Measuring device for air inlet distortion test of aero-engine

Abstract

The invention discloses an aero-engine air inlet distortion test measuring device which is applied to be connected between an inlet of an aero-engine and a distortion generator, the test measuring device comprises a switching part and an air inlet flow guide basin, the switching part is used for being connected to the inlet of the aero-engine, a mounting cavity is formed in the switching part in a penetrating mode in the first direction, and the air inlet flow guide basin is arranged in the mounting cavity. A plurality of branch pipes are arranged in the mounting cavity at intervals in the second direction, and the branch pipes are parallel to the third direction; a plurality of static pressure measuring points are arranged on the windward side of each branch pipe at intervals in the third direction, and a total pressure measuring point is arranged on one side, in the third direction, of each static pressure measuring point; a plurality of total temperature measuring points are arranged on at least two branch pipes which are relatively close to the outside in the second direction; according to the device and the method, quick response is achieved when the change of an air inlet flow field of an engine reaches a distortion point, and static pressure parameters and total pressure parameters of all positions of the section, perpendicular to the first direction, of the mounting cavity are accurately obtained.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine test, and particularly to a measuring device for aero-engine inlet distortion test. Background Art

[0002] One of the common problems encountered in the use of aero-engines is the aerodynamic instability of the compression system. With the continuous progress of the research and development process of modern high-performance engines, higher requirements are put forward for solving key problems such as surge and over-temperature caused by engine inlet distortion. Therefore, it is of great significance to measure aero-engine inlet distortion.

[0003] During the process of measuring aero-engine inlet distortion test, first, a distortion generator is provided at the inlet of the aero-engine, and a distortion measuring device is provided between the distortion generator and the inlet of the aero-engine. By adjusting the insertion change of the distortion adjustment plate of the distortion generator, when the engine inlet flow field changes to the distortion point, the test parameters (specifically including static pressure, total pressure, and total temperature) mutate and are measured by the distortion measuring device. However, most of the existing distortion measuring devices are complex to install, the number of total temperature and total pressure measurement points is small, the test parameters respond slowly when the air flow changes, and the static pressure measurement points are set on the wall surface of the flow guiding basin, and the static pressure at the center position of the flow guiding basin cannot be accurately measured. Summary of the Invention

[0004] In view of this, the present invention provides a measuring device for aero-engine inlet distortion test to solve the problems that the existing distortion measuring device has a small number of total temperature and total pressure measurement points, the test parameters respond slowly when the air flow changes, and the static pressure measurement points are set on the wall surface of the flow guiding basin, and the static pressure at the center position of the flow guiding basin cannot be accurately measured.

[0005] The present invention provides a measuring device for aero-engine inlet distortion test, which is applied and connected between the inlet of the aero-engine and the distortion generator. The test measuring device includes:

[0006] An adapter part, which is used to connect to the inlet of the aero-engine. The adapter part is provided with an installation cavity penetrating along a first direction. A plurality of branch pipes are arranged at intervals along a second direction in the installation cavity. The branch pipes are arranged parallel to a third direction. The first direction, the second direction, and the third direction are perpendicular to each other in pairs; a plurality of static pressure measurement points are arranged at intervals along the third direction on the windward surface of each branch pipe, and a total pressure measurement point is arranged on one side of each static pressure measurement point along the third direction; a plurality of total temperature measurement points are arranged on at least two relatively outer branch pipes along the second direction;

[0007] An air inlet flow guiding basin, one end of which is detachably connected to the adapter part through a fastener, and the other end is used to connect to the distortion generator.

[0008] The aircraft engine intake distortion test and measurement device according to the present invention has at least the following beneficial effects:

[0009] By integrating a plurality of branch pipes evenly spaced along the second direction in the installation cavity of the adapter, and each branch pipe is evenly spaced along the third direction, a plurality of static pressure measuring points and total pressure measuring points are evenly spaced at various positions of the cross section in the installation cavity perpendicular to the first direction, so that a rapid response can be made when the change of the engine intake air flow field reaches a distortion point, and the static pressure parameters and total pressure parameters of various positions of the cross section of the installation cavity perpendicular to the first direction can be accurately obtained; total temperature measuring points are arranged at intervals on the windward surfaces of at least two relatively outer branch pipes along the second direction, so that a rapid response can be made when the change of the engine intake air flow field reaches a distortion point, and the total temperature parameters can be accurately obtained; at the same time, the adapter and the intake guide basin can be directly assembled into one by fasteners, without the need for welding and other operations, and the installation is simple.

