Test apparatus for containment capability of aero-engine casing

Abstract

The present invention belongs to the technical field of test inspection, and specifically relates to a test apparatus for the containment capability of an aero-engine casing, comprising a horizontal base plate, an air cannon device, a support device, a measurement device and a safety protection device, wherein the air cannon device comprises an air cannon base, an air cannon chamber, an electrical cabinet, a chamber controller, a flange, a cannon barrel, and a component detachment device; the support device comprises a cannon barrel bracket, a pair of infrared dot sensor brackets, and a dual-port fixture; the measurement device comprises infrared dot sensors, a signal transceiver, a power supply, a data acquisition instrument, a high-speed camera, and a data processor; and the safety protection device comprises explosion-proof glass, a protective panel and a pair of protective walls. The present invention having a rationally designed structure allows accurate simulation of the impact between screws or nuts after failure and the casing and adjacent components, thereby improving the safety and reliability of the casing, providing significant application prospects in aviation engineering.

Description

An aero-engine casing containment test device TECHNICAL FIELD

[0001] The present application belongs to the technical field of test detection, and particularly relates to an aero-engine casing containment test device. BACKGROUND

[0002] The aero-engine casing is an important component of the engine, and the performance thereof directly affects the overall performance and safety of the engine. The casing bears dynamic and static loads under various complex environments in actual working conditions, including centrifugal load, thermal load and vibration load, etc. The screw and nut are one of the important parts of the casing containment. The damage mode of the engine casing containment screw or nut is obtained through test, which is the key to ensure the flight safety of the whole machine. Therefore, it is of important practical significance and strategic significance to carry out the aero-engine casing containment test technology research.

[0003] The present application simulates the failure conditions of the important parts of the screw or nut in the engine casing, including the impact of the screw or nut after failure with the casing and adjacent parts and the impact of the parts fixed by the screw or nut after flying out under the action of unbalanced load on the support system, measures the speed of the screw or nut after flying out and the damage form of the impact on the casing, to examine the reliability and safety of the casing, so as to verify the safety and reliability of the aero-engine casing containment test device based on the air gun. SUMMARY

[0004] To solve the problems in the prior art, the present application provides an aero-engine casing containment test device.

[0005] The present application provides the following technical scheme:

[0006] An aero-engine casing containment test device, comprising a horizontal bottom plate, an air gun device, a support device, a measuring device and a safety protection device, wherein:

[0007] The air gun device comprises an air gun base, an air gun gas chamber, an electrical cabinet, a gas chamber controller, a flange plate, a barrel and a piece removing device, the air gun base is arranged at one end of the horizontal bottom plate, the air gun gas chamber comprises a large gas chamber and a small gas chamber in the large gas chamber, the large gas chamber is connected with the electrical cabinet through a gas pipe, one end of the large gas chamber and one end of the small gas chamber are connected with the air gun base, the other end of the large gas chamber is connected with the flange plate, one end of the barrel passes through the flange plate and is connected with the small gas chamber, and the other end is connected with the piece removing device, and a part tray is freely arranged in the barrel;

[0008] The support device comprises a barrel support, a pair of infrared point sensor supports and a double-port fixing tool, the infrared point sensor support comprises a hollow inverted T-shaped support and a hollow horizontal rod at the upper end of the inverted T-shaped support, the inverted T-shaped support comprises a horizontal part and a vertical part, a waist-shaped hole is arranged on each of the horizontal part and the vertical part, a horizontal rod mounting through hole, a pair of sensor mounting through holes and a threaded hole are arranged on the horizontal rod, and the double-port fixing tool is arranged corresponding to the piece separating device;

[0009] The measuring device comprises infrared point sensors, signal transceivers, power supplies, data acquisition instruments, high-speed cameras and data processors, the infrared point sensors are electrically connected with the signal transceivers, the signal transceivers are electrically connected with the data acquisition instruments, the signal transceivers and the data acquisition instruments are respectively electrically connected with the power supplies, and the data acquisition instruments and the high-speed cameras are respectively connected to the data processors.

[0010] The safety protection device comprises an explosion-proof glass, a protection plate and a pair of protection walls, the protection plate is arranged at the other end of the horizontal bottom plate, the pair of protection walls are arranged on the two sides of the other end of the horizontal bottom plate, and the explosion-proof glass and the high-speed camera are arranged between the horizontal bottom plate and the protection walls.

