIEF DESCRIPTION OF DRAWINGS

[0017] The above and other features, properties and advantages of the present application will become more apparent by the following description with reference to the accompanying drawings and examples, in which:

[0018] Figure 1 is a perspective view of the calibration test device.

[0019] Figure 2 is a plan view of the calibration test device.

[0020] Figure 3 is a side view of the calibration test device when viewed from the right side of Figure 2 .

[0021] Figure 4 is a side view of the calibration test device when viewed from the left side of Figure 2 .

[0022] Figure 5 is a sectional view of the calibration test device.

[0023] Figure 6 is a sectional view of the butt joint casing.

[0024] Figure 7 is an enlarged view of the butt flange.

[0025] Figure 8 is a schematic view of the calibration test device on which a measuring device is installed.

[0026] Figure 9 is a deformation cloud chart when only the butt flange of the pair of fan-shaped segments bears the axial force.

[0027] Figure 10A and Figure 10B are vertical direction displacement cloud charts when the middle part of the fan-shaped segment bears the axial force without and with the reinforcing rib, respectively.

[0028] Figure 11A , Figure 11B and Figure 11CThe graphs are respectively the distance of flange root being pulled apart under the same proportional axial force of the calibration test assembly and the complete casing test piece at 700℃, 20℃ and 500℃. DETAILED DESCRIPTION

[0029] The application will be further described with reference to the specific embodiments and drawings, and more details are set forth in the following description in order to fully understand the application, but the application can be implemented in many other ways different from the description, and the person skilled in the art can make similar generalization and deduction according to the actual application without departing from the spirit of the application, therefore the protection scope of the application should not be limited by the specific embodiments.

[0030] For example, the first feature is formed above or on the second feature in the description, which can include the embodiment that the first feature and the second feature are directly connected, and can also include the embodiment that an additional feature is formed between the first feature and the second feature, so that the first feature and the second feature can not be directly connected. Further, when the first element is described in connection with or in combination with the second element, the description includes the embodiment that the first element and the second element are directly connected or combined with each other, and also includes the embodiment that one or more other intervening elements are added to indirectly connect or combine the first element and the second element.

[0031] Figure 6 The cross-sectional configuration of the docking casing 20 is exemplarily shown. Figure 6 In the drawings, the combustion chamber casing 20a and the high-pressure turbine casing 20b are taken as examples of the docking casing 20. The mounting edge 30a of the combustion chamber casing 20a and the mounting edge 30b of the high-pressure turbine casing 20b can be taken as examples of the docking mounting edges 30 of the docking casing 20. The docking casing 20 each has a barrel 40, and the docking mounting edges 30 are flange structures at the connection of the barrels 40 of the docking casing 20, i.e. connection flange structures. The docking mounting edges 30 each have bolt holes 50 for the connection bolts 80 to pass through, and cooperate with the nuts 801 to connect the docking mounting edges 30 together. The bolt holes 50 are usually uniformly distributed along the circumference of the corresponding mounting edge 30.

[0032] The casing axial force refers to the force along the axial direction of the engine borne by the casing 20 caused by the gas load when the aero-engine is working, also known as the gas axial force. As mentioned above, in order to ensure the safety of the aero-engine test, the axial force borne by the casing mounting edge 30 needs to be measured, and the measurement device needs to be calibrated before measurement.

[0033] Directly using a complete casing test piece to carry out a casing axial force high-temperature calibration test has problems of long casing production and manufacturing cycle, high processing cost, and high heating equipment cost. To solve the above technical problems, it is necessary to provide a high-efficiency and low-cost casing axial force high-temperature calibration test scheme.

[0034] The calibration test device 10 provided by the present application is used for casing axial force high-temperature calibration test. In particular, the calibration test device 10 comprises the calibration test assembly 1 provided by the present application.

