Simulation device for dynamic failure test of aero-engine

Abstract

The invention discloses an aero-engine power failure test simulation device, and belongs to the technical field of aero-engine tests. The device comprises an aero-engine, a dynamometer, a first coupler and a power failure device, the power failure device comprises an input shaft seat assembly, an output shaft seat assembly, a device base, a second coupler and a feeding tool rest assembly, and the input shaft seat assembly and the output shaft seat assembly are arranged on the device base side by side at intervals; the feeding tool rest assembly is arranged on the device base and located between the input shaft seat assembly and the output shaft seat assembly. The second coupler is rotationally assembled in the feeding tool rest assembly. Compared with the prior art, the device has the following beneficial effects that the feeding tool rest assembly is introduced, so that mechanical rotation between the aero-engine and the dynamometer is cut off by cutting off a coupler, the engine suddenly loses power to cause flying rotation of a power turbine at the moment of cutting off transmission, and the power turbine is prevented from rotating. Simulation of the power failure condition of the aero-engine is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine testing, and in particular to an aero-engine power failure test simulation device. Background Art

[0002] The aircraft engine power failure test is an important assessment test in the engine development stage. This test is used to evaluate the response and safety of aircraft engines when they suddenly lose power. The power failure test usually simulates the following scenarios: for example, when the propeller or turbofan of an aircraft suddenly detaches or breaks during flight, or when other system failures cause the engine power to suddenly disappear, how the engine responds to such drastic changes. This is to assess whether the overspeed protection function of the engine digital control system is normal, or to create a real environment for the overspeed shedding load of the power turbine blades.

[0003] However, existing aircraft engine power failure test equipment cannot simulate the situation where the engine's power turbine spins wildly due to a sudden loss of load. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft engine power failure test simulation device, which disconnects the mechanical rotation between the engine and the dynamometer by cutting off the coupling. At the moment of transmission disconnection, the engine will experience a power turbine runaway due to the sudden loss of load, thereby solving at least one technical problem involved in the background technology.

[0005] In order to solve the above-mentioned technical problems, the present invention is achieved as follows:

[0006] The present invention provides an aircraft engine power failure test simulation device, comprising an aircraft engine, a dynamometer, a first coupling and a power failure device arranged between the aircraft engine and the dynamometer, wherein the power failure device comprises an input shaft seat assembly, an output shaft seat assembly, a device base, a second coupling and a feed tool holder assembly, wherein the input shaft seat assembly and the output shaft seat assembly are arranged in parallel and spaced relation on the device base, and the input shaft seat assembly comprises an input shaft connected to the aircraft engine at one end through the first coupling, and the output shaft seat assembly comprises an output shaft connected to the dynamometer at one end through the first coupling; the feed tool holder assembly is arranged on the device base and is located between the input shaft seat assembly and the output shaft seat assembly; the second coupling is rotatably assembled in the feed tool holder assembly, and the two ends of the second coupling are respectively connected to the other end of the input shaft and the other end of the output shaft.

[0007] Optionally, the power disabling device further comprises a first adjustment pad disposed between the input shaft seat assembly and the device base and between the output shaft seat assembly and the device base.

[0008] Optionally, the feed tool holder assembly is fixed to the device base via a tool holder assembly mounting seat.

[0009] Optionally, the feed tool holder assembly includes a damping ring device, a third coupling, a stepper motor and a tool, the number of the damping ring devices is two, and they are arranged in parallel and spaced relation on the tool holder assembly mounting seat; the two ends of the second coupling respectively pass through the two damping ring devices to respectively connect the input shaft and the output shaft; the stepper motor is connected to the tool through the third coupling to drive the tool to cut the second coupling.

[0010] Optionally, the damping ring device includes a damping ring support and a damping ring embedded in the damping ring support and sleeved on the second coupling.

[0011] Optionally, a gap is set between the damping ring and the second coupling.

[0012] Optionally, the damping ring is provided with a lubrication channel for lubricating the damping ring and the second coupling, and the damping ring support is provided with a lubrication oil pipe joint mounting hole connected to the lubrication channel.

[0013] Optionally, it also includes a lubrication system, which is connected to the lubrication oil pipe joint mounting hole through a lubrication oil pipe.

