Aero-engine fuel cut-off test device

Abstract

The invention discloses an aero-engine fuel cut-off test device, which comprises a lubricating oil tank, an oil supply pipe, an intermittent oil supply device, a complete fuel cut-off device, a speed change device and an air supply pipe, and is characterized in that the oil supply pipe is communicated with the lubricating oil tank, and two spaced mounting bases are integrally formed on the outer wall of the oil supply pipe; the intermittent oil supply device and the complete oil cut-off device are sequentially arranged on the two mounting bases at intervals in the oil supply direction; the two ends of an output shaft of the speed change device are connected with and drive the intermittent oil supply device and the complete oil cut-off device respectively. One end of the air supply pipe is communicated with the mounting base corresponding to the intermittent oil supply device, an elastic sealing valve is arranged at the communication position, the other end of the air supply pipe is communicated with the top of the lubricating oil tank, and when the intermittent oil supply device blocks the oil supply pipe, the elastic sealing valve is triggered, so that air in the lubricating oil tank enters a pipeline of the oil supply pipe. According to the invention, the continuous dynamic process of fuel cut-off of the lubricating system of the aero-engine is completely reproduced, so that the test data is more accurate.

Description

Technical Field

[0001] The present application relates to the technical field of aviation engine testing, and in particular to an aviation engine fuel cut-off test device. Background Art

[0002] The reliability of aircraft engine lubrication systems directly affects flight safety, and the simulation of oil-out failures under complex operating conditions is a key step in ground testing.

[0003] In the existing technology, oil cut-off test equipment mostly adopts a static oil cut-off mode, which completely cuts off the lubricating oil pipeline through only a single valve or plug. This simple switching method from oil flow to complete oil cut-off can only simulate a single scenario of instantaneous complete oil cut-off, such as extreme sudden failures such as sudden pipeline rigid fracture, pump body failure, and bird strike.

[0004] However, the engine fuel cut-off scenarios in actual flight are dynamic, diverse, and complex, and the existing fuel cut-off methods cannot reproduce the dynamic failure process in actual flight.

[0005] For example, when the aircraft is in a rollover or tilted flight posture, the lubrication system often suffers from insufficient oil supply and suction due to the tilted liquid level in the oil tank, mixing the air in the expansion chamber of the oil tank into the suction to form a gas-liquid mixed lubrication medium. This type of fault has dynamic characteristics ranging from intermittent oil supply to air replenishment interference, and the existing oil cut-off method lacks a corresponding simulation structure.

[0006] In addition, for the engine's continuous failure chain, from oil leakage due to pipe cracks (accompanied by air intake) to complete oil cut-off, and then to air intake again after switching to the backup pipe (i.e., re-inhalation and air inclusion phenomenon), the existing static oil cut-off method cannot achieve multi-stage dynamic simulation, resulting in the test data being difficult to reflect the engine performance degradation law under real failures. Summary of the Invention

[0007] The present application aims to solve at least one of the technical problems in the above-mentioned technology to a certain extent.

[0008] To achieve the above-mentioned purpose, the first aspect of the present application proposes an aircraft engine oil cut-off test device, comprising: a lubricating oil tank, an oil supply pipe, an intermittent oil supply device, a complete oil cut-off device, a speed change device and an air supply pipe, wherein one end of the oil supply pipe is connected to the lubricating oil tank, and the other end is connected to the lubrication system of the aircraft engine to be tested, and the outer wall of the oil supply pipe is integrally formed with two spaced mounting bases; the intermittent oil supply device and the complete oil cut-off device are sequentially arranged on the two mounting bases at intervals along the oil supply direction; the two ends of the output shaft of the speed change device are respectively connected to and drive the intermittent oil supply device and the complete oil cut-off device; wherein, after the speed reaches a threshold value, the speed change device The complete oil cut-off device is driven to seal the oil supply pipe. The intermittent oil supply device includes a reciprocating structure and a first cylinder, wherein the input end of the reciprocating structure is connected to the output shaft of the speed change device; the first cylinder is pivotally connected to the reciprocating end of the reciprocating structure, and is slidably sealed and arranged on the mounting base to intermittently seal the oil supply pipe; one end of the air supply pipe is connected to the mounting base corresponding to the intermittent oil supply device, and an elastic sealing valve is provided at the connection point, and the other end is connected to the top of the lubricating oil tank, wherein when the first cylinder seals the oil supply pipe, the elastic sealing valve is triggered to allow the air in the lubricating oil tank to enter the pipeline of the oil supply pipe.

