Dynamic monitoring device for fatigue cracks of aero-engine high-temperature test bed

Abstract

The invention relates to the technical field of dynamic monitoring, and discloses an aero-engine high-temperature test bed fatigue crack dynamic monitoring device, which comprises a profiling shell, and an eddy current detection sensor, a signal processing module, a wireless communication module and a miniature centrifugal refrigerator which are packaged in the profiling shell, a plurality of micro air film holes are formed in the detection end face of the profiling shell, and the air film holes are matched with the micro centrifugal refrigerator to form a cooling air film on the detection face under the action of centrifugal force. An internal water cooling pipeline and an external air guide channel are arranged on the inner side wall and the outer side wall of the profiling shell correspondingly, and the heat dissipation effect is enhanced in a matched mode. The eddy current detection sensor is formed by winding an insulated wire and a ferrite magnetic core, so that tiny fatigue defects can be effectively detected. According to the invention, the dynamic monitoring of the fatigue crack of the preset monitoring point in the center hole of the test main shaft on the test bed under the high-speed and high-temperature operation environment is effectively realized.

Description

Technical Field

[0001] The invention relates to the technical field of eddy current dynamic monitoring, and in particular to a fatigue crack dynamic monitoring device for a high-temperature test bench of an aero-engine. Background Art

[0002] Aircraft engines are known as the "crown jewel of modern industry", which shows their high status in the industrial field. The working environment of aircraft engines is extremely harsh, and they need to maintain long-term stable operation under conditions of high temperature, high pressure, and high speed. Therefore, when designing and manufacturing a new model of engine, a test bench simulation test is essential before it goes into space. This also includes when fatigue cracks occur in the test spindle of the aircraft engine, the expansion rate of the fatigue crack generation site under different speed loads, temperature pressure and other conditions, as well as how to locate and change it. This is a parameter that engineering and technical personnel must focus on. In the prior art, the patent with application number 202411287234.9 discloses a method for monitoring the fatigue crack growth state of the main shaft of an aircraft engine high-speed test bench, and discloses a detection method that uses an eddy current monitoring device and a test spindle to form asynchronous relative motion to achieve dynamic monitoring of the fatigue crack growth trend of the aircraft engine under high-speed operation. However, in actual test applications, the temperature of the aircraft engine can reach up to 600°C when the aircraft engine is running at high speed. The eddy current sensor composed of coils disclosed in the above patent is difficult to meet the temperature resistance performance, including temperature drift, sensitivity, reliability and other indicators. How to further improve the temperature resistance of eddy current sensors is an urgent problem to be solved. Summary of the invention

[0003] In order to solve the above problems, the present invention provides a dynamic monitoring device for fatigue cracks of an aircraft engine high temperature test bench, which is implemented as follows:

[0004] A dynamic monitoring device for fatigue cracks of an aircraft engine high-temperature test bench is used to form asynchronous relative motion with a test spindle on the test bench under simulated high-speed rotation, and to dynamically monitor a preset monitoring point of the test spindle center hole. The monitoring device includes a contoured housing and an eddy current detection sensor, a signal processing module, a wireless communication module, and a micro centrifugal refrigerator encapsulated inside the contoured housing.

[0005] A plurality of tiny air film holes are provided on the detection end surface of the profiling shell; and an air guide channel is also provided on the outer side wall of the profiling shell adjacent to or opposite to the detection end surface thereof, the air inlet and the air outlet of the air guide channel form a symmetrical double trumpet structure, and the inner wall of the air guide channel is coated with a heat dissipation coating;

[0006] The eddy current detection sensor is arranged at a position close to the detection end surface inside the contoured housing, and comprises a ferrite core and an insulated wire, wherein the insulated wire is wound around the outside of the ferrite core;

[0007] The signal processing module and the wireless communication module are packaged at the rear end of the eddy current detection sensor and are electrically connected to the eddy current detection sensor;

[0008] The micro centrifugal refrigerator includes a coolant storage chamber and a plurality of air flow ducts connected thereto, the other ends of the air flow ducts are respectively connected to corresponding tiny air film holes; a centrifugal opening and closing valve which is automatically opened and closed by centrifugal force is provided at the connection between the air flow duct and the coolant storage chamber.

[0009] Furthermore, the centrifugal opening and closing valve comprises a circular valve body, a rotating valve disc and a sealing ring, wherein the rotating valve disc is arranged in the middle of the circular valve body, and the sealing ring is embedded between the circular valve body and the connecting part;

[0010] When the monitoring device rotates at a high speed, the rotary valve flap is moved and opened under the action of centrifugal force, and the coolant storage chamber and the air flow conduit are communicated with each other.

[0011] Furthermore, a built-in water cooling pipe is provided on the side wall of the contoured shell corresponding to the air guiding channel, and the built-in water cooling pipe is sealed and filled with cooling liquid.

[0012] Furthermore, the shape of the micro air film holes is circular or elliptical.