[0010] In an optional embodiment, both end surfaces of the branch pipe along the third direction are flush with both side walls of the adapter portion along the third direction.

[0011] In an optional embodiment, the static pressure measuring point is connected to a first pressure pipe, and the total pressure measuring point is connected to a second pressure pipe. The first pressure pipe and the second pressure pipe are arranged in the branch pipe and extend from the opposite front side of the branch pipe along the third direction.

[0012] In an optional implementation, in the same branch pipe, a total temperature measuring point is provided on a side of each static pressure measuring point away from the total pressure measuring point along the third direction.

[0013] In an optional implementation, six branch pipes are provided, and the six branch pipes are numbered 1, 2, 3, ..., 6 in sequence along the second direction, and the windward surfaces of the two branch pipes numbered 2 and 4 are provided with the total temperature measuring points.

[0014] In an optional implementation, the total temperature measuring point is connected to a temperature measuring point lead, and the temperature measuring point lead is disposed in the branch pipe and extends from an opposite rear side of the branch pipe along the third direction.

[0015] In an optional embodiment, one end of the air intake guide basin facing away from the adapter portion is configured to be trumpet-shaped; a transition straight cylinder portion is provided between the adapter portion and the air intake guide basin, the adapter portion and the transition straight cylinder portion are detachably connected via a locking assembly, and the transition straight cylinder portion is detachably connected to the air intake guide basin via the fastener.

[0016] In an optional embodiment, the transition straight cylinder portion is folded outwardly toward the end surface of the air intake guide basin to form a first connecting plate, and the first connecting plate is provided with a plurality of first through holes at intervals along the contour of the first connecting plate; the air intake guide basin is folded outwardly toward the end surface of the transition straight cylinder portion to form a second connecting plate, and a second through hole is provided on the second connecting plate at a position corresponding to the first through hole; the fastener includes a matching first fastening bolt and a first nut; during assembly, the first fastening bolt passes through the corresponding first through hole and the second through hole, and is screwed onto the first nut.

[0017] In an optional embodiment, the adapter portion is folded outwardly toward the end surface of the transition straight tube portion to form a third connecting plate, and the third connecting plate is provided with a plurality of third through holes at intervals along the contour of the third connecting plate; the transition straight tube portion is folded outwardly toward the end surface of the adapter portion to form a fourth connecting plate, and the fourth connecting plate is provided with a fourth through hole at a position corresponding to the third through hole; the locking assembly includes a matching second fastening bolt and a second nut; during assembly, the second fastening bolt passes through the corresponding third through hole and the fourth through hole, and is screwed onto the second nut.

[0018] In an optional embodiment, the end surface of the adapter portion facing away from the air intake guide basin is folded outward to form a fifth connecting plate, and the fifth connecting plate is provided with a fifth through hole at a position corresponding to the threaded hole of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 This is a schematic diagram of the main structure of an aircraft engine intake distortion test and measurement device according to an embodiment of the present invention;

[0021] Figure 2 A schematic diagram of the top view of an aircraft engine intake distortion test and measurement device according to an embodiment of the present invention;

[0022] Figure 3 The present invention is a three-dimensional schematic diagram of a partial structure of an aircraft engine intake distortion test and measurement device according to an embodiment of the present invention.

[0023] Description of reference numerals:

[0024] 100 - Transfer part, 110 - Installation cavity, 120 - Branch pipe, 130 - Measuring point assembly, 131 - Static pressure measuring point, 132 - Total pressure measuring point, 133 - Total temperature measuring point, 141 - First pressure guiding pipe, 142 - Second pressure guiding pipe, 143 - Temperature measuring point lead wire, 150 - Third connecting plate, 151 - Third through hole, 160 - Fifth connecting plate, 161 - Fifth through hole;

[0025] 200 - Air inlet guiding basin, 210 - Second connecting plate;

[0026] 300 - Transition straight tube part, 310 - First connecting plate, 320 - Fourth connecting plate;

[0027] 410 - Distortion adjustment plate. Specific implementation manner

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Apparently, the described embodiments are some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0029] In the description of this embodiment, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing this embodiment and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to this embodiment. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0030] In the description of this embodiment, it should be noted that unless otherwise clearly specified and limited, the terms "install", "connect", and "couple" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in this embodiment can be understood according to specific circumstances.