[0009] In addition, the aircraft engine fuel cut-off test device proposed in the present application may also have the following additional technical features:

[0010] As a further description of the above technical solution: the complete oil cut-off device includes a centrifugal pendulum structure and a second cylinder with a reset function, wherein the second cylinder is slidably sealed and arranged on the corresponding mounting base; the rotating end of the centrifugal pendulum structure is connected to the output shaft of the speed change device, so that after the rotation speed of the centrifugal pendulum structure exceeds the threshold, the knocking end of the centrifugal pendulum structure is thrown out and knocks on the second cylinder due to centrifugal action, so as to press the second cylinder into and seal the oil supply pipe; wherein the second cylinder is provided with an extrusion spring connected to the mounting seat, so as to keep the second cylinder away from the oil supply pipe when the rotation speed of the centrifugal pendulum structure does not exceed the threshold.

[0011] As a further description of the above technical solution: the centrifugal pendulum structure includes a second turntable, a pendulum rod and a tension spring, wherein the second turntable is connected to the output shaft of the speed change device; multiple pendulum rods are pivoted at equal angles along the center of the second turntable; the middle part of each pendulum rod is connected to the second turntable through a tension spring.

[0012] As a further description of the above technical solution: the reciprocating structure includes a first turntable and a pivot rod, wherein the first turntable is connected to the output shaft of the speed change device; one end of the pivot rod is eccentrically and pivotally set on the first turntable, and the other end is pivotally connected to the first cylinder.

[0013] As a further description of the above technical solution: the speed change device includes a driving structure, a tapered roller, a moving structure and a roller, wherein the two tapered rollers are arranged in parallel in a mirror-like manner; the output end of the driving structure is connected to one of the tapered rollers; the intermittent oil supply device and the complete oil cut-off device are respectively connected to the two ends of the other tapered roller; the moving structure is arranged between the two tapered rollers; the roller is rotatably arranged on the moving end of the moving structure, and the two sides of the roller are respectively in contact with the two tapered rollers.

[0014] As a further description of the above technical solution: the driving structure includes a first driving motor and a meshing gear set, wherein the gear set includes two meshing gears, and one of the gears is coaxially connected to the conical roller, and the other gear is connected to the output end of the first driving motor.

[0015] As a further description of the above technical solution: the moving structure includes a second drive motor, a bidirectional lead screw and a lead screw slider, wherein the bidirectional lead screw is arranged between the two conical rollers and is connected to the output end of the second drive motor; the lead screw slider is arranged on the bidirectional lead screw; the roller is rotatably arranged on the lead screw slider through a bearing.

[0016] As a further description of the above technical solution: the mounting base includes a thickened portion, a cylinder and an extension portion, wherein the thickened portion is integrally formed on the outer wall of the oil supply pipe; the cylinder and the extension portion are respectively arranged at two ends of the thickened portion and are connected to the thickened portion respectively; wherein the first cylinder or the second cylinder can be respectively slidably sealed in the corresponding cylinder.

[0017] As a further description of the above technical solution: the elastic sealing valve includes a retaining ring, a baffle, a bracket, a column rod and a connecting spring, wherein the retaining ring is arranged at the air outlet end of the air supply pipe; the bracket is arranged in the air supply pipe; the column rod is movably arranged in the center of the bracket; the baffle is arranged on the side of the column rod close to the retaining ring; the connecting spring is sleeved on the column rod and connects the baffle and the bracket to abut the baffle against the retaining ring to achieve sealing of the air supply pipe; wherein the outer ring size of the baffle is larger than the inner ring size of the retaining ring, and smaller than the outer ring size of the retaining ring.

[0018] As a further description of the above technical solution: a trigger head is provided on the side of the first cylinder close to the extension part. When the first cylinder blocks the oil supply pipe, the trigger head presses down the baffle; the first cylinder is away from the oil inlet end and has an inward contraction part at the corner close to the extension part to form an air circulation channel.

[0019] The aircraft engine fuel cut-off test device according to the present application has the following beneficial effects:

[0020] (1) The intermittent oil supply device is driven at low speed by the speed change device, and the intermittent oil supply device is coordinated with the air supply pipe to simulate the scene of intermittent insufficient suction of lubricating oil and mixing with air under working conditions such as aircraft rollover.

[0021] (2) The complete oil cut-off device is triggered at high speed by the speed change device to simulate the complete interruption of oil supply caused by sudden impacts such as bird strikes and pipeline ruptures.

[0022] (3) The speed change device is used to first reduce the speed and start the intermittent oil supply device to simulate the intermittent air inhalation after oil leakage, and then the speed is increased to trigger the complete oil cut-off device, simulating the oil leakage to worsen until it is completely cut off. Finally, the speed is reduced to restore the intermittent oil supply device, simulating the re-inhalation of air after switching to the backup pipeline, and completely reproducing the continuous dynamic process of the aircraft engine lubrication system "intermittent-complete oil cut-re-inhalation of air", so that the test data can reflect the engine performance degradation law under real faults.