[0013] Furthermore, the airflow duct is a straight duct or a curved duct.

[0014] Compared with the prior art, the present application can obtain the following technical effects:

[0015] The present invention provides a monitoring device with heat insulation and heat dissipation effects, including a contoured shell and a high-frequency magnetic eddy current detection sensor, a signal processing module, a wireless communication module and a micro centrifugal refrigerator encapsulated inside the contoured shell. The centrifugal force generated by the high-speed rotation of the monitoring device is used to control the opening and closing of the air flow channel of the micro centrifugal refrigerator, supply the coolant and transmit it to the tiny air film holes on the surface of the contoured shell, so as to form an air film with heat insulation effect on the detection end face of the contoured shell. The overall structure is reliable, and the effective operation of the eddy current detection sensor is guaranteed. Through the air guide channel on the outer side of the contoured shell, during the high-speed rotation of the monitoring device, the special air guide channel structure can induce the surrounding air flow to flow quickly in the channel, thereby enhancing the heat dissipation effect. At the same time, the formed circulating air layer also has a heat insulation effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the examples of the present invention or the technical solutions in the prior art or the drawings required for use in the description of the prior art, a brief introduction is given. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0017] Figure 1 Schematic diagram of the relative position of the monitoring device and the test spindle.

[0018] Figure 2 This is a connection diagram of the eddy current detection sensor, signal processing module, and wireless communication module.

[0019] Figure 3 This is a simplified schematic diagram of the internal packaging structure of the monitoring device.

[0020] Figure 4 It is a simple schematic diagram of profiling shell end face detection.

[0021] In the figure:

[0022] 10-Test spindle;

[0023] 20-Guide rail;

[0024] 30-monitoring device, 31-contact shell, 32-detection end face, 33-air film hole, 34-eddy current detection sensor, 35-signal processing module, 36-wireless communication module, 37-micro centrifugal refrigerator, 371-coolant storage chamber, 372-air flow duct, 373-centrifugal opening and closing valve, 38-built-in water cooling pipeline, 39-air guide channel, 391-bell mouth. DETAILED DESCRIPTION

[0025] In order to make the purpose, 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 in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Therefore, the following detailed description of the embodiments of the present invention provided in the drawings is not intended to limit the scope of the claimed invention, but only represents selected embodiments of the present invention.

[0026] The present invention discloses a dynamic monitoring device for fatigue cracks of an aircraft engine high temperature test bench, which is used to form an asynchronous relative motion with a test spindle 10 on the test bench under simulated high-speed rotation, and to perform dynamic monitoring of a preset monitoring point of the center hole of the test spindle 10. A monitoring point can be preset in the center hole of the test spindle 10, a guide rail 20 is coaxially installed in the circumferential direction of the center hole to maintain a fixed distance from the inner surface of the center hole of the test spindle 10, and a monitoring device 30 of the present invention is slidably arranged on the guide rail 20, and the detection surface of the monitoring device 30 is directly opposite to the inner surface of the center hole of the test spindle 10.

[0027] In this embodiment, the monitoring device 30 includes a contoured shell 31 and an eddy current detection sensor 34, a signal processing module 35, a wireless communication module 36, and a micro centrifugal refrigerator 37 encapsulated inside the contoured shell 31; the eddy current detection sensor 34 is installed at a position close to the detection end surface 32 inside the contoured shell 31, the signal processing module 35 and the wireless communication module 36 are encapsulated and arranged at the rear end of the eddy current detection sensor 34, and are electrically connected to the eddy current detection sensor 34, and the micro centrifugal refrigerator 37 is arranged at any position inside the contoured shell 31.

[0028] A plurality of tiny air film holes 33 are provided on the detection end surface 32 of the contoured shell 31; the miniature centrifugal refrigerator 37 includes a coolant storage chamber 371 and a plurality of air flow ducts 372 connected thereto, and the other ends of the air flow ducts 372 are respectively connected to the corresponding tiny air film holes 33; a centrifugal opening and closing valve 373 which is automatically opened and closed by centrifugal force is provided at the connection between the air flow duct 372 and the coolant storage chamber 371.

[0029] In this embodiment, the centrifugal opening and closing valve 373 includes a circular valve body, a rotating valve flap and a sealing ring. The rotating valve flap is arranged in the middle of the circular valve body, and the sealing ring is embedded between the circular valve body and the connection. When the monitoring device 30 rotates at a high speed, the rotating valve flap is moved and opened under the action of centrifugal force, and the coolant storage chamber 371 and the airflow duct 372 are connected to each other.

[0030] During detection, when the monitoring device and the test spindle rotate asynchronously relative to each other, the centrifugal opening and closing valve of the micro centrifugal refrigerator opens under the action of centrifugal force, and squeezes the coolant into the air flow duct. The coolant flows in the air flow duct, and under the action of centrifugal force, the coolant is quickly pushed to the outside of the contoured shell to form a cooling air film, insulate the sensor and cool down the external environment.