[0035] Figure 1 The three-dimensional structure of the calibration test device 10 is exemplarily shown. Figure 2 、 Figure 3 and Figure 4 The three views of the calibration test device 10 are exemplarily shown respectively. Figure 5 The cross-sectional structure of the calibration test device 10 taken along the line B-B of Figure 4 It should be understood that all the drawings are only exemplary and are not drawn according to the condition of the same scale, and should not be taken as a limitation on the actual protection scope required by the present application.

[0036] The calibration test assembly 1 is used for casing axial force high-temperature calibration test. The calibration test assembly 1 comprises a butt joint test piece T1.

[0037] The butt joint test piece T1 comprises two fan-shaped segments 2, a plurality of external connection bolts 81 and a plurality of butt joint bolts 82. The two fan-shaped segments 2 are respectively used to simulate one casing of a butt joint casing 20. That is, in the illustrated embodiment, one fan-shaped segment 2a (left fan-shaped segment 2a in the figure) of the two fan-shaped segments 2 can be used to simulate a combustion chamber casing 20a, and the other fan-shaped segment 2b (right fan-shaped segment 2b in the figure) of the two fan-shaped segments 2 can be used to simulate a high-pressure turbine casing 20b. Figure 4 Figure 4

[0038] It can be understood that when not distinguished, the fan-shaped segments 2a and 2b can be collectively referred to as the fan-shaped segments 2. In addition, in some drawings, the corresponding features of the fan-shaped segments 2a and 2b are distinguished by the same number respectively suffixed by a and b, and in some drawings, the corresponding features of the fan-shaped segments 2a and 2b are directly identified by the same number.

[0039] Figure 1 In the figure, the fan-shaped segment 2a is taken as an example, each fan-shaped segment 2 comprises a fan segment 21, a butt joint flange 22 and an external connection flange 23.

[0040] ​​The sector 21 extends along the axial direction X0 and has a butt end 212 and a connecting end 211. The sector 21 simulates a sector-shaped portion of the barrel 40 of the corresponding casing 20. That is, the sector 21 can be considered to be substantially the same as a sector-shaped portion of the barrel 40 of the corresponding casing 20 to be simulated, which is cut along the axial direction X0 and then cut along the circumferential direction CO, at least the radius of the sector 21 is consistent with the radius of the barrel 40 of the corresponding casing 20 to be simulated. Preferably, the wall thickness of the sector 21 near the butt end 212 is also consistent with the wall thickness of the barrel 40 of the corresponding casing 20 to be simulated at the corresponding position.

[0041] The butt flange 22 is arranged at the butt end 212 of the sector 21. The butt flange 22 is distributed with a plurality of butt holes 322 along the circumferential direction CO. Moreover, the plurality of butt holes 322 is consistent with the distribution of the bolt holes 50 of the corresponding mounting edge 30 of the corresponding casing 20. That is, the size and the distribution interval between each other of the butt holes 322 are consistent with the bolt holes 50 of the corresponding mounting edge 30 of the corresponding casing 20.

[0042] The external flange 21 is arranged at the connecting end 211 of the sector 21, and the external flange 21 is distributed with a plurality of external holes 31 along the circumferential direction CO.

[0043] The butt test piece T1 has a symmetry plane PL parallel to the axial direction X0 (shown in Figure 4 That is, the symmetry plane PL is a plane passing through the central axis of the sector 21 (or, when supplemented, the cylinder) and dividing the sector 21 into two equal parts.

[0044] Each sector 2 is connected to the loading tool 41 or the fixing tool 42 (shown in Figure 8 The two sectors 2 are butted to each other by the plurality of butt bolts 82 passing through the butt holes 32 of the respective butt flanges 22.

[0045] The span of the external bolts 81 distributed along the circumferential direction CO is greater than the span of the butt bolts 82 distributed along the circumferential direction CO. That is, the circumferential distance between the two external bolts 81 located at the outermost along the circumferential direction CO is greater than the circumferential distance between the two butt bolts 82 located at the outermost along the circumferential direction CO, or the corresponding central angle of the two external bolts 81 at the outermost is greater than the corresponding central angle of the two butt bolts 82 at the outermost.