[0023] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0025] Figure 1 This is a schematic structural diagram of an aircraft engine fuel cut-off test device according to one embodiment of the present application;

[0026] Figure 2 is a structural schematic diagram of an aircraft engine fuel cut-off test device according to another embodiment of the present application;

[0027] Figure 3 is a structural schematic diagram of an aircraft engine fuel cut-off test device according to another embodiment of the present application;

[0028] Figure 4 is a schematic structural diagram of a speed change device according to an embodiment of the present application;

[0029] Figure 5 is a schematic structural diagram of a speed change device according to another embodiment of the present application;

[0030] Figure 6 This is a schematic diagram of the internal structure of the first cylinder and the mounting base according to one embodiment of the present application;

[0031] Figure 7 is an enlarged structural schematic diagram of a part A according to an embodiment of the present application;

[0032] Figure 8 is an enlarged structural schematic diagram of a part A according to another embodiment of the present application;

[0033] Figure 9 is a schematic diagram of the internal structure of the second cylinder and the mounting base according to one embodiment of the present application;

[0034] As shown in the figure:

[0035] 100, oil tank; 200, oil supply pipe; 201, mounting base; 2011, thickened portion; 2012, cylinder; 2013, extension portion; 300, intermittent oil supply device; 310, reciprocating structure; 311, first turntable; 312, pivot rod; 320, first cylinder; 321, contraction portion; 322, trigger head; 400, complete oil cut-off device; 410, centrifugal pendulum structure; 411, second turntable; 412, pendulum rod; 413, tension spring; 420, Second cylinder; 421, extrusion spring; 500, speed change device; 510, drive structure; 511, first drive motor; 512, gear set; 520, tapered roller; 530, moving structure; 531, second drive motor; 532, bidirectional lead screw; 533, lead screw slider; 540, roller; 600, air supply pipe; 601, elastic sealing valve; 6011, retaining ring; 6012, baffle; 6013, bracket; 6014, column rod; 6015, connecting spring. DETAILED DESCRIPTION

[0036] The following describes in detail embodiments of the present application, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present application, and should not be construed as limiting the present application.

[0037] The following describes an aircraft engine fuel cut-off test device according to an embodiment of the present application with reference to the accompanying drawings.

[0038] like Figure 1 and Figure 2 As shown, the aircraft engine oil cut-off test device of the embodiment of the present application may include a lubricating oil tank 100, an oil supply pipe 200, an intermittent oil supply device 300, a complete oil cut-off device 400, a speed change device 500 and an air supply pipe 600.

[0039] The oil tank 100 contains a lubricating medium and reserves an air expansion chamber to simulate the gas-liquid coexistence state of the oil tank 100 during actual flight. One end of the oil supply pipe 200 is connected to the oil tank 100 and extends into the lubricating medium, and the other end is connected to the lubrication system of the aircraft engine to be tested.

[0040] It should be noted that, when conducting the test, the aircraft engine to be tested and the lubrication system may be mounted on a test bench, and the pumping structure of the lubrication system may be connected to the oil supply pipe 200 .

[0041] The outer wall of the oil supply pipe 200 is integrally formed with two spaced mounting bases 201. The intermittent oil supply device 300 and the complete oil cut-off device 400 are sequentially arranged on the two mounting bases 201 at intervals along the oil supply direction. The two ends of the output shaft of the speed change device 500 are respectively connected to and drive the intermittent oil supply device 300 and the complete oil cut-off device 400.

[0042] It should be noted that, in order to ensure stable operation of the intermittent oil supply device 300 , the complete oil cut-off device 400 and the speed change device 500 , the speed change device 500 and the mounting base 201 on the oil supply pipe 200 may be mounted on a fixing frame.

[0043] like Figure 2 As shown, the intermittent oil supply device 300 includes a reciprocating structure 310 and a first cylinder 320, wherein the input end of the reciprocating structure 310 is connected to the output shaft of the speed change device 500, the first cylinder 320 is pivotally connected to the reciprocating end of the reciprocating structure 310, and is slidably sealed on the mounting base 201 to intermittently block the oil supply pipe 200.

[0044] One end of the air supply pipe 600 is connected to the mounting base 201 corresponding to the intermittent oil supply device 300, and an elastic sealing valve 601 is provided at the connection point, and the other end is connected to the top of the lubricating oil tank 100. When the first cylinder 320 blocks the oil supply pipe 200, the elastic sealing valve 601 is triggered to allow the air in the lubricating oil tank 100 to enter the pipeline of the oil supply pipe 200 under the dual effects of the pressure change of the expansion chamber in the lubricating oil tank 100 and the pump suction structure of the aircraft engine lubrication system.