[0031] In this embodiment, the eddy current detection sensor 34 includes a ferrite core and an insulated wire, and the insulated wire is wound around the outside of the ferrite core; the insulated wire is a thin insulated wire with high conductivity, low temperature drift and good stability, and the ferrite core has the property that the magnetic permeability does not drift with temperature. The two are wound into a high-frequency magnetic eddy current detection sensor, which can effectively detect tiny fatigue defects on the test spindle.

[0032] Furthermore, an air guide channel 39 is also provided on the outer wall of the contoured shell 31 adjacent to or opposite to its detection end face 32; in the present embodiment, the air inlet and air outlet of the air guide channel 39 form a double trumpet-shaped structure that is symmetrical to each other; in the present embodiment, according to the rotation path of the monitoring device 30, an air inlet and outlet are added in the middle of the air guide channel 39 on the two outer walls adjacent to the detection end face 32 to form multi-directional air guidance.

[0033] At the same time, a heat dissipation coating is applied on the inner wall of the air guide channel 39. The air guide channel 39 with a double bell mouth 391 design can quickly inlet or outlet air from any direction, take away the hot air on the surface of the monitoring device 30, and enhance the heat dissipation effect. At the same time, the formed circulating air layer also has a heat insulation effect. In this embodiment, the heat dissipation coating adopts a porous sweating cooling material, which absorbs moisture or other coolants. When the monitoring device rotates, the surrounding temperature rises, and the moisture or coolant in the material evaporates and absorbs a large amount of heat. The airflow is exchanged through the air guide channel 39 that circulates the inlet and outlet air, thereby improving the heat dissipation effect.

[0034] Furthermore, a built-in water cooling pipe 38 is provided on the side wall of the contoured housing 31 corresponding to the air guide channel 39, and a coolant is sealed and filled in the built-in water cooling pipe 38. The coolant sealed and filled in the built-in water cooling pipe 38 and the external air guide channel 39 cooperate with each other to perform heat exchange inside and outside the contoured housing 31.

[0035] The computational fluid dynamics simulation model is used to design the air film holes 33 and the air flow conduit 372 according to the known rotation speed of the monitoring device to ensure smooth and uniform air flow. In this embodiment, the shape of the micro air film holes is circular or elliptical, and the air flow conduit is a straight conduit or a curved conduit. In other embodiments, irregularly shaped air film holes and air flow conduit structures can also be selected to continuously optimize the cooling effect.

[0036] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A dynamic monitoring device for fatigue cracks of an aircraft engine high temperature test bench, which adopts a detection method in which an eddy current monitoring device and a test spindle form asynchronous relative motion, and is characterized by: The monitoring device includes a contoured housing and an eddy current detection sensor, a signal processing module, a wireless communication module, and a micro centrifugal refrigerator encapsulated inside the contoured housing; A plurality of tiny air film holes are provided on the detection end surface of the profiling shell; and an air guide channel is also provided on the outer side wall of the profiling shell adjacent to or opposite to the detection end surface thereof, the air inlet and the air outlet of the air guide channel form a symmetrical double trumpet structure, and the inner wall of the air guide channel is coated with a heat dissipation coating; The eddy current detection sensor is arranged at a position close to the detection end surface inside the contoured housing, and comprises a ferrite core and an insulated wire, wherein the insulated wire is wound around the outside of the ferrite core; The signal processing module and the wireless communication module are packaged at the rear end of the eddy current detection sensor and are electrically connected to the eddy current detection sensor; The micro centrifugal refrigerator includes a coolant storage chamber and a plurality of air flow ducts connected thereto, the other ends of the air flow ducts are respectively connected to corresponding tiny air film holes; a centrifugal opening and closing valve which is automatically opened and closed by centrifugal force is provided at the connection between the air flow duct and the coolant storage chamber.

2. The device for dynamic monitoring of fatigue cracks of an aircraft engine high temperature test bench according to claim 1, characterized in that: The centrifugal opening and closing valve comprises a circular valve body, a rotating valve disc and a sealing ring, wherein the rotating valve disc is arranged in the middle of the circular valve body, and the sealing ring is embedded between the circular valve body and the connecting part; When the monitoring device rotates at a high speed, the rotary valve flap is moved and opened under the action of centrifugal force, and the coolant storage chamber and the air flow conduit are communicated with each other.

3. The dynamic monitoring device for fatigue cracks of an aircraft engine high temperature test bench according to claim 1, characterized in that: A built-in water cooling pipe is arranged on a side wall of the contoured shell corresponding to the air guiding channel, and the built-in water cooling pipe is sealed and filled with cooling liquid.

4. The device for dynamic monitoring of fatigue cracks of an aircraft engine high temperature test bench according to claim 1, characterized in that: The shape of the micro air film hole is circular or elliptical.

5. The device for dynamic monitoring fatigue cracks of an aircraft engine high temperature test bench according to claim 1, characterized in that: The airflow conduit is a straight conduit or a curved conduit.

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