Aeroengine fan shaft test device

Abstract

The application relates to an aero-engine fan shaft testing device, which comprises a support body (1), a first loading device (3), a second loading device (4) and a flexible connecting piece (6), the support body (1) is used for supporting a fan shaft (2), the first loading device (3) is used for applying a first acting force to the fan shaft (2), the first acting force is used for simulating an FBO load suffered by the fan shaft (2) in a working state, the second loading device (4) is used for applying a second acting force to the fan shaft (2), the second acting force is used for simulating an axial force suffered by the fan shaft (2) in the working state, and the flexible connecting piece (6) is connected between the second loading device (4) and the fan shaft (2). The flexible connection between the second loading device and the fan shaft can reduce the impact of the FBO load on the second loading device, and the second loading device is effectively protected.

Description

Technical Field

[0001] This invention relates to the field of aero-engine strength testing technology, and in particular to an aero-engine fan shaft testing device. Background Technology

[0002] The fan shaft of an aero-engine is one of the most important force-transmitting components. In accordance with the requirements of structural failure safety levels and civil aero-engine airworthiness regulations, major aero-engine manufacturers design, manufacture, verify, and maintain it as a life-limited component. Its safety directly affects the safe flight of the entire engine and even the aircraft.

[0003] Fan blade out (FBO) testing is one of the most important airworthiness assessment tests for aero-engines. It is characterized by high loads, short time durations, and allows for plastic deformation and even failure of the engine structure, but the engine itself must not fall off. As the primary structure bearing the FBO load (the transient impact load caused by the breakage and detachment of engine fan blades due to bird strikes, hail, or fatigue), strength tests to verify the fan bearing's ability to withstand FBO loads are essential verification tests. Typically, directly applying transient impact loads is the most effective way to verify the structural performance of the fan shaft under FBO load conditions. However, current technologies usually involve testing the fan shaft on compressor components, which is costly in terms of manpower, resources, and funding; performance tests on the fan shaft alone are rarely conducted.

[0004] It should be noted that the information disclosed in the background section of this invention is intended only to enhance the understanding of the overall background of this invention, and should not be construed as an admission or in any way implying that such information constitutes prior art known to those skilled in the art. Summary of the Invention

[0005] This invention provides a test device for aero-engine fan shafts, which can perform individual tests on the performance of fan shafts, saving manpower, material resources and financial resources.

[0006] According to one aspect of the present invention, an aircraft engine fan shaft testing apparatus is provided, comprising:

[0007] Support body, used to support the fan shaft;

[0008] A first loading device is used to apply a first force to the fan shaft, the first force being used to simulate the FBO load on the fan shaft during operation;

[0009] A second loading device is used to apply a second force to the fan shaft, the second force simulating the axial force experienced by the fan shaft during operation; and

[0010] A flexible connector is used to connect the second loading device and the fan shaft.

[0011] In some embodiments, the flexible connector includes a steel wire rope.

[0012] In some embodiments, the aircraft engine fan shaft testing device further includes a first connecting rod and a second connecting rod, the first connecting rod being connected to the drive end of the second loading device, the second connecting rod being connected to the fan shaft, and a flexible connector being connected between the first connecting rod and the second connecting rod.

[0013] In some embodiments, there are two second loading devices, which act on both ends of the fan shaft respectively.

[0014] In some embodiments, the first loading device includes an electromagnetic actuator.

[0015] In some embodiments, the first loading device includes a coil wound around the outer periphery of the fan shaft and electrical conductors disposed on both sides of the fan shaft.

[0016] In some embodiments, the support body includes a support frame, a first bearing, and a second bearing. The first bearing is supported between the support frame and a first fulcrum of the fan shaft, and the second bearing is supported between the support frame and a second fulcrum of the fan shaft.

[0017] In some embodiments, the first bearing is configured to provide radial constraint force to the fan shaft, and the second bearing is configured to provide both radial and axial constraint force to the fan shaft.