[0011] Compared with the prior art, the present application has the following beneficial effects:

[0012] 1、The piece separating device in the present application can effectively separate the screw or nut from the part tray, and can achieve the purpose of truly simulating the impact of the cartridge.

[0013] 2、The infrared point sensor support in the present application can effectively place the infrared point sensor, and the waist-shaped hole on the structure can help accurately focus the laser emitter and receiver, effectively ensuring the accuracy and efficiency of the speed measurement.

[0014] 3、The double-port fixing tool in the present application can effectively ensure that the placed cartridge and other related parts can be focused on the barrel outlet, and can accurately hit cartridges and other related parts of various models through rotation and movement.

[0015] 4、Compared with the traditional barrel in the same research direction, the barrel in the present application is longer, and the purpose of this design is to ensure that the part tray has enough acceleration distance; the inner diameter is smaller, and when the weight of the part tray is light enough, the part tray will be faster under the impact of air pressure.

[0016] 5、The part tray in the present application has a groove design, which can ensure that the screw or nut can be better placed, and can be separated from the part tray by the piece separating device under the action of inertial force.

[0017] 6、The present application is based on air cannon and aircraft engine casing and other parts, combined design of a complete set of test device can complete the containment of the casing, this test device can accurately simulate the important parts of the engine casing screw or nut in failure caused by the casing and other related parts of the impact situation, through the actual simulation can effectively improve the safety and reliability of the casing and other related parts. BRIEF DESCRIPTION OF DRAWINGS

[0018] Fig. 1 is a schematic diagram of the present application one;

[0019] Fig. 2 is a schematic diagram of the present application two;

[0020] Fig. 3 is a schematic diagram of the present application three;

[0021] Fig. 4 is a schematic diagram of the air chamber of the air cannon;

[0022] Fig. 5 is a schematic diagram of the flange plate;

[0023] Fig. 6 is a schematic diagram of the barrel;

[0024] Fig. 7 is a schematic diagram of the piece device one;

[0025] Fig. 8 is a schematic diagram of the piece device two;

[0026] Fig. 9 is a schematic diagram of the part tray one;

[0027] Fig. 10 is a schematic diagram of the part tray two;

[0028] Fig. 11 is a schematic diagram of the sensor bracket;

[0029] Fig. 12 is a schematic diagram of the cross bar in the sensor bracket;

[0030] Fig. 13 is a schematic diagram of the double mouth type fixed tooling;

[0031] Fig. 14 is a schematic diagram of the double break method speed measurement.

[0032] Wherein, 1-horizontal bottom plate, 2-air cannon base, 3-air cannon gas chamber, 31-large air chamber, 311-flange end face, 312-air inlet, 32-small air chamber, 321-threaded through hole, 4-electrical cabinet, 5-gas chamber controller, 6-flange plate, 61-flange base, 62-U-shaped frame, 621-fastening through hole, 63-fixing seat, 631-threaded mounting hole, 7-cannon barrel, 71-air outlet hole, 72-handle, 8-removing device, 81-first through hole, 82-small hole, 9-part tray, 91-second through hole, 92-screw groove, 93-nut groove, 10-cannon barrel support, 11-infrared point sensor support, 111-inverted T-shaped support, 1111-waist-shaped hole, 112-crossbar, 1121-crossbar mounting through hole, 1122-sensor mounting through hole, 1123-threaded hole, 12-double-port fixing tool, 13-infrared point sensor, 14-signal transceiver, 15-power supply, 16-data acquisition instrument, 17-high-speed camera, 18-data processor, 19-explosion-proof glass, 20-protection plate, 21-protection wall, 22-bullet. DETAILED DESCRIPTION

[0033] The technical solutions of the application are further described below in combination with the drawings and examples.