[0031] The following combines Figures 1 to 3 , to describe the embodiments of the present invention.

[0032] According to an embodiment of the present invention, an aircraft engine intake distortion test and measurement device is provided, which is applied and connected between the inlet of the aircraft engine and the distortion generator. The test and measurement device includes an adapter 100 and an intake guide basin 200. The adapter 100 is used to be connected to the inlet of the aircraft engine. The adapter 100 is provided with a mounting cavity 110 along a first direction. A plurality of branch pipes 120 are arranged at intervals along a second direction in the mounting cavity 110. The branch pipes 120 are arranged parallel to a third direction. A plurality of static pressure measuring points 131 are arranged at intervals along the third direction on the windward surface of each branch pipe 120. Four static pressure measuring points 131 are preferably provided here. A total pressure measuring point 132 is provided on one side of each static pressure measuring point 131 along the third direction. A plurality of total temperature measuring points 133 are provided on at least two of the branch pipes 120 that are relatively close to the outside along the second direction. One end of the intake guide basin 200 is detachably connected to the adapter 100 by a fastener, and the other end is used to be connected to the distortion generator.

[0033] The intake distortion test and measurement device of the present embodiment is provided by integrating a plurality of branch pipes 120 evenly spaced along the second direction in the mounting cavity 110 of the adapter 100, and four static pressure measuring points 131 and four total pressure measuring points 132 are evenly spaced along the third direction on each branch pipe 120, so that a plurality of static pressure measuring points 131 and total pressure measuring points 132 are evenly spaced at various positions of the cross section perpendicular to the first direction in the mounting cavity 110, so that a rapid response is achieved when the change of the engine intake air flow field reaches the distortion point, and the static pressure parameters and total pressure parameters of various positions of the cross section perpendicular to the first direction of the mounting cavity 110 are accurately obtained; total temperature measuring points 133 are arranged at intervals on the windward surfaces of at least two relatively outer branch pipes 120 along the second direction, so that a rapid response is achieved when the change of the engine intake air flow field reaches the distortion point, and the total temperature parameters are accurately obtained; at the same time, the adapter 100 and the intake guide basin 200 can be directly assembled into one by fasteners, without the need for welding and other operations, and the installation is simple.

[0034] It should be noted that, because the branch pipe 120 and the adapter 100 are integrated as one in this embodiment, the steps of drilling a hole in the adapter 100, welding a mounting seat, and installing the branch pipe 120 on the mounting seat can be omitted, and the installation and assembly are simple.

[0035] It should be noted that the windward surface of the branch pipe 120 refers to an end surface of the branch pipe 120 that faces away from the aircraft engine along the first direction.

[0036] It can be understood that the branch pipe 120 is provided with perforations therethrough.

[0037] It can be understood that the first direction mentioned in the text refers to the airflow direction, and the second direction and the third direction are located in the same plane perpendicular to the first direction, that is, the first direction, the second direction and the third direction are parallel to each other.Figure 3 The first direction, the second direction, and the third direction are described as the first direction, the second direction, and the third direction, but should not be construed as a specific limitation on the first direction.

[0038] In some embodiments, the two end faces of the branch pipe 120 along the third direction are flush with the two side walls of the adapter 100 along the third direction; such that the branch pipe 120 is assembled with the adapter 100 in a double - fulcrum support manner. Compared with the installation method of "one - end support and one - end suspension", the assembly structure of the branch pipe 120 and the adapter 100 in this embodiment is stable, ensuring that the strength of the branch pipe 120 provided with a plurality of static pressure measurement points 131 and total pressure measurement points 132 meets the requirements without the need to additionally increase the diameter when the air flow changes suddenly. Because the branch pipe 120 is thin, the blockage ratio is small, thus ensuring that the windward surface of the branch pipe 120 provided with a plurality of static pressure measurement points 131 and total pressure measurement points 132 meets the blockage ratio requirement (specifically 5% for the inlet air flow passage).