[0045] It should be noted that, after the speed of the speed change device 500 reaches a threshold, the speed change device 500 drives the complete oil cut-off device 400 to block the oil supply pipe 200 through the centrifugal effect of the high-speed rotation.

[0046] As a possible scenario, Figure 1 As shown, the complete oil cut-off device 400 includes a centrifugal pendulum structure 410 and a second cylinder 420 with a reset function.

[0047] Among them, the second cylinder 420 is slidably sealed and arranged on the corresponding mounting base 201, and the rotating end of the centrifugal pendulum structure 410 is connected to the output shaft of the speed change device 500, so that after the rotation speed of the centrifugal pendulum structure 410 exceeds the threshold, the multiple knocking ends of the centrifugal pendulum structure 410 are thrown out due to centrifugal action and knock on the second cylinder 420 in sequence, so as to press the second cylinder 420 into and seal the oil supply pipe 200.

[0048] The second cylinder 420 is sleeved with a compression spring 421 connected to the mounting base 201 to keep the second cylinder 420 away from the oil supply pipe 200 when the rotation speed of the centrifugal pendulum structure 410 does not exceed a threshold.

[0049] For example: Under the simulated working conditions where the aircraft rolls over or tilts, causing the oil level in the fuel tank to tilt, and air is mixed into the lubrication system during suction, resulting in insufficient lubricating oil suction, the relevant staff adjusts the speed change device 500 to the low-speed mode, drives the reciprocating structure 310 of the intermittent oil supply device 300 to move, and drives the first cylinder 320 to slide back and forth in the mounting base 201.

[0050] When the first cylinder 320 blocks the oil supply pipe 200, the elastic sealing valve 601 of the air supply pipe 600 is triggered synchronously, and the air in the lubricating oil tank 100 enters the pipeline through the air supply pipe 600, forming a cycle from oil cut-off to air replenishment. When the first cylinder 320 returns to its position and opens the pipeline, the elastic sealing valve 601 automatically closes and restores pure oil supply.

[0051] The "pure oil-gas-liquid mixture-pure oil" state appears alternately in the oil supply pipe 200, accurately reproducing the intermittent suction and air mixing phenomenon of the lubrication system during rollover, realizing the simulation of the gas-liquid mixed lubrication medium entering the engine lubrication system, and can test the engine's performance indicators such as speed stability and bearing temperature changes under cavitation interference.

[0052] It should be noted that, for the simulation of the above-mentioned working conditions, since there is no need to completely cut off the operation of the oil cut-off device 400, it is only necessary to control the speed change device 500 to drive at a low speed. In the case of low-speed driving, the centrifugal pendulum structure 410 does not reach the threshold of the rotation speed, so the striking end of the centrifugal pendulum structure 410 will not be thrown out and strike the second cylinder 420, and the second cylinder 420 will remain away from the oil supply pipe 200 under the action of the extrusion spring 421.

[0053] For example: when simulating the instantaneous complete oil cut-off condition in sudden situations such as bird strikes and pipeline rigidity fractures, the relevant staff quickly upgrades the speed change device 500 to high-speed mode, and its output shaft drives the centrifugal pendulum structure 410 to rotate rapidly. After reaching the speed threshold, the striking end of the centrifugal pendulum structure 410 is thrown out and continuously strikes the second cylinder 420, so that the second cylinder 420 is pressed into the oil supply pipe 200, thereby achieving sealing and completely cutting off the oil supply path.

[0054] The oil supply pipe 200 switches instantly from an oil-passing state to a completely oil-cut-off state, and key parameters such as the engine shutdown process after a sudden oil cut-off and the emergency system startup delay can be tested.

[0055] It should be noted that although the intermittent oil cut-off device is also working when the complete oil cut-off device 400 performs a complete oil cut-off operation, since the complete oil cut-off device 400 blocks the oil supply pipe 200, even the intermittent oil cut-off device in a working state will not affect the effect of the complete oil cut-off.

[0056] For example, when simulating the complete fault chain of the lubrication system, from oil leakage due to cracks in the pipeline (including air intake), to complete oil cut-off, and then to air intake again after switching to the backup pipeline, the relevant staff adjusted the speed change device 500 to a low speed, the intermittent oil supply device 300 worked, the first cylinder 320 reciprocated to block the oil supply pipe 200, and the air supply pipe 600 was replenished with air synchronously, simulating the state of insufficient oil supply caused by cracks in the pipeline.

[0057] Then, the relevant staff raised the speed change device 500 to high speed, triggered the complete oil cut-off device 400, and completely blocked the oil supply pipe 200, simulating the oil supply interruption caused by the expansion of the crack.