[0034] As shown in FIGS. 1-14, an aero-engine case containment test device includes a horizontal bottom plate 1, an air cannon device, a support device, a measuring device, and a safety protection device, wherein:

[0035] The air cannon device includes an air cannon base 2, an air cannon gas chamber 3, an electrical cabinet 4, a gas chamber controller 5, a flange plate 6, a cannon barrel 7, and a removing device 8, the air cannon base 2 is arranged at one end of the horizontal bottom plate 1, the air cannon gas chamber 3 includes a large air chamber 31 and a small air chamber 32 in the large air chamber 31, the large air chamber 31 is connected with the electrical cabinet 4 through an air pipe, one end of the large air chamber 31 and one end of the small air chamber 32 are connected with the air cannon base 2, the other end of the large air chamber 31 is connected with the flange plate 6, one end of the cannon barrel 7 penetrates through the flange plate 6 and is connected with the small air chamber 32, and the other end of the cannon barrel 7 is connected with the removing device 8, and a part tray 9 is freely arranged in the cannon barrel 7;

[0036] The support device includes a cannon barrel support 10, a pair of infrared point sensor supports 11, and a double-port fixing tool 12, the infrared point sensor support 11 includes a hollow inverted T-shaped support 111 and a hollow crossbar 112 at the upper end of the inverted T-shaped support 111, the inverted T-shaped support 111 includes a horizontal portion and a vertical portion, the horizontal portion and the vertical portion are both provided with a waist-shaped hole 1111, the crossbar 112 is provided with a crossbar mounting through hole 1121, a pair of sensor mounting through holes 1122, and threaded holes 1123, and the double-port fixing tool 12 is arranged correspondingly to the removing device 8.

[0037] The measuring device comprises an infrared point sensor 13, a signal transceiver 14, a power supply 15, a data acquisition instrument 16, a high-speed camera 17 and a data processor 18, the infrared point sensor 13 is electrically connected with the signal transceiver 14, the signal transceiver 14 is electrically connected with the data acquisition instrument 16, the signal transceiver 14 and the data acquisition instrument 16 are respectively electrically connected with the power supply 15, and the data acquisition instrument 16 and the high-speed camera 17 are respectively connected to the data processor 18.

[0038] The safety protection device comprises an explosion-proof glass 19, a protection plate 20 and a pair of protection walls 21, the protection plate 20 is arranged at the other end of the horizontal bottom plate 1, the pair of protection walls 21 are arranged at the two sides of the other end of the horizontal bottom plate 1, and the explosion-proof glass 19 and the high-speed camera 17 are arranged between the horizontal bottom plate 1 and the protection wall 21.

[0039] The aero-engine casing containment test device, one end of the atmosphere chamber 31 is provided with a flange end face 311, the top of the small atmosphere chamber 32 is provided with a threaded through hole 321, the flange plate 6 comprises a flange base 61, a U-shaped frame 62 in the middle of the flange base 61 and a fixing seat 63 with a threaded mounting hole 631 in the U-shaped frame 62, the threaded mounting hole 631 penetrates through the flange base 61, both ends of the barrel 7 are provided with external threads, one end of the atmosphere chamber 31 and one end of the small atmosphere chamber 32 are welded together with the air cannon base 2, the large flange end face 311 of the atmosphere chamber 31 is connected with the flange base 61 of the flange plate 6 through bolts, one end of the barrel 7 penetrates through the threaded mounting hole 631 and is connected with the threaded through hole 321 at the top of the small atmosphere chamber 32, and the other end is connected with the piece removing device 8 through threads.

[0040] The aero-engine casing containment test device, the piece removing device 8 is an open-ended cylinder, an internal thread is arranged in the cylinder, and a first through hole 81 is arranged in the middle of the bottom.

[0041] The aero-engine casing containment test device, the part tray 9 is a hollow cylinder, a second through hole 91 is arranged in the middle of the bottom, and a groove is arranged at the top.

[0042] The aero-engine casing containment test device, a pair of infrared point sensor supports 11 are symmetrically arranged at both sides of the barrel 7, the infrared point sensor supports 11 are fixed on the horizontal bottom plate 1 through screws at the bottom, a gas outlet hole 71 is symmetrically arranged on the barrel 7, and the sensor mounting through hole 1122 is aligned with the gas outlet hole 71 on the barrel 7.

[0043] The aero-engine casing containment test device, a pair of handles 72 are arranged on the barrel 7.

[0044] The air cannon base 2, the cannon barrel support 10, the double-port type fixing tool 12, the explosion-proof glass 19 and the protective plate 20 are connected with the horizontal bottom plate 1 through bolts.

[0045] The air cannon device is a set of devices designed on the basis of the existing air cannon (model RLHDNJ-KQP, including an air cannon air chamber, an electrical cabinet, an air chamber controller, a cannon barrel and the like, and the air cannon air chamber includes a large air chamber and a small air chamber). Among them, the air cannon air chamber, the electrical cabinet and the air chamber controller are used without change in the application.