[0039] As Figure 3 shown, specifically, the static pressure measurement point 131 is connected to a first pressure - guiding pipe 141, the total pressure measurement point 132 is connected to a second pressure - guiding pipe 142. The first pressure - guiding pipe 141 and the second pressure - guiding pipe 142 are arranged inside the branch pipe 120 and extend out from the relative front side of the branch pipe 120 along the third direction. Leading the first pressure - guiding pipe 141 and the second pressure - guiding pipe 142 out from the side surface of the adapter 100 along the third direction ensures that there is no interference with the aero - engine and the pipeline.

[0040] It should be noted that the relative front side and the relative rear side described in this embodiment are based on Figure 3 the perspective shown.

[0041] As Figure 3 shown, specifically, in the same branch pipe 120, a total temperature measurement point 133 is arranged on one side of each static pressure measurement point 131 along the third direction away from the total pressure measurement point 132; such that a total temperature measurement point 133, a total pressure measurement point 132, and a static pressure measurement point 131 are adjacent to each other to form a measurement point assembly 130, and the installation space occupied by the measurement point assembly 130 is small, such that more measurement point assemblies 130 can be arranged on the windward surface of the same branch pipe 120 without increasing the dimension in the third direction, which is beneficial to improving the test response speed and test accuracy.

[0042] Specifically, six branch pipes 120 are provided, and the six branch pipes 120 are numbered 1, 2, 3 ... 6 in sequence along the second direction, and the windward surfaces of the two branch pipes 120 numbered 2 and 4 are provided with the total temperature measuring points 133. By providing the total temperature measuring points 133 on the two branch pipes 120 symmetrically provided along the second direction about the center position of the installation cavity 110, the number of the total temperature measuring points 133 is reduced on the basis of meeting the precise measurement of the total temperature parameters; and only the total pressure measuring point 132 and the static pressure measuring point 131 are provided on some branch pipes 120, so as to compare and obtain whether the provision of the total temperature measuring point 133 on the side of the static pressure measuring point 131 away from the total pressure measuring point 132 along the third direction affects the measurement results of the total pressure measuring point 132 and the static pressure measuring point 131.

[0043] In order to further improve the uniformity of the cross-sectional distribution of the static pressure measuring points 131 and the total pressure measuring points 132 in the installation cavity 110 perpendicular to the first direction, specifically, the spacing between two adjacent static pressure measuring points 131 along the second direction is the same as the spacing between two adjacent branch pipes 120 .

[0044] Specifically, the total temperature measuring point 133 is connected to a temperature measuring point lead 143, which is disposed in the branch pipe 120 and extends from the relatively rear side of the branch pipe 120 along the third direction. On the one hand, the temperature measuring point lead 143 is led out from the side of the adapter 100 along the third direction to ensure that it does not interfere with the aircraft engine and pipelines; on the other hand, the temperature measuring point lead 143 and the first pressure lead pipe 141 are respectively led out from the two side surfaces of the adapter 100 along the third direction, so that the space utilization efficiency is higher.

[0045] like Figure 1 As shown, in some embodiments, the end of the air intake guide basin 200 away from the adapter 100 is set to be trumpet-shaped; a transition straight cylinder portion 300 is set between the adapter 100 and the air intake guide basin 200, and the adapter 100 and the transition straight cylinder portion 300 are detachably connected through a locking assembly, and the transition straight cylinder portion 300 is detachably connected to the air intake guide basin 200 through the fastener. First, the trumpet shape facilitates the introduction of airflow, and the transition is made through the transition straight cylinder portion 300, so that the airflow flow field entering the installation cavity 110 is basically consistent with the airflow flow field entering the aircraft engine inlet, so that the static pressure parameter, total pressure parameter and total temperature parameter are obtained more accurately when the engine intake airflow field changes to the distortion point. By detachably connecting the adapter 100, the transition straight cylinder portion 300 and the air intake guide basin 200, it is convenient to assemble for measurement, and it is also convenient to disassemble and store after the measurement is completed.