[0014] Optionally, a reference protrusion is provided on the damping ring support, and the reference protrusion is provided with a radial marking reference surface and an end surface marking reference surface.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] (1) By setting a stepper motor, it is possible to control the stepper motor to reverse and quickly retract the tool when the power fails and the torque measurement value suddenly drops;

[0017] (2) By setting a gap between the damping ring and the second coupling and filling the gap with lubricating oil, the friction between the damping ring and the shaft section of the second coupling is reduced and the friction heat is cooled, and the "shaft-sticking" phenomenon can also be prevented;

[0018] (3) By introducing the feed tool holder assembly, the mechanical rotation between the aircraft engine and the dynamometer is disconnected by cutting off the coupling. At the moment of disconnection of the transmission, the engine will suddenly lose the load and the power turbine will spin fast, thus simulating the power failure of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative work, among which:

[0020] Figure 1 A schematic diagram of the overall structure of the aircraft engine power failure test simulation device provided by the present invention;

[0021] Figure 2 A schematic diagram of the main structure of the power disabling device provided by the present invention;

[0022] Figure 3 A schematic diagram of the top view of the power disabling device provided by the present invention;

[0023] Figure 4 This is a schematic structural diagram of the damping ring device provided by the present invention. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0025] See also Figures 1 to 3 As shown, an embodiment of the present invention provides an aircraft engine power failure test simulation device, including an aircraft engine 1, a dynamometer 2, a first coupling 3, and a power failure device 4 arranged between the aircraft engine 1 and the dynamometer 2. Of course, the device also includes conventional supporting settings such as a lubrication system and a protective cover, which will not be specifically described here.

[0026] The power disabling device 4 includes an input shaft seat assembly 41 , an output shaft seat assembly 42 , a device base 43 , a second coupling 44 and a feed tool holder assembly 45 .

[0027] The input shaft seat assembly 41 and the output shaft seat assembly 42 are arranged in parallel and spaced apart on the device base 43, and the input shaft seat assembly 41 includes an input shaft 411 whose one end is connected to the aircraft engine 1 through the first coupling 3, and the output shaft seat assembly 42 includes an output shaft 421 whose one end is connected to the dynamometer 3 through the first coupling 3.

[0028] The feed tool holder assembly 45 is disposed on the device base 43 and is located between the input shaft seat assembly 41 and the output shaft seat assembly 42 .

[0029] The second coupling 44 is rotatably assembled in the feed tool holder assembly 45 , and two ends of the second coupling 44 are respectively connected to the other end of the input shaft 411 and the other end of the output shaft 421 .

[0030] The power disabling device 4 further includes a first adjustment pad 46 disposed between the input shaft seat assembly 41 and the device base 43 and between the output shaft seat assembly 42 and the device base 43 .

[0031] The feed tool holder assembly 45 is fixed on the device base 43 via a tool holder assembly mounting seat 47 .

[0032] Furthermore, a second adjustment pad 48 is provided between the feed tool holder assembly 45 and the tool holder assembly mounting seat 47 .

[0033] The feed tool holder assembly 45 includes a damping ring device 451 , a third coupling 452 , a stepping motor 453 and a tool 454 .

[0034] There are two damping ring devices 451 , which are arranged in parallel and at intervals on the tool holder assembly mounting seat 47 .

[0035] Two ends of the second coupling 44 pass through the two damping ring devices 451 to respectively connect the input shaft 411 and the output shaft 421 .

[0036] The stepper motor 453 is connected to the cutter 454 through the third coupling 452 to drive the cutter 454 to cut the second coupling 44. By setting the stepper motor 453, it is possible to control the stepper motor 453 to reverse and quickly retract the cutter when power fails and the torque measurement value suddenly drops.

[0037] It should be noted that, by introducing the feed tool holder assembly 45, the mechanical rotation between the aircraft engine 1 and the dynamometer 2 is disconnected by cutting off the coupling. At the moment of disconnection of the transmission, the engine will experience a situation where the power turbine spins rapidly due to sudden power failure, thereby simulating the situation where the aircraft engine power fails.

[0038] Recombination Figure 4 As shown, the damping ring device 451 includes a damping ring support 4511 and a damping ring 4512 embedded in the damping ring support 4511 and sleeved on the second coupling 44 .

[0039] The damping ring 4512 is provided with a lubrication channel 4513 for lubricating the damping ring 4512 and the second coupling 44 , and the damping ring support 4511 is provided with a lubrication oil pipe joint mounting hole 4514 communicating with the lubrication channel 4513 .

[0040] The lubrication system (not shown) is connected to the lubrication oil pipe joint mounting hole 4514 via a lubrication oil pipe.

[0041] A gap is set between the damping ring 4512 and the second coupling 44, and the gap is filled with lubricating oil, which can reduce the friction between the damping ring 4512 and the shaft section of the second coupling 44 and cool the friction heat, and also prevent the "shaft sticking" phenomenon from occurring.

[0042] The damping ring support 4511 is provided with a reference protrusion 4515 , and the reference protrusion 4515 is provided with a radial marking reference surface 4516 and an end surface marking reference surface 4517 .

[0043] The working principle of the aircraft engine power failure test simulation device provided by the embodiment of the present invention is as follows:

[0044] When the engine operation test is carried out, the aircraft engine 1, the power failure device 4 and the dynamometer 2 are all in normal operating state. Under certain conditions, according to the test program instructions, the lubrication system connects the damping ring device 451 and supplies oil to the damping ring 4512 and the tool 454 for lubrication and cooling. At the same time, the stepper motor 453 is controlled to drive the feed tool holder assembly 45 to feed and cut the intermediate shaft section of the second coupling 44 until the shaft section is cut off or the shaft section is sheared off due to excessive torsional shear stress during the cutting process, thereby disconnecting the transmission between the aircraft engine 1 and the dynamometer 2 (load), realizing the simulation function of engine power failure.

[0045] When power failure occurs, the torque measurement value will suddenly drop. After sensing this, the measurement and control system will immediately issue a command to control the stepper motor 453 to reverse and retract the tool quickly.

[0046] It should be noted that, in this article, the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the existence of other identical elements in the process, method, article or device including the element.

[0047] In addition, it should be noted that the scope of the methods and systems in the embodiments of the present invention is not limited to performing functions in the order shown or discussed, and may also include performing functions in a substantially simultaneous manner or in reverse order according to the functions involved. For example, the described methods may be performed in an order different from that described, and various steps may be added, omitted, or combined. In addition, features described with reference to certain examples may be combined in other examples.

[0048] The embodiments of the present invention are described above, but the present invention is not limited to the above-mentioned specific implementation modes. The above-mentioned specific implementation modes are merely illustrative and not restrictive. Under the guidance of the present invention, ordinary technicians in this field can also make many forms without departing from the scope of protection of the purpose of the present invention and the claims, all of which are protected by the present invention.

Claims

1. An aircraft engine power failure test simulation device, characterized in that: It includes an aircraft engine, a dynamometer, a first coupling and a power failure device arranged between the aircraft engine and the dynamometer, the power failure device includes an input shaft seat assembly, an output shaft seat assembly, a device base, a second coupling and a feed tool holder assembly, the input shaft seat assembly and the output shaft seat assembly are arranged in parallel and spaced relation on the device base, and the input shaft seat assembly includes an input shaft connected to the aircraft engine at one end through the first coupling, and the output shaft seat assembly includes an output shaft connected to the dynamometer at one end through the first coupling; the feed tool holder assembly is arranged on the device base and is located between the input shaft seat assembly and the output shaft seat assembly; the second coupling is rotatably assembled in the feed tool holder assembly, and the two ends of the second coupling are respectively connected to the other end of the input shaft and the other end of the output shaft.

2. The aircraft engine power failure test simulation device according to claim 1, characterized in that: The power disabling device also includes a first adjustment pad arranged between the input shaft seat assembly and the device base and between the output shaft seat assembly and the device base.

3. The aircraft engine power failure test simulation device according to claim 1, characterized in that: The feed tool holder assembly is fixed on the device base through a tool holder assembly mounting seat.

4. The aircraft engine power failure test simulation device according to claim 3, characterized in that: A second adjustment pad is provided between the feed tool holder assembly and the tool holder assembly mounting seat.

5. The aircraft engine power failure test simulation device according to claim 3, characterized in that: The feed tool holder assembly includes a damping ring device, a third coupling, a stepper motor and a tool. There are two damping ring devices, which are arranged in parallel and at intervals on the tool holder assembly mounting seat; the two ends of the second coupling respectively pass through the two damping ring devices to respectively connect the input shaft and the output shaft; the stepper motor is connected to the tool through the third coupling to drive the tool to cut the second coupling.

6. The aircraft engine power failure test simulation device according to claim 5, characterized in that: The damping ring device comprises a damping ring support and a damping ring embedded in the damping ring support and sleeved on the second coupling.

7. The aircraft engine power failure test simulation device according to claim 6, characterized in that: A gap is arranged between the damping ring and the second coupling.

8. The aircraft engine power failure test simulation device according to claim 7, characterized in that: The damping ring is provided with a lubrication channel for lubricating the damping ring and the second coupling, and the damping ring support is provided with a lubrication oil pipe joint mounting hole connected with the lubrication channel.

9. The aircraft engine power failure test simulation device according to claim 8, characterized in that: It also includes a lubrication system, which is connected to the lubrication oil pipe joint mounting hole through a lubrication oil pipe.

10. The aircraft engine power failure test simulation device according to claim 6, characterized in that: The damping ring support is provided with a reference protrusion, and the reference protrusion is provided with a radial marking reference surface and an end surface marking reference surface.

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