[0046] The air cannon air chamber 3, the large air chamber 31 and the small air chamber 2 are all cylinders, the large air chamber 31 is inflated and pressure maintained through the air inlet 312 on the large air chamber 31, then the air pressure in the large air chamber 31 fills the small air chamber 32, and the small air chamber 32 reaches a certain air pressure through the air chamber controller 5 and then releases the pressure impact on the part tray 9.

[0047] The electrical cabinet 4 has an air inlet and an air outlet, the air inlet is connected with the air chamber controller 5, and the air outlet is connected with the air cannon air chamber 3. The air chamber controller 5 has specific buttons and air pressure display, and the air pressure value is controlled to a certain value through the buttons, and then the pressure is released.

[0048] The threaded mounting hole 631 on the fixed seat 63 of the flange plate 6 penetrates the flange base 61. Threaded holes are arranged on the U-shaped frame 62 and the fixed seat 63, the U-shaped frame 62 and the fixed seat 63 are connected with the flange base 61 through the threaded holes, fastening through holes 621 are symmetrically arranged on the side wall of the U-shaped frame 62, a through hole is arranged on the fixed seat 63 and communicates with the fastening through holes 621, a screw is screwed into the fastening through holes 621 and passes through the through hole on the fixed seat 63 to abut against the cannon barrel 7 for fastening the cannon barrel 7.

[0049] The handle 72 is arranged on the cannon barrel 7 by welding, which facilitates the rotational connection of the two ends of the cannon barrel 7 with the flange plate 6 and the part releasing device 8 respectively; two pairs of air outlet holes 71 are symmetrically arranged on the cannon barrel 7 and penetrate the cannon barrel 7.

[0050] The part releasing device 8 separates the part tray 9 from the screw or nut placed in the groove of the part tray 9. When the screw or nut flies out of the first through hole 81 of the part releasing device 8, the posture of the screw or nut flying out and the process of impacting the housing and other related parts are shot by the high-speed camera 17. Small holes 82 are symmetrically arranged on the bottom side wall of the part releasing device 8, which facilitates the action of the force rod and the rotation of the part releasing device 8 and the cannon barrel 7 during installation or disassembly.

[0051] The part tray 9 is a hollow structure, the purpose is to reduce weight; the part tray 9 is initially freely placed in the barrel 7, and in order to achieve longer distance acceleration effect in formal test, the part tray 9 needs to be pushed to the bottom of the barrel 7 through the tool telescopic rod. The front end of the part tray 9 is provided with a recess, such as a screw groove 92 or a nut groove 93, for placing a screw or a nut, and the size of the screw or the nut can be changed by changing the size of the recess on the part tray 9 for placing the screw or the nut. The part tray 9 and the screw or the nut are separated by the part separating device 8, at this time the part tray 9 is blocked in the part separating device 8, only the screw or the nut is thrown out, and the failure mode of the screw or the nut is mainly flying off. In order to buffer the great impact of the part tray 9 in the impact process, a silica gel pad with a thickness of 4-5 cm is placed in the part separating device 8.

[0052] The infrared point sensor support 11 is used to place the infrared point sensor 13, so that the transmitting end and the receiving end are kept in a straight line and as close as possible, the light beam is enhanced, and the accuracy when being blocked is improved. The horizontal part and the vertical part of the hollow inverted T-shaped support 111 are provided with four pairs of waist-shaped holes 1111, the overall structure can be adjusted left and right through the waist-shaped holes on the horizontal part, and the horizontal rod can be adjusted up and down through the waist-shaped holes on the vertical part; a pair of horizontal rod mounting through holes 1121 on the horizontal rod 112 are used to be connected with a pair of waist-shaped holes 1111 on the vertical part of the inverted T-shaped support 111 through bolts, a pair of sensor mounting through holes 1122 on the horizontal rod 112 are used to place the infrared point sensor 13, and a pair of threaded holes 1123 are provided to press the infrared point sensor 13 through a screw to prevent the infrared point sensor 13 from being blown away by air flow. The bottom of the infrared point sensor support 11 is fixed on the horizontal bottom plate 1 through a screw, and the hole position for placing the infrared point sensor 13 can be aligned with the air outlet holes 71 on both sides of the barrel 7 through the adjustment of the waist-shaped holes, and then the infrared point sensor 13 is placed in the sensor mounting through hole 1122, so that the transmitter and the receiver of the infrared point sensor 13 are kept in a straight line with the air outlet holes 71 of the barrel 7. The signal transceiver 14 is connected with the infrared point sensor 13 for sensing signals, and the other port of the signal transceiver 14 is connected with the data acquisition instrument 16, the signals sensed by the signal transceiver 14 can be collected by the data acquisition instrument 16, the data acquisition instrument 16 is connected with the data processor 18, the collected data can be analyzed through the data processor 18, and the data processor 18 adopts a computer.