[0046] Specifically, a first connecting plate 310 is formed by turning the end surface of the transition straight cylinder part 300 facing the air inlet guide basin 200 outward. A plurality of first through holes are arranged at intervals along the contour of the first connecting plate 310. A second connecting plate 210 is formed by turning the end surface of the air inlet guide basin 200 facing the transition straight cylinder part 300 outward. Second through holes are arranged at positions corresponding to the first through holes on the second connecting plate 210. The fastener includes a matching first fastening bolt and a first nut. During assembly, first, align the first through holes of the first connecting plate 310 with the second through holes of the second connecting plate 210 along the first direction. Then, pass the first fastening bolt through the corresponding first through hole and second through hole, and screw the first nut. When disassembly is required, just remove the first nut from the corresponding first fastening bolt. The disassembly and assembly are convenient. At the same time, by turning the first connecting plate 310 and the second connecting plate 210 outward, the contact connection area between the transition straight cylinder part 300 and the air inlet guide basin 200 is increased, further improving the connection strength between the two.

[0047] As Figure 1 and Figure 2 shown, specifically, a first groove is provided on the end surface of the transition straight cylinder part 300 facing the air inlet guide basin 200, and a second groove is provided on the end surface of the air inlet guide basin 200 facing the transition straight cylinder part 300. During assembly, the first groove and the second groove enclose a connection cavity. The distortion generator includes a distortion adjustment plate 410. The distortion adjustment plate 410 is slidably arranged in the connection cavity along the second direction and is driven to slide by a driving motor. By assembling the transition straight cylinder part 300 and the air inlet guide basin 200, a connection cavity for the distortion adjustment plate 410 to slide is obtained, further simplifying the installation difficulty.

[0048] As Figure 1 and Figure 3As shown, specifically, the adapter portion 100 is folded outwardly toward the end surface of the transition straight tube portion 300 to form a third connecting plate 150, and the third connecting plate 150 is provided with a plurality of third through holes 151 at intervals along the contour of the third connecting plate 150; the transition straight tube portion 300 is folded outwardly toward the end surface of the adapter portion 100 to form a fourth connecting plate 320, and the fourth connecting plate 320 is provided with a fourth through hole at a position corresponding to the third through hole 151; the locking assembly includes a matching second fastening bolt and a second nut; during assembly, first align the third through hole 151 of the third connecting plate 150 with the fourth through hole of the fourth connecting plate 320 along the first direction, then pass the second fastening bolt through the corresponding third through hole 151 and the fourth through hole, and screw on the second nut; when disassembly is required, just remove the second nut from the corresponding second fastening bolt, which is convenient for disassembly and assembly. At the same time, the third connecting plate 150 and the fourth connecting plate 320 are formed by folding outwards, thereby increasing the contact and connection area between the transition straight tube portion 300 and the adapter portion 100, and further improving the connection strength between the two.

[0049] Specifically, the end surface of the adapter portion 100 facing away from the air intake guide basin 200 is folded outward to form a fifth connecting plate 160, and the fifth connecting plate 160 is provided with a fifth through hole 161 at a position corresponding to the threaded hole of the aircraft engine; when assembling for testing, it is only necessary to align the fifth through hole 161 of the fifth connecting plate 160 with the threaded hole of the aircraft engine along the first direction, and then use a screw to pass through the fifth through hole 161 and thread it into the threaded hole to realize the assembly of the intake distortion test measuring device of this embodiment with the aircraft engine, which is easy to install; at the same time, by folding outward to form the fifth connecting plate 160, the contact connection area between the adapter portion 100 and the aircraft engine is increased, and the connection strength between the two is further improved.

[0050] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are all within the scope defined by the present invention.

Claims

1. An intake distortion test measurement device for an aeroengine, which is applied and connected between the inlet of the aeroengine and the distortion generator, is characterized in that, The test measuring device comprises: An adapter (100) is used to be connected to the inlet of an aircraft engine, wherein the adapter (100) is provided with an installation cavity (110) penetrating along a first direction, wherein a plurality of branch pipes (120) are arranged in the installation cavity (110) at intervals along a second direction, wherein the branch pipes (120) are arranged parallel to a third direction, and the first direction, the second direction and the third direction are mutually perpendicular in pairs; a plurality of static pressure measuring points (131) are arranged at intervals along the third direction on the windward surface of each branch pipe (120), and a total pressure measuring point (132) is arranged on one side of each static pressure measuring point (131) along the third direction; and a plurality of total temperature measuring points (133) are arranged on at least two of the branch pipes (120) that are relatively close to the outside along the second direction; An air intake guide basin (200) has one end detachably connected to the adapter (100) via a fastener, and the other end is used to be connected to the distortion generator.