[0018] In some embodiments, the first connection stiffness between the support body and the first fulcrum is greater than the second connection stiffness between the first connector and the first fulcrum when the fan shaft is connected to the first fulcrum in the working state, and the third connection stiffness between the support body and the second fulcrum is greater than the fourth connection stiffness between the second connector and the second fulcrum when the fan shaft is connected to the second fulcrum in the working state.

[0019] In some embodiments, the ratio of the first connection stiffness to the third connection stiffness is equal to the ratio of the second connection stiffness to the fourth connection stiffness.

[0020] Based on the above technical solution, the testing device provided in this embodiment of the invention can conduct separate tests on the performance of the fan shaft. Compared with the method of testing the fan shaft by mounting it on the compressor component, it can significantly save manpower, material resources, and financial resources. Moreover, the testing device includes a first loading device and a second loading device. The first loading device can apply an FBO load to the fan shaft, and the second loading device can apply an axial force load to the fan shaft, thereby making the test closer to the actual stress condition of the fan shaft, and the results obtained after the test are more valuable for reference. In addition, the second loading device and the fan shaft are connected by a flexible connector. After the first loading device applies an FBO load to the fan shaft, the flexible connector can buffer the reaction force caused by the instantaneous failure of the fan shaft test piece on the second loading device, reduce the damage to the second loading device, and protect the second loading device. Attached Figure Description

[0021] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this application, illustrate exemplary embodiments of the invention and, together with their description, serve to explain the invention and do not constitute an undue limitation thereof. In the drawings:

[0022] Figure 1 This is a schematic diagram of one embodiment of the aero-engine fan shaft testing device of the present invention.

[0023] Figure 2 This is a cross-sectional view of a portion of the structure in one embodiment of the aero-engine fan shaft testing device of the present invention.

[0024] In the picture:

[0025] 1. Support body; 2. Fan shaft; 3. First loading device; 31. Coil; 32. Electrical conductor; 4. Second loading device; 5. Protective plate; 6. Flexible connector; 7. First connecting rod; 8. Second connecting rod; 9. Third connecting rod; 10. Fan disc; 11. First bearing; 12. Second bearing; 13. Third bearing; 14. Sleeve; 15. Fourth bearing. Detailed Implementation

[0026] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0027] In the description of this invention, it should be understood that the terms "center," "lateral," "longitudinal," "front," "rear," "left," "right," "upper," "lower," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this invention.

[0028] Research revealed that testing the fan shaft mounted on compressor components is extremely costly in terms of manpower, resources, and finances. Therefore, testing the fan shaft separately could be considered. However, in actual operation, in addition to the FBO load, the fan shaft is also subjected to an axial force of equal magnitude. Therefore, if testing the fan shaft separately is chosen, the axial force it experiences must also be considered.

[0029] The FBO load is characterized by its short application time and large load capacity, and can be equivalent to a large number of impact loads. Currently, the commonly used method for applying impact loads is to use a drop hammer or vibration table excitation, but these methods cannot simultaneously apply the FBO load and a large number of axial forces within a limited space. Moreover, after the FBO load is applied, the instantaneous failure of the test specimen may exert a reaction force on the axial force loading device, thereby causing the axial force loading device to fail.

[0030] Based on the above analysis, a test device for aero-engine fan shaft is provided.

[0031] like Figure 1 and Figure 2 As shown, in some embodiments of the aero-engine fan shaft testing device provided by the present invention, the testing device includes a support body 1, a first loading device 3, a second loading device 4, and a flexible connector 6. The support body 1 is used to support the fan shaft 2. The first loading device 3 is used to apply a first force to the fan shaft 2. The first force is used to simulate the FBO load on the fan shaft 2 under working conditions. The second loading device 4 is used to apply a second force to the fan shaft 2. The second force is used to simulate the axial force on the fan shaft 2 under working conditions. The flexible connector 6 connects the second loading device 4 and the fan shaft 2.