[0053] The double-port fixing tool 12 is used to place the cartridge and other related parts and can adjust the position according to the size of the parts to ensure that the parts can be adjusted according to the position of the barrel 7. The double-port fixing tool 12 is a hollow shell without plates in front and back. The double-port fixing tool 12 is provided with a plurality of threaded holes and waist-shaped holes for fixing the cartridge and other parts on the double-port fixing tool 12 and fixing the double-port fixing tool 12 on the horizontal bottom plate 1. The cartridge and other parts can be adjusted in direction by rotating the cartridge and other parts or the double-port fixing tool 12. The waist-shaped holes can also be used to move and adjust the position of the double-port fixing tool or the cartridge and other parts, which are all to ensure focusing with the barrel outlet and facilitate better impact of the screw or nut. Whether the cartridge is fixed inside or outside the double-port fixing tool 12 depends on the actual size and position of the cartridge. If the product is large and needs to be fixed outside, the cartridge is fixed inside, otherwise. In short, the cartridge and other related parts are fixed by screwing through the double-port fixing tool 12, and the position of the specific cartridge and other related parts can be adjusted to ensure that the screw or nut can accurately hit the test piece.

[0054] The infrared point sensor 13 is a complete system, including two LSSPD-1.2-3P photodiodes, two IV conversion amplifiers, two linear DC voltage stabilizing power modules (±12V), two infrared point lasers 5mW 650nm 5mW, and Dupont wires and 50Ω SMA to BNC radio frequency coaxial cable lines. The signals of the transmitting end and the receiving end are different, and are converted through the IV amplifier. Finally, the voltage signal is collected by the data acquisition instrument. The model of the infrared point sensor 13 is CZ3460. One pair of infrared point sensor supports 11, one of which on the barrel side, the pair of sensor mounting holes 1122 on the crossbar 112 of which are used to place the signal transmitter, specifically the infrared point laser. The other one on the other side of the barrel, the pair of sensor mounting holes 1122 on the crossbar 112 of which are used to place the signal receiver, specifically the photodiode. The signal transmitter and the signal receiver are connected to the IV conversion amplifier for signal conversion. The converted signal is transmitted to the terminal processing through the data acquisition instrument, and the power module provides power for the IV conversion amplifier.

[0055] The data acquisition instrument 16 is a DH5922D model, and the collected data is a voltage signal. The speed is calculated by the interval time of the voltage signal. The specific method of calculating the speed is the double-laser blocking method. The speed measurement system uses infrared point sensors to measure the speed by the double-blocking method. The main method is to use the data acquisition instrument 16 to collect the blocking signal to obtain the time difference, and then divide the distance between the two pairs of sensors by the time difference to obtain the speed. The high-speed camera can capture the posture and impact of the screw or nut separated by the piece separating device.

[0056] The double laser interruption method refers to that two pairs of lasers are arranged on both sides of the symmetrically opened holes at the front end of the barrel, one side is a laser transmitter and the other side is a laser receiver, and the infrared rays form a straight line before interruption. When the front end of an object passes through the first pair of sensors, the infrared rays are interrupted at this time, and when the rear end of the object passes through the first pair of sensors, the infrared rays are restored at this time, which is the single interruption method. When the front end of an object passes through the second pair of sensors, the infrared rays of the second pair of sensors are interrupted at this time, and when the rear end of the object passes through the second pair of sensors, the infrared rays are restored at this time, which is the double interruption method. The speed of the object can be obtained by dividing the distance between the two pairs of sensors by the interval time of the front end of the object passing through the two pairs of sensors.