[0058] Finally, the relevant staff reduced the speed change device 500 to a low speed, reset the complete oil cut-off device 400, restarted the intermittent oil supply device 300, and replenished air in the air supply pipe 600 to simulate the air inclusion phenomenon after switching to the backup pipeline.

[0059] Through the above-mentioned working condition simulation, this device breaks through the limitations of traditional static fuel cut-off devices and realizes dynamic multi-mode coverage. It can simulate the entire process from intermittent insufficient suction state to complete fuel cut-off state, and then to the re-inhalation and gas-containing state, completely reproducing the complex fuel cut-off scenarios in real flight. Combined with the synchronous collection of multi-dimensional parameters (pressure, flow, temperature, vibration) of the engine lubrication system, it provides a quantitative basis for the anti-fuel cut-off design of the lubrication system.

[0060] To clearly illustrate the above embodiment, in one embodiment of the present application, Figure 4 As shown, the centrifugal pendulum structure 410 includes a second rotating disk 411 , a pendulum rod 412 and a tension spring 413 .

[0061] Among them, the second turntable 411 is connected to the output shaft of the speed change device 500, and multiple pendulum rods 412 are pivoted at equal angles along the center of the second turntable 411. The middle part of each pendulum rod 412 is connected to the second turntable 411 through a tension spring 413.

[0062] It should be noted that when the speed change device 500 is in low-speed mode, the rotational centrifugal force of the second turntable 411 is small and is insufficient to overcome the tension of the tension spring 413. At this time, the pendulum rod 412 is constrained by the tension spring 413 to a position close to the center of the second turntable 411, and the end striking end does not contact the second cylinder 420. The complete oil cut-off device 400 remains in the open state, and the oil supply pipe 200 supplies oil normally.

[0063] When the speed of the speed change device 500 increases and exceeds the threshold, under the action of the centrifugal force of the second turntable 411, the counterweight at the end of the pendulum rod 412 generates an outward inertial force, the tension spring 413 is stretched, the centrifugal force completely overcomes the spring tension, the pendulum rod 412 is thrown outward around the pivot point, and the end striking end quickly hits the second cylinder 420, and the second cylinder 420 is pressed into the oil supply pipe 200 by the impact force, thereby blocking the pipeline. Since the speed is relatively fast at this time, multiple pendulum rods 412 quickly hit the second cylinder 420 in turn, and the second cylinder 420 cannot return to its position, thereby cutting off the oil supply path.

[0064] In one embodiment of the present application, Figure 5 As shown, the reciprocating structure 310 includes a first rotary plate 311 and a pivot rod 312 .

[0065] The first rotating disk 311 is connected to the output shaft of the speed change device 500 . One end of the pivot rod 312 is eccentrically and pivotally disposed on the first rotating disk 311 , and the other end is pivotally connected to the first cylinder 320 .

[0066] It should be noted that when the speed change device 500 is in the low-speed mode, the first turntable 311 rotates synchronously, and one end of its eccentrically arranged pivot rod 312 makes a circular motion around the center of the turntable 311, while the other end is axially constrained by the first cylinder 320 (can only slide along the mounting base 201), thereby forming a reciprocating push on the first cylinder 320.

[0067] When the pivot rod 312 rotates with the first turntable 311 to the side close to the oil supply pipe 200, it pushes the first cylinder 320 to slide along the mounting base 201 toward the center of the pipeline until the flow cross-section of the oil supply pipe 200 is blocked. At this time, the elastic sealing valve 601 of the air supply pipe 600 is triggered, and air enters the oil supply pipe 200.

[0068] When the pivot rod 312 rotates to a side away from the oil supply pipe 200 , the first cylinder 320 is pulled back, the flow section of the oil supply pipe 200 is reopened, the elastic sealing valve 601 is automatically closed, and normal oil supply is restored.

[0069] In one embodiment of the present application, Figure 6 and Figure 9 As shown, the mounting base 201 includes a thickened portion 2011 , a cylinder 2012 and an extension portion 2013 .

[0070] The thickened portion 2011 is integrally formed on the outer wall of the oil supply pipe 200 , and the cylinder 2012 and the extension portion 2013 are respectively arranged at two ends of the thickened portion 2011 and are communicated with the thickened portion 2011 .

[0071] The first cylinder 320 and the second cylinder 420 are respectively slidably and sealedly disposed in the corresponding cylinder 2012 .

[0072] It should be noted that the cylinder 2012 serves as a sliding track for the first cylinder 320 or the second cylinder 420, and its inner wall forms a matching sealing structure (such as a gap seal or a sealing ring auxiliary seal) with the first cylinder 320 or the second cylinder 420, which can not only guide the cylinder to slide stably in the axial direction, but also prevent the lubricating oil from leaking from the gap between the cylinder and the cylinder 2012, thereby ensuring the pressure stability in the oil supply pipe 200; in addition, the length design of the cylinder 2012 is adapted to the sliding stroke of the cylinder, ensuring that the cylinder completely withdraws from the oil supply pipe 200 channel in the non-blocked state without affecting the normal oil supply.

[0073] When the first cylinder 320 or the second cylinder 420 blocks the oil supply pipe 200 , the end of the first cylinder 320 or the second cylinder 420 moves into the extending portion 2013 .

[0074] It should be noted that the second cylinder 420 is acted upon by the restoring force of the extrusion spring 421, and there is a time interval between the strikes of multiple pendulum rods 412. When the complete oil cut-off device 400 is working, the second cylinder 420 tends to retreat before the next pendulum rod 412 strikes. Therefore, the second cylinder 420 retreats in the extension portion 2013. Due to the blocking effect of the extension portion 2013, a gap between the second cylinder 420 and the oil supply pipe 200 can be avoided before the next pendulum rod 412 strikes, thereby preventing lubricating oil from leaking, thereby ensuring the continued stability of the complete oil cut-off state and the accuracy of the extreme fault simulation.

[0075] In one embodiment of the present application, Figure 7 and Figure 8 As shown, the elastic sealing valve 601 includes a retaining ring 6011, a baffle 6012, a bracket 6013, a column rod 6014 and a connecting spring 6015.

[0076] The retaining ring 6011 is arranged at the gas outlet end of the gas supply pipe 600 , and the bracket 6013 is arranged in the gas supply pipe 600 . The bracket 6013 is a non-enclosed structure, and the gas in the gas supply pipe 600 can pass through the bracket 6013 .

[0077] The column rod 6014 is movably set at the center of the bracket 6013, the baffle 6012 is set on the side of the column rod 6014 close to the retaining ring 6011, the connecting spring 6015 is sleeved on the column rod 6014, and connects the baffle 6012 and the bracket 6013 to make the baffle 6012 abut against the retaining ring 6011 to achieve sealing of the air supply pipe 600.

[0078] The outer ring size of the baffle 6012 is larger than the inner ring size of the baffle 6011 and smaller than the outer ring size of the baffle 6011 .

[0079] To clearly illustrate the above embodiment, in one embodiment of the present application, Figure 6 and Figure 7 As shown, a trigger head 322 is provided on one side of the first cylinder 320 close to the extension portion 2013. When the first cylinder 320 blocks the oil supply pipe 200, the trigger head 322 presses down the baffle 6012. The first cylinder 320 is away from the oil inlet end and has an inward contraction portion 321 at the corner close to the extension portion 2013 to form an air circulation channel.

[0080] It should be noted that when the first cylinder 320 does not block the oil supply pipe 200, the trigger head 322 is away from the baffle 6012, and the connecting spring 6015 pushes the baffle 6012 to fit tightly against the retaining ring 6011, and the air supply pipe 600 is in a sealed state to prevent air from entering the oil supply pipe 200 without control.

[0081] When the first cylinder 320 blocks the oil supply pipe 200, the trigger head 322 at its end simultaneously presses down the baffle 6012, so that a gap appears between the baffle 6012 and the retaining ring 6011, and the air supply pipe 600 is connected to the oil supply pipe 200 through the gap of the retaining ring 6011. At this time, the contraction part 321 of the first cylinder 320 forms a channel, so that the air entering from the air supply pipe 600 flows smoothly into the oil supply pipe 200 through the extension part 2013, realizing the dynamic coordination of cutting off oil and replenishing air at the same time.

[0082] When the first cylinder 320 retreats to open the oil supply pipe 200, the trigger head 322 disengages from the baffle 6012, and the connecting spring 6015 returns to push the baffle 6012 to fit the retaining ring 6011, and the air supply pipe 600 is resealed, and air supply stops.

[0083] In one embodiment of the present application, Figures 3 to 5 As shown, the speed change device 500 includes a driving structure 510 , a tapered roller 520 , a moving structure 530 and a roller 540 .

[0084] Among them, the two conical rollers 520 are arranged in parallel in a mirror-like manner, the output end of the driving structure 510 is connected to one of the conical rollers 520, the intermittent oil supply device 300 and the complete oil cut-off device 400 are respectively connected to the two ends of the other conical roller 520, the movable structure 530 is arranged between the two conical rollers 520, and the roller 540 is rotatably arranged on the movable end of the movable structure 530, and the two sides of the roller 540 are respectively in contact with the two conical rollers 520.

[0085] To clearly illustrate the above embodiment, in one embodiment of the present application, the driving structure 510 includes a first driving motor 511 and a meshing gear set 512 .