[0046] When the calibration test assembly 1 is used, the complete casing 20 can be simulated by the fan-shaped segments 2, which can significantly reduce the volume of the calibration test assembly, shorten the production cycle and reduce the material cost. Moreover, the connecting end 211 of the fan-shaped segment 2a can be used as the loading end of the fan-shaped segment, and the connecting end 211 of the fan-shaped segment 2b can be used as the loading end of the fan-shaped segment, so that the circumferential distribution span of the external bolt 81 of the loading end is larger than the circumferential distribution span of the abutting bolt 82, the influence of the boundary between the loading end and the fixed end on the calibration test can be reduced, and thus the calibration test can be accurately performed instead of the complete casing.

[0047] As mentioned above, the present application also provides a calibration test device 10, which can be used for high-temperature calibration test of the casing axial force. The calibration test device 10 can include the calibration test assembly 1. The calibration test device 10 can also include a fixing tool 42 and a loading tool 41. The fixing tool 42 can be connected to the external flange 21 of one of the two fan-shaped segments 2b of the calibration test assembly. The loading tool 41 can be connected to the external flange 21 of the other of the two fan-shaped segments 2a of the calibration test assembly, thereby loading the calibration test assembly 1 with simulated axial force. For example, the loading tool 41 can have a transfer hole 42 Figure 3 connected to the driving shaft (for example, the output shaft of the linear motor) of the driving device, so that the loading tool 41 can load the calibration test assembly 1 with simulated axial force.

[0048] In the illustrated embodiment, the abutment test piece T1 can be a first abutment test piece T1. The calibration test assembly 1 can also include a second abutment test piece T2. The second abutment test piece T2 can be symmetrically arranged with the first abutment test piece T1 relative to the first plane P1 Figure 5 illustrated in the figure). The first plane P1 can be perpendicular to the symmetry plane PL. See Figure 1 and Figure 5 The fan-shaped segments corresponding to the fan-shaped segments 2a, 2b in the abutment test piece T2 are respectively denoted as 2a', 2b', and the specific arrangement will not be described again. The distance between the first abutment test piece T1 and the second abutment test piece T2 can be small under the condition that they do not touch each other, and in particular, the maximum distance of the fan-shaped segments 2 belonging to the first abutment test piece T1 and the second abutment test piece T2 in the direction perpendicular to the first plane P1 is less than the outer diameter of the complete casing.

[0049] It can be understood that the words "first", "second" and the like used in the text are only used to facilitate the differentiation of the corresponding features, and have no special meaning unless otherwise stated, and therefore cannot be understood as limiting the scope of protection of the present application.

[0050] Figure 9 The deformation cloud diagram of the abutment flange 22 when subjected to axial force is shown when only the first abutment test piece T1. AsFigure 9 As shown, when only one pair of the sector segments bears the axial force load, the sector segments will produce greater bending deformation. When there is only one pair of the sector segments, it is difficult to determine the center of the axial force load, and slight deviation during loading will produce additional bending moment, which causes the sector segments to bend and deform. In order to reduce the bending deformation of the pair of sector segments, a two-pair sector segment vertically symmetrical design is used, which can greatly reduce the additional bending moment generated by the axial force load and improve the axial force calibration accuracy.

[0051] It can be understood that specific words are used in the description of the embodiments of the present application, such as "one embodiment", "another embodiment", and / or "some embodiments", which means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that the "one embodiment" or "another embodiment" mentioned in different places in the specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present application can be properly combined.