[0057] The calculation method of the double interruption method of the infrared point sensor is shown in FIG. 14. The interval time of the bullet 22 passing through the infrared point sensor 13 with a distance L is recorded as ΔT, and the bullet calculation speed is as follows:

[0058] Vbullet=L / ΔT

[0059] Here, the front end of the part tray 9 is slotted to place a screw or nut, so it is analogous to the bullet 22, that is, the shell corresponds to the part tray 9, and the bullet head corresponds to the screw or nut; the screw or nut is placed in the part tray 9, and the air chamber is used to accelerate the entire part tray 9, that is, the screw or nut placed in the part tray 9.

[0060] The speed of the screw or nut before flying out of the barrel port is also the speed of the part tray 9, and at this time the part tray 9 and the screw or nut have not been separated, and the size of the groove on the part tray 9 for placing the screw or nut is changed, and different models of screws or nuts are placed to simulate the test conditions of the screw or nut flying out at high speed and impacting the machine case and other parts in the real environment.

[0061] The high-speed camera 17 is used to shoot the posture of the screw or nut flying out and the process of impacting the machine case and other parts. Specifically, the high-speed camera 17 is placed on one side of the outlet of the barrel 7, and the explosion-proof glass 19 is placed outside the high-speed camera 17 to protect the high-speed camera 17.

[0062] In order to prevent the screw or nut from flying in an unpredictable trajectory due to failure, a protective plate 20 and a protective wall 21 are provided for protection. Specifically, the protective plate 20 is arranged behind the outlet of the barrel 7, and the protective wall 21 is made of sand and placed on both sides of the outlet of the barrel 7. The purpose of arranging the protective plate 20 and the protective wall 21 is to prevent the flying screw or nut from flying in an unpredictable trajectory due to failure, and to protect the surrounding objects and the environment.

[0063] During the test, first, the air cannon device and the supporting device are built; then, the measuring device and the safety protection device are arranged near the barrel 7; finally, the air pressure in the air cannon air chamber 3 is controlled to accelerate the impact of the part tray 9, and the screws or nuts placed in the part tray 9 are separated under the action of the part separating device 8, so that the flying screws or nuts impact the case and other parts.

[0064] The present application is based on the existing air cannon system and the aero-engine case and other parts, and a complete set of test device capable of completing the case containment test is designed, which can accurately simulate the impact of the important screw or nut of the engine case on the case and other related parts when the screw or nut fails, and the safety and reliability of the case and other related parts can be effectively improved through actual simulation.

[0065] The present application fixes and debugs the simulation parts or the real engine case through the double-port fixing tool, and the main research contents include determining the screw or nut launch speed and determining the screw or nut impact posture of the case; the safety performance of the case is researched by changing the state of the contained parts of the case containment test device; the reliability and safety of the case can be researched by changing the size of the screw or nut, the impact speed of the screw or nut, the failure mode of the screw or nut, etc.; the speed of the screw or nut before flying out of the barrel port is determined by the double laser blocking method, and the test situation of the screw or nut impacting the case and other parts after flying out at high speed in the real environment is simulated by changing the air cannon air pressure and the size of the part tray.

[0066] Compared with the prior art, the aero-engine case containment test device provided by the present application has a scientific structure design, can accurately simulate the impact of the screw or nut after failure on the case and adjacent parts, and can improve the safety and reliability of the case, and has important aviation engineering application prospect.

[0067] The principles and implementation modes of the present application are described by applying specific examples in this paper, and the above examples are only used to help understand the method and core idea of the present application. The above description is only the preferred embodiment of the present application. It should be pointed out that due to the limitation of language expression, there are infinite specific structures, and for ordinary skilled persons in the technical field, some improvements, refinements or changes can be made without departing from the principles of the present application, and the above technical features can be combined in an appropriate way; these improvements, refinements, changes or combinations, or the direct application of the inventive concept and technical scheme to other occasions without improvement, shall be regarded as the protection scope of the present application.