[0086] The gear set 512 includes two meshing gears, one of which is coaxially connected to the tapered roller 520 , and the other is connected to the output end of the first drive motor 511 .

[0087] To clearly illustrate the previous embodiment, in one embodiment of the present application, the moving structure 530 includes a second driving motor 531 , a bidirectional lead screw 532 and a lead screw slider 533 .

[0088] The bidirectional lead screw 532 is arranged between the two tapered rollers 520 and connected to the output end of the second drive motor 531. The lead screw slider 533 is arranged on the bidirectional lead screw 532. The roller 540 is rotatably arranged on the lead screw slider 533 through a bearing.

[0089] It should be noted that the first drive motor 511 is started, and drives the connected tapered roller 520 to rotate through the gear set 512. The power is transmitted to the other tapered roller 520 through the roller 540, thereby driving the intermittent oil supply device 300 and the complete oil cut-off device 400.

[0090] Based on the test requirements, relevant personnel turned on the second drive motor 531 to drive the bidirectional screw 532 to rotate. The screw slider 533 drove the roller 540 to move axially along the tapered roller 520, changing the contact point diameter ratio to achieve speed regulation. Through the dynamic change of speed, the intermittent oil supply device 300 and the complete oil cut-off device 400 can be coordinated in time, simulating a continuous fault chain.

[0091] In summary, according to the aircraft engine oil cut-off test device of the embodiment of the present application, the intermittent oil supply device 300 is driven at a low speed by the speed change device 500, and cooperates with the air supply pipe 600 to simulate the scene of intermittent insufficient suction of lubricating oil and mixing with air under working conditions such as aircraft rollover; the complete oil cut-off device 400 is triggered at a high speed by the speed change device 500 to simulate the complete interruption of oil supply caused by sudden impacts such as bird strikes and pipeline ruptures; the intermittent oil supply device 300 is first started by slowing down the speed change device 500 to simulate the intermittent inhalation of air after oil leakage, and then the speed is increased to trigger the complete oil cut-off device 400 to simulate the oil leakage aggravating to complete interruption, and finally the intermittent oil supply device 300 is restored by slowing down to simulate the re-inhalation of air after switching to the backup pipeline, so as to completely reproduce the continuous dynamic process of "intermittent-complete oil cut-off-re-inhalation of air" of the lubrication system of the aircraft engine, so that the test data can reflect the engine performance degradation law under real faults.

[0092] In the description of this specification, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features indicated. Therefore, a feature specified as "first" or "second" may explicitly or implicitly include at least one of such features. In the description of this application, "plurality" means at least two, for example, two, three, etc., unless otherwise specifically defined.

[0093] In the description of this specification, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0094] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. An aircraft engine fuel cut-off test device, characterized in that: include: A lubricating oil tank (100), an oil supply pipe (200), an intermittent oil supply device (300), a complete oil cut-off device (400), a speed change device (500) and an air supply pipe (600), wherein: One end of the oil supply pipe (200) is connected to the oil tank (100), and the other end is connected to the lubrication system of the aircraft engine to be tested. The outer wall of the oil supply pipe (200) is integrally formed with two spaced mounting bases (201); The intermittent oil supply device (300) and the complete oil cut-off device (400) are sequentially arranged at intervals on the two mounting bases (201) along the oil supply direction; The two ends of the output shaft of the speed change device (500) are respectively connected to and drive the intermittent oil supply device (300) and the complete oil cut-off device (400), wherein the speed change device (500) drives the complete oil cut-off device (400) to block the oil supply pipe (200) after the speed reaches a threshold value; The intermittent oil supply device (300) comprises a reciprocating structure (310) and a first cylinder (320), wherein the input end of the reciprocating structure (310) is connected to the output shaft of the speed change device (500); the first cylinder (320) is pivotally connected to the reciprocating end of the reciprocating structure (310), and the first cylinder (320) and the mounting base (201) are slidably sealed to intermittently block the oil supply pipe (200); One end of the air supply pipe (600) is connected to the mounting base (201) corresponding to the intermittent oil supply device (300), and an elastic sealing valve (601) is provided at the connection point, and the other end is connected to the top of the lubricating oil tank (100), wherein when the first cylinder (320) blocks the oil supply pipe (200), the elastic sealing valve (601) is triggered to allow the air in the lubricating oil tank (100) to enter the pipeline of the oil supply pipe (200).