2. The aero-engine inlet distortion test measurement device according to claim 1, characterized in that, Both end surfaces of the branch pipe (120) along the third direction are flush with two side walls of the adapter portion (100) along the third direction.

3. The aeroengine inlet distortion test measurement device according to claim 2, wherein The static pressure measuring point (131) is connected to a first pressure-guiding pipe (141), and the total pressure measuring point (132) is connected to a second pressure-guiding pipe (142). The first pressure-guiding pipe (141) and the second pressure-guiding pipe (142) are arranged in the branch pipe (120) and extend from the opposite front side of the branch pipe (120) along the third direction.

4. The aeroengine inlet distortion test measurement device according to claim 3, wherein On the same branch pipe (120), a total temperature measuring point (133) is provided on a side of each static pressure measuring point (131) away from the total pressure measuring point (132) along the third direction.

5. The aeroengine inlet distortion test measurement device according to claim 4, characterized in that, Six branch pipes (120) are provided, and the six branch pipes (120) are numbered 1, 2, 3, ... 6 in sequence along the second direction, and the windward surfaces of the two branch pipes (120) numbered 2 and 4 are provided with the total temperature measuring points (133).

6. An aeroengine inlet distortion test measurement device according to claim 4 or 5, characterized in that, The total temperature measuring point (133) is connected to a temperature measuring point lead (143), and the temperature measuring point lead (143) is arranged in the branch pipe (120) and extends from the relatively rear side of the branch pipe (120) along the third direction.

7. An aero-engine inlet distortion test measurement device according to claim 1, characterized in that One end of the air intake guide basin (200) facing away from the adapter portion (100) is arranged in a trumpet shape; a transition straight cylinder portion (300) is arranged between the adapter portion (100) and the air intake guide basin (200); the adapter portion (100) and the transition straight cylinder portion (300) are detachably connected via a locking assembly; and the transition straight cylinder portion (300) is detachably connected to the air intake guide basin (200) via the fastener.

8. The aeroengine inlet distortion test measurement device according to claim 7, characterized in that, The transition straight cylinder portion (300) is folded outwardly toward the end surface of the air intake guide basin (200) to form a first connecting plate (310), and the first connecting plate (310) is provided with a plurality of first through holes at intervals along the contour of the first connecting plate (310); the air intake guide basin (200) is folded outwardly toward the end surface of the transition straight cylinder portion (300) to form a second connecting plate (210), and a second through hole is provided on the second connecting plate (210) at a position corresponding to the first through hole; the fastener comprises a matching first fastening bolt and a first nut; during assembly, the first fastening bolt passes through the corresponding first through hole and the second through hole, and is screwed onto the first nut.

9. An aeroengine inlet distortion test measurement device according to claim 7 or 8, characterized in that, The end surface of the adapter portion (100) is folded outwardly toward the transition straight tube portion (300) to form a third connecting plate (150), and the third connecting plate (150) is provided with a plurality of third through holes (151) at intervals along the contour of the third connecting plate (150); the end surface of the transition straight tube portion (300) is folded outwardly toward the adapter portion (100) to form a fourth connecting plate (320), and the fourth connecting plate (320) is provided with a fourth through hole at a position corresponding to the third through hole (151); the locking assembly comprises a matching second fastening bolt and a second nut; during assembly, the second fastening bolt passes through the corresponding third through hole (151) and the fourth through hole, and is screwed onto the second nut.

10. An aeroengine inlet distortion test measurement device according to claim 1 or 7, characterized in that, The end surface of the adapter portion (100) facing away from the air intake guide basin (200) is folded outward to form a fifth connecting plate (160), and the fifth connecting plate (160) is provided with a fifth through hole (161) at a position corresponding to the threaded hole of the aircraft engine.

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