Claims

1. An aeroengine case containment test apparatus, characterised in that, The application relates to an air cannon device, which comprises a horizontal bottom plate (1), an air cannon device, a supporting device, a measuring device and a safety protection device, wherein: The air cannon device comprises an air cannon base (2), an air cannon air chamber (3), an electric cabinet (4), an air chamber controller (5), a flange plate (6), a cannon barrel (7) and a piece removing device (8), the air cannon base (2) is arranged at one end of the horizontal bottom plate (1), the air cannon air chamber (3) comprises a large air chamber (31) and a small air chamber (32) in the large air chamber (31), the large air chamber (31) is connected with the electric cabinet (4) through an air pipe, one end of the large air chamber (31) and one end of the small air chamber (32) are connected with the air cannon base (2), the other end of the large air chamber (31) is connected with the flange plate (6), one end of the cannon barrel (7) penetrates through the flange plate (6) and is connected with the small air chamber (32), and the other end of the cannon barrel (7) is connected with the piece removing device (8); a part tray (9) is freely arranged in the cannon barrel (7); The supporting device comprises a cannon barrel support (10), a pair of infrared point sensor supports (11) and a double-port type fixing tool (12), the infrared point sensor support (11) comprises a hollow inverted T-shaped support (111) and a hollow horizontal rod (112) at the upper end of the inverted T-shaped support (111), the inverted T-shaped support (111) comprises a horizontal part and a vertical part, a waist-shaped hole (1111) is arranged on the horizontal part and the vertical part, a horizontal rod mounting through hole (1121), a pair of sensor mounting through holes (1122) and screw holes (1123) are arranged on the horizontal rod (112), and the double-port type fixing tool (12) is arranged correspondingly to the piece removing device (8); The measuring device comprises an infrared point sensor (13), a signal transceiver (14), a power supply (15), a data acquisition instrument (16), a high-speed camera (17) and a data processor (18), the infrared point sensor (13) is electrically connected with the signal transceiver (14), the signal transceiver (14) is electrically connected with the data acquisition instrument (16), the signal transceiver (14) and the data acquisition instrument (16) are respectively electrically connected with the power supply (15), and the data acquisition instrument (16) and the high-speed camera (17) are respectively connected to the data processor (18); The safety protection device comprises explosion-proof glass (19), a protection plate (20) and a pair of protection walls (21), the protection plate (20) is arranged at the other end of the horizontal bottom plate (1), the pair of protection walls (21) are arranged on the two sides of the other end of the horizontal bottom plate (1), and the explosion-proof glass (19) and the high-speed camera (17) are arranged between the horizontal bottom plate (1) and the protection walls (21).

2. The aeroengine case containment test apparatus of claim 1, wherein, The large air chamber (31) is provided with a flange end face (311) at one end, the small air chamber (32) is provided with a threaded through hole (321) at the top, the flange plate (6) comprises a flange base (61), a U-shaped frame (62) in the middle of the flange base (61) and a fixing seat (63) with a threaded mounting hole (631) in the U-shaped frame (62), the threaded mounting hole (631) penetrates the flange base (61), the barrel (7) is provided with external threads at both ends, one end of the large air chamber (31) and one end of the small air chamber (32) are welded together with the air cannon base (2), the large flange end face (311) of the large air chamber (31) is connected with the flange base (61) of the flange plate (6) by bolts, one end of the barrel (7) passes through the threaded mounting hole (631) and is connected with the threaded through hole (321) at the top of the small air chamber (32), and the other end is connected with the piece removing device (8) by threads.

3. The aeroengine case containment test apparatus of claim 1, wherein, The piece removing device (8) is a cylindrical body with an open end, an internal thread is arranged in the cylindrical body, and a first through hole (81) is formed in the middle of the bottom.

4. The aeroengine case containment test apparatus of claim 1, wherein, The part tray (9) is a hollow cylindrical body, a second through hole (91) is formed in the middle of the bottom, and a groove is formed in the top.

5. The aeroengine case containment test apparatus of claim 1, wherein, The pair of infrared point sensor supports (11) are symmetrically arranged on both sides of the barrel (7), the infrared point sensor support (11) is fixed on the horizontal bottom plate (1) by screws at the bottom, the barrel (7) is symmetrically provided with an air outlet (71), and the sensor mounting through hole (1122) is aligned with the air outlet (71) on the barrel (7).

6. The aeroengine case containment test apparatus of claim 1, wherein, A pair of handles (72) are arranged on the barrel (7).

7. The aeroengine case containment test apparatus of claim 1, wherein, The air cannon base (2), the barrel support (10), the double-port fixing tool (12), the explosion-proof glass (19) and the protective plate (20) are connected with the horizontal bottom plate (1) by bolts.

Images