2. The aircraft engine fuel cut-off test device according to claim 1, characterized in that: The complete oil cut-off device (400) comprises a centrifugal pendulum structure (410) and a second cylinder (420) with a reset function, wherein: The second cylinder (420) is slidably and sealingly arranged on the corresponding mounting base (201); The rotating end of the centrifugal pendulum structure (410) is connected to the output shaft of the speed change device (500), so that after the rotation speed of the centrifugal pendulum structure (410) reaches a threshold value, the striking end of the centrifugal pendulum structure (410) is thrown out due to centrifugal action and strikes the second cylinder (420), thereby pressing the second cylinder (420) into and sealing the oil supply pipe (200); The second cylinder (420) is sleeved with a compression spring (421) connected to the mounting seat (201) to keep the second cylinder (420) away from the oil supply pipe (200) when the rotation speed of the centrifugal pendulum structure (410) does not exceed a threshold value.

3. The aircraft engine fuel cut-off test device according to claim 2, characterized in that: The centrifugal pendulum structure (410) comprises a second rotating disk (411), a pendulum rod (412) and a tension spring (413), wherein: The second rotating disk (411) is connected to the output shaft of the speed changing device (500); The plurality of pendulum rods (412) are respectively pivotally arranged at equal angles along the center of the second rotating disk (411); The middle portion of each pendulum rod (412) is connected to the second rotating disk (411) via a tension spring (413).

4. The aircraft engine fuel cut-off test device according to claim 1, characterized in that: The reciprocating structure (310) includes a first rotating disk (311) and a pivot rod (312), wherein: The first rotating disk (311) is connected to the output shaft of the speed changing device (500); One end of the pivot rod (312) is eccentrically and pivotally arranged on the first rotating disk (311), and the other end is pivotally connected to the first cylinder (320).

5. The aircraft engine fuel cut-off test device according to claim 1, characterized in that: The speed changing device (500) comprises a driving structure (510), a tapered roller (520), a moving structure (530) and a roller (540), wherein: The two tapered rollers (520) are arranged in parallel in a mirror-image manner; The output end of the driving structure (510) is connected to one of the tapered rollers (520); The intermittent oil supply device (300) and the complete oil cut-off device (400) are respectively connected to two ends of the other tapered roller (520); The moving structure (530) is arranged between the two tapered rollers (520); The roller (540) is rotatably arranged on the movable end of the movable structure (530), and two sides of the roller (540) are respectively in contact with the two tapered rollers (520).

6. The aircraft engine fuel cut-off test device according to claim 5, characterized in that: The driving structure (510) includes a first driving motor (511) and a meshing gear set (512), wherein: The gear set (512) includes two meshing gears, one of which is coaxially connected to the tapered roller (520), and the other is connected to the output end of the first drive motor (511).

7. The aircraft engine fuel cut-off test device according to claim 5, characterized in that: The moving structure (530) includes a second driving motor (531), a bidirectional lead screw (532) and a lead screw slider (533), wherein: The bidirectional lead screw (532) is arranged between the two tapered rollers (520) and is connected to the output end of the second drive motor (531); The lead screw slider (533) is arranged on the bidirectional lead screw (532); The roller (540) is rotatably arranged on the lead screw slider (533) via a bearing.

8. The aircraft engine fuel cut-off test device according to claim 2, characterized in that: The mounting base (201) comprises a thickened portion (2011), a cylinder (2012) and an extension portion (2013), wherein: The thickened portion (2011) is integrally formed on the outer wall of the oil supply pipe (200); The cylinder (2012) and the extension portion (2013) are respectively arranged at two ends of the thickened portion (2011) and are respectively connected to the thickened portion (2011); The first barrel (320) or the second barrel (420) is respectively slidably and sealedly arranged in the corresponding cylinder (2012).

9. The aircraft engine fuel cut-off test device according to claim 8, characterized in that: The elastic sealing valve (601) comprises a retaining ring (6011), a baffle (6012), a bracket (6013), a column rod (6014) and a connecting spring (6015), wherein: The retaining ring (6011) is arranged at the air outlet end of the air supply pipe (600); The bracket (6013) is arranged in the air supply pipe (600); The upright rod (6014) is movably arranged at the center of the bracket (6013); The baffle (6012) is arranged on a side of the upright rod (6014) close to the baffle ring (6011); The connecting spring (6015) is sleeved on the upright rod (6014) and connects the baffle (6012) and the bracket (6013) so as to abut the baffle (6012) against the retaining ring (6011) to achieve sealing of the air supply pipe (600); The outer ring size of the baffle (6012) is larger than the inner ring size of the baffle (6011) and smaller than the outer ring size of the baffle (6011).

10. The aircraft engine fuel cut-off test device according to claim 9, characterized in that: A trigger head (322) is provided on one side of the first cylinder (320) close to the extension portion (2013); when the first cylinder (320) blocks the oil supply pipe (200), the trigger head (322) presses down the baffle (6012); and the first cylinder (320) has an inward contraction portion (321) at a corner away from the oil inlet end and close to the extension portion (203) to form an air circulation channel.

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