[0052] In the illustrated embodiment, the plurality of external holes 31 can be aligned with the plurality of abutting holes 32 in the axial direction X0. That is, the distribution spacing, number and distribution position of the external holes 31 and the abutting holes 32 in the circumferential direction C0are consistent with each other, as shown in Figure 4 In other words, at this time, the number of external bolts 81 is greater than the number of abutting bolts 82, thereby making the span of the external bolts 81 distributed along the circumferential direction C0greater than the span of the abutting bolts 82 distributed along the circumferential direction C0. Further, the size of the external holes 31 and the abutting holes 32 can also be the same. That is, the size, position and spacing of the external bolt holes (i.e., external holes 31) of the loading end flange (i.e., external flange 21a) of the sector segment 2a of the simulated combustion chamber casing 20a and the fixing end flange (i.e., external flange 21b) of the sector segment 2b of the simulated high-pressure turbine casing 20b are consistent with the abutting bolt holes (i.e., abutting holes 32) between the two sector segments 2a, 2b. In this way, the machining difficulty and structural complexity of the bolt holes of the loading end flange and the fixing end flange of the sector segment can be reduced.

[0053] In the illustrated embodiment, the number of external bolts 81 of the external flange 21 can be two more than the number of abutting bolts 82 of the abutting flange 22. That is, Figure 1 and Figure 4 In the above, one more on each side of the circumferential direction C0than the abutting bolts 82. In this way, the circumferential central angle can be reduced as much as possible, and the production cycle and machining cost can be reduced.

[0054] The number of the butt bolts 82 can be at least six. In the illustrated embodiment, further, the butt bolts 82 are exactly six. It is analyzed that the clamping measuring device or the lever measuring device needs to occupy the space of at least four (four) bolts, and the circumferential direction of the sector segment at least contains six butt bolts, which can reduce the influence of the two side boundaries of the sector segment on the calibration test of the measuring device. That is, the outer flange of the simulation combustion chamber case sector segment and the simulation high-pressure turbine case sector segment is connected by using six bolts.

[0055] The number of the butt bolts 82 can be at least six. In the illustrated embodiment, further, the butt bolts 82 are exactly six. It is analyzed that the clamping measuring device or the lever measuring device needs to occupy the space of at least four (four) bolts, and the circumferential direction of the sector segment at least contains six butt bolts, which can reduce the influence of the two side boundaries of the sector segment on the calibration test of the measuring device. That is, the outer flange of the simulation combustion chamber case sector segment and the simulation high-pressure turbine case sector segment is connected by using six bolts.

[0056] The above setting can make the circumferential central angle of the sector segment as small as possible under the premise of ensuring the calibration accuracy of the case axial force, so as to reduce the production cycle and processing cost.

[0057] In the illustrated embodiment, the number of the outer connection holes 31 of the outer connection flange 21 can be consistent with the number of the outer connection bolts 81. That is, the outer connection bolts 81 are all connected through the outer connection holes 31 of the outer connection flange 21, without any idle.

[0058] In the illustrated embodiment, the number of the butt connection holes 32 of the butt connection flange 22 can be more than the number of the butt bolts 82. That is, among the plurality of butt connection holes 32, there are some idle butt connection holes 32 which are not connected with the butt bolts 82. Figure 1 In the illustrated embodiment, compared with the butt bolts 82, there are one more butt connection holes 32 on both sides of the circumferential direction CO, that is, there are two idle butt connection holes 32 located at the outermost position on both sides of the circumferential direction CO.

[0059] In the illustrated embodiment, the sector segment 2 can be provided with a reinforcing rib 4 at the middle position of the sector segment 21 along the axial direction X0. That is, the reinforcing rib 4 is located between the outer connection flange 21 and the butt connection flange 22 along the axial direction X0.

[0060] Figure 10A And Figure 10B The vertical direction displacement cloud diagrams of the sector segment 2 with and without the reinforcing rib 4 under the axial force are respectively shown. As shown in FIGS. 8 and 9, if the sector segment 2 has no reinforcing rib 4 in the middle part, the two side boundaries will be obviously deformed and shrink inward after the axial force is loaded. The setting of the reinforcing rib 4 with a certain thickness in the middle part of the sector segment 2 can reduce the influence of the deformation on the calibration accuracy. Combined with FIGS. 10 and 11, it can be seen that the reinforcing rib 4 can effectively reduce the deformation of the sector segment 2 under the axial force, and the axial force calibration accuracy of the sector segment 2 is improved. Figure 10A ​Figure 10A and Figure 10B It can be seen that the inward shrinkage deformation of the sector-shaped flange section with reinforcing ribs is reduced by about half compared to the section without reinforcing ribs. For example, based on the structural characteristics of the complete combustion chamber casing and the high-pressure turbine casing, Figure 5 In the simulation combustion chamber casing 20a, the reinforcing rib 4a of the sector segment 2a is provided on the inner side (or concave side) of the sector segment 21a, while the reinforcing rib 4b of the sector segment 2b of the simulation high pressure turbine casing 20b can be provided on both the inner and outer sides (or convex sides) of the sector segment 21b.

[0061] Combination Figure 5 and Figure 7 The axial length L0 of sector 21 can be more than 1.5 times the height H0 of mating flange 22. This ensures more accurate calibration test results.

[0062] The central angle α0 of sector segment 2 can be a predetermined number ( Figure 3 In the middle, the central angle α1 corresponding to the 8 external holes 31 is expanded by 5° on both sides of the circumferential C0, that is, α2 = 5°. For example, α0 is kept at 40-45°.

[0063] When designing the sector segment of the aforementioned calibration test component 1, it is possible to achieve a small circumferential central angle and a short axial length while ensuring the calibration accuracy of the axial force of the casing. The thickness of the sector segment can be kept consistent with that of the complete casing, thereby reducing the production cycle and processing costs. The aforementioned calibration test component and device can also be referred to as a high-temperature calibration test component and device for the axial force of the sector segment casing.

[0064] Considering that current methods for measuring the axial force of the casing using clamping or lever measuring devices all rely on measuring the distance the casing's mating flange root is pulled apart under axial force, when designing the sector segment 2 of calibration test assembly 1, it is sufficient to ensure that the mating flanges 22 between sector segments 2 are consistent with the complete casing. For example... Figure 6 As shown, based on the flange structure design at the junction of the combustion chamber casing 20a and the high-pressure turbine casing 20b, the flange 22 at the junction of the simulated sector segment 2a of the combustion chamber casing 20a and the simulated sector segment 2b of the high-pressure turbine casing 20b is designed. The final setting of the flange 22 at the junction of the sector segment 2b is as follows. Figure 7 As shown, at the same time, the positional distribution of the connecting bolts 82 of the flange 22 at the joint of the sector segment is consistent with the positional distribution of the connecting bolts 80 of the complete casing. Therefore, the above-mentioned calibration test assembly 1 can be called the sector segment flange high-temperature calibration test assembly.

[0065] As an example, when designing the calibration test assembly, first, the sector flange structure and bolt position distribution can be designed according to the complete casing abutting installation edge structure and bolt position distribution. Then, the minimum number of abutting bolts is determined according to the space required by the measuring device, and the same number of bolts is added on both sides during actual design to reduce the influence of the boundaries of the two sides of the sector. Then, the outer bolt position distribution of the loading end and the fixed end of the sector is made consistent with the abutting bolt position distribution. Then, the number of outer bolts of the loading end and the fixed end of the sector is set to be more than the number of abutting bolts. Then, two pairs of sectors are designed to be vertically symmetrically distributed. Then, a certain thickness of reinforcing ribs are arranged in the middle of the sector, for example, according to the structural characteristics of the complete casing. At this point, the design of the calibration test assembly is completed.

[0066] The present application also provides a calibration test method for the axial force high-temperature calibration test of a casing, that is, a calibration test method for the axial force high-temperature calibration test of a casing. The calibration test method uses the calibration test device 10 described above. The calibration test method comprises the following steps S1, S2 and S3.

[0067] Step S1, install the casing axial force measuring device to the calibration test assembly 1 of the calibration test device 10.

[0068] Figure 8 The clamping measuring device 60a and the lever measuring device 60b are shown as examples of the casing axial force measuring device. When actually performing step S1, reference can be made to Figure 8 Install the casing axial force measuring device 60a and / or 60b to the calibration test assembly 1.

[0069] Step S2, place the calibration test assembly with the installed casing axial force measuring device into the environmental box, set the temperature according to a certain gradient, and then gradually load the simulated axial force through the loading tool of the calibration test device to obtain the relationship curve between the strain output of the casing axial force measuring device and the simulated axial force at different temperatures.

[0070] When actually performing step S2, the calibration test assembly 1 with the installed casing axial force measuring device 60a, 60b can be placed into the environmental box, for example, the temperature is set to room temperature (for example, 20°), 100℃, 200℃, …, 600℃, 700℃, and then the axial force is gradually and slowly loaded to obtain the relationship curve between the strain output of the casing axial force measuring device 60a, 60b and the simulated axial force at different temperatures.

[0071] Step S3, repeat step S2 several times, and then obtain the final relationship curve between the strain output of the casing axial force measuring device and the simulated axial force at different temperatures after multiple averaging.

[0072] In the actual execution of step S3, step S2 can be repeated approximately 3-5 times. After averaging the results, the relationship curves between the strain output and simulated axial force of the casing axial force measuring devices 60a and 60b at different temperatures are obtained. This completes the calibration test method, that is, the calibration test of the casing axial force measuring device.

[0073] Analysis shows that since the axial force measuring devices for the casing, such as the lever measuring device 60b and the clamping measuring device 60a, obtain the axial force by measuring the distance the flange root of the casing mating flange is pulled apart under the action of axial force, it is feasible to use the sector segment casing for the calibration test of the casing axial force measuring device as long as the distance the flange root is pulled apart is consistent with that of the complete casing under the same proportional axial force. Figure 11A to Figure 11C The diagram shows the curves obtained through simulation analysis of the distance the flange root is pulled apart under the same proportional axial force on the axial force high-temperature calibration test device of the sector segment casing (calibration test component 1) and the complete casing at different temperatures. The horizontal axis represents the axial force loading ratio, and the vertical axis represents the distance the flange root is pulled apart.

[0074] Depend on Figure 11A to Figure 11C It can be seen that the difference in the distance at which the flange root is pulled apart when the calibration test assembly 1 and the complete casing are subjected to the same proportional axial force at different temperatures does not exceed 4%. Specifically, the difference is about 3.5% at room temperature, 2.5% at 500℃, and 0.5% at 700℃. Therefore, the high-temperature calibration test assembly 1 for the axial force of the aforementioned sector-shaped casing can replace the complete casing for calibration tests of the casing axial force measuring device, which can meet engineering requirements.

[0075] The calibration test assembly of the aforementioned calibration test device utilizes sector-shaped test pieces to simulate complete casing test pieces, which can significantly reduce the volume of the test pieces, shorten the production cycle, and reduce material costs. In this calibration test assembly, one sector-shaped segment simulates one complete casing, and another sector-shaped segment simulates another complete casing. Two sector-shaped segments are connected to form a pair of sector-shaped segment connections. A pair of identical sector-shaped segment connections are arranged vertically, forming two pairs of vertically symmetrical sector-shaped segments. This significantly reduces calibration errors caused by bending deformation of the flanges connecting the sector-shaped segments under axial force. In this calibration test assembly, the flanges of the sector-shaped segments only need to ensure that the flange structure between the two sector-shaped segments is consistent with the connecting flange structure of the complete casing. Other structural features of the complete casing do not need to be reflected in the sector-shaped segments. Compared to the complete casing, the structure of the sector-shaped segments is simpler, easier to manufacture, and lower in cost. Furthermore, the addition of reinforcing ribs in the middle of the sector-shaped segments in this calibration test assembly can significantly reduce the inward shrinkage deformation of the sector-shaped segments under axial force, making them closer to the state of the complete casing under axial force, thus reducing calibration errors.

[0076] Overall, the fan segment case axial force high temperature calibration test device and assembly have the characteristics of small volume, short production cycle, simple structure and low processing cost. When the device and assembly are applied to the case axial force high temperature calibration test, the problems of long production cycle, complex structure and high cost of the case axial force high temperature calibration test can be solved.

[0077] Although the present application is disclosed with the preferred embodiments as above, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present application. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, without departing from the technical solutions of the present application, fall within the protection scope defined by the claims of the present application.

Claims

1. A calibration test assembly for high-temperature calibration testing of the axial force of a casing, characterized in that, The calibration test assembly includes a docking test piece, which comprises two sector segments, multiple external bolts, and multiple docking bolts. The two sector segments are respectively used to simulate one casing of the docking housing. Each sector segment includes: The fan segment, extending axially and having a mating end and a connecting end, simulates a fan-shaped portion of the corresponding casing's body; A fan-shaped mating flange is disposed at the mating end of the fan segment. The mating flange has multiple mating holes distributed circumferentially, and the distribution of these multiple mating holes corresponds to the bolt holes on the corresponding mounting edge of the corresponding housing. A sector-shaped external flange is disposed at the connecting end of the sector segment, and the external flange has multiple external holes distributed circumferentially; and The test piece has a symmetrical plane parallel to the axial direction. Each sector segment is connected to the loading fixture or fixing fixture by passing through the external holes of the external flange with the plurality of external bolts. The two sector segments are connected to each other by passing through the docking holes of their respective docking flanges with the plurality of docking bolts. The span of the external bolts distributed circumferentially is larger than the span of the docking bolts distributed circumferentially.

2. The calibration test assembly as described in claim 1, characterized in that, The docking test specimen is the first docking test specimen; The calibration test assembly further includes a second docking test piece, which is arranged symmetrically with respect to the first docking test piece with respect to a second plane, the second plane being perpendicular to the plane of symmetry.

3. The calibration test assembly as described in claim 1 or 2, characterized in that, The external connection hole of the external flange is aligned axially with the mating hole of the mating flange.

4. The calibration test assembly as described in claim 1, characterized in that, The number of external bolts on the external flange is two more than the number of mating bolts on the mating flange.

5. The calibration test assembly as described in claim 1, characterized in that, The number of the mating bolts is at least six; and The number of external bolts is at least eight.

6. The calibration test assembly as described in claim 1, characterized in that, The number of external holes on the external flange is the same as the number of external bolts.

7. The calibration test assembly as described in claim 1, characterized in that, The sector segment has a reinforcing rib at the middle position along the axial direction.

8. The calibration test assembly as described in claim 1, characterized in that, The axial length of the sector is more than 1.5 times the height of the mating flange.

9. A calibration test apparatus for high-temperature calibration testing of the axial force of a casing, characterized in that, include: Calibration test assembly as described in any one of claims 1 to 8; A fixed fixture is connected to the external flange of one sector of the two sector segments of the calibration test assembly; and A loading fixture is connected to the outer flange of the other sector of the two sector segments of the calibration test assembly, thereby applying a simulated axial force to the calibration test assembly.

10. A calibration test method for high-temperature calibration test of axial force on a casing, characterized in that, The calibration test apparatus as described in claim 9, wherein the calibration test method includes: S1. Install the casing axial force measuring device onto the calibration test assembly of the calibration test device; S2. Place the calibration test assembly with the installed casing axial force measuring device into the environmental chamber, set the temperature according to a certain gradient, and then apply the simulated axial force step by step through the loading fixture of the calibration test device to obtain the relationship curve between the strain output of the casing axial force measuring device and the simulated axial force at different temperatures. S3. Repeat step S2 several times, and after averaging the results, obtain the final relationship curve between the strain output of the casing axial force measuring device and the casing axial force at different temperatures.

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