[0032] The test apparatus provided in the above embodiments can test the performance of the fan shaft 2 separately, which can significantly save manpower, material resources and financial resources compared to the solution of installing the fan shaft on the compressor component for testing.

[0033] Moreover, the test apparatus includes a first loading device 3 and a second loading device 4. The first loading device 3 can apply an FBO load to the fan shaft 2, and the second loading device 4 can apply an axial force load to the fan shaft 2, so that the test is closer to the actual stress condition of the fan shaft 2, and the results obtained after the test are more valuable for reference.

[0034] In addition, the second loading device 4 and the fan shaft 2 are connected by a flexible connector 6. After the first loading device 3 applies the FBO load to the fan shaft 2, the flexible connector 6 can buffer the reaction force caused by the instantaneous failure of the fan shaft test piece on the second loading device 4, reduce the damage to the second loading device 4, and protect the second loading device 4.

[0035] The test apparatus provided in this embodiment of the invention can apply FBO load while applying axial force, and can protect the safety of the second loading device after the test piece suddenly fails, making it a relatively safe test apparatus.

[0036] In some embodiments, the flexible connector 6 includes a steel wire rope. In other embodiments, the flexible connector 6 may also be a nylon rope of sufficient strength or an elastic connector, etc.

[0037] In some embodiments, the test apparatus further includes a first connecting rod 7 and a second connecting rod 8, the first connecting rod 7 being connected to the drive end of the second loading device 4, the second connecting rod 8 being connected to the fan shaft 2, and a flexible connector 6 being connected between the first connecting rod 7 and the second connecting rod 8.

[0038] By setting the first connecting rod 7 and the second connecting rod 8, it is convenient to connect with the second loading device 4 and the fan shaft 2.

[0039] In some embodiments, there are two second loading devices 4, which act on both ends of the fan shaft 2 respectively.

[0040] By setting two second loading devices 4, axial forces can be applied to both ends of the fan shaft 2 respectively, thereby more realistically simulating the situation where both ends of the fan shaft 2 are subjected to axial forces in actual operation, making the test conditions closer to the real working conditions, and improving the accuracy of the test results.

[0041] In some embodiments, the first loading device 3 includes an electromagnetic actuator.

[0042] Electromagnetic actuators can meet the requirements of short load application time and large load in FBO, and compared with drop hammers, they have better controllability and a significant advantage in applying instantaneous loads. Compared with vibration table excitation, electromagnetic actuators do not produce much vibration, which can reduce the impact on the force-applying components and the surrounding environment.

[0043] In some embodiments, the first loading device 3 includes a coil 31 wound around the outer periphery of the fan shaft 2 and electrical conductors 32 disposed on both sides of the fan shaft 2. When the electrical conductors 32 are connected to direct current, a magnetic field is generated. Then, current is connected to the excitation coil 31. The excitation coil 31 and the electrical conductors 32 cooperate to generate an electromagnetic force, which acts on the fan shaft 2 to simulate the FBO load.

[0044] In some embodiments, the support body 1 includes a support frame, a first bearing 11 and a second bearing 12, the first bearing 11 being supported between the support frame and a first fulcrum of the fan shaft 2, and the second bearing 12 being supported between the support frame and a second fulcrum of the fan shaft 2.

[0045] By setting the first bearing 11 and the second bearing 12, the support from the casing that the fan shaft 2 receives when it is installed on the compressor component can be simulated.

[0046] In some embodiments, the first bearing 11 is configured to provide radial constraint force to the fan shaft 2, and the second bearing 12 is configured to provide both radial and axial constraint force to the fan shaft 2. This arrangement allows the support experienced by the fan shaft 2 to more closely resemble the support it receives when mounted on a compressor component.

[0047] In some embodiments, the first connection stiffness between the support body 1 and the first fulcrum is greater than the second connection stiffness between the first connector and the first fulcrum when the fan shaft 2 is connected to the first fulcrum in the working state, and the third connection stiffness between the support body 1 and the second fulcrum is greater than the fourth connection stiffness between the second connector and the second fulcrum when the fan shaft 2 is connected to the second fulcrum in the working state.

[0048] Generally, to more closely approximate real-world conditions, the first connection stiffness should be set to be equal to the second connection stiffness, and the third connection stiffness should be set to be equal to the fourth connection stiffness. However, due to the large FBO load, the deformation at the first and second support points of the fan shaft 2 may be significant after being subjected to the FBO load, potentially even leading to failure before the fan shaft 2 itself. If the connection at the first and second support points fails before the fan shaft 2, it will affect the test of the load capacity of the fan shaft 2. Therefore, setting the first connection stiffness to be greater than the second connection stiffness and the third connection stiffness to be greater than the fourth connection stiffness can prevent the connection at the first and second support points from failing before the fan shaft 2, effectively ensuring that the test of the load capacity of the fan shaft 2 can be carried out smoothly and improving the reliability of the test.

[0049] In some embodiments, the ratio of the first connection stiffness to the third connection stiffness is equal to the ratio of the second connection stiffness to the fourth connection stiffness. This arrangement ensures that the stress distribution on the fan shaft 2 is consistent with the actual stress distribution during operation, which not only more closely approximates the real stress conditions but also guarantees sufficient connection strength between the first and second support points, preventing the connection at the first and second support points from failing before the fan shaft 2 under FBO load.

[0050] The following is in conjunction with the appendix Figure 1 and 2 The structure and operation of one embodiment of the aero-engine fan shaft testing device of the present invention will be described below:

[0051] like Figure 1 As shown, the test apparatus includes a support body 1 for supporting the fan shaft 2, a first loading device 3, a second loading device 4, and a protective plate 5.

[0052] like Figure 2 As shown, the first loading device 3 includes a coil 31 and an electrical conductor 32. There are two second loading devices 4. One second loading device 4 is drivenly connected to the first connecting rod 7. The first connecting rod 7 and the second connecting rod 8 are connected via a flexible connector 6. The second connecting rod 8 is connected to a sleeve 14 via a third bearing 13. The sleeve 14 is threadedly connected to the front end of the fan disc 10, and the first end of the fan shaft 2 is mounted on the fan disc 10. The other second loading device 4 is drivenly connected to the third connecting rod 9. The third connecting rod 9 is connected to the second end of the fan shaft 2 via a fourth bearing 15. The two second loading devices 4 apply axial forces in opposite directions to the fan shaft 2 at both ends. The second loading devices can be servo actuators. The third bearing 13 and the fourth bearing 15 can be thrust bearings.

[0053] A coil 31 is wound around the outer periphery of the fan disc 10, and two electrical conductors 32 are positioned opposite each other on both sides of the fan disc 10. The fan shaft 2 has a first fulcrum and a second fulcrum. The first fulcrum is closer to the first end of the fan shaft 2 in the axial direction, and the second fulcrum is closer to the second end of the fan shaft 2 in the axial direction. The first fulcrum is supported by a first bearing 11, and the second fulcrum is supported by a second bearing 12, simulating the support of the fan shaft 2 by the casing when the fan shaft 2 is mounted on the compressor component. The first bearing 11 can be a roller bearing to provide radial restraint; the second bearing 12 can be a ball bearing to provide both radial and axial restraint.

[0054] The protective plate 5 has a through hole, through which the second connecting rod 8 passes. The protective plate 5 is vertically installed on the side of the first loading device 3, which can protect the second loading device 4 and the operator of the second loading device 4, and prevent the second loading device 4 and the operator from being impacted by the first loading device 3. When the first loading device 3 uses an electromagnetic actuator, it can also prevent magnetic field radiation from harming the operator.

[0055] When testing the fan shaft 2, firstly, the axial loading forces F2 and F3 of the two second loading devices 4 are applied to the fan shaft 2. After the axial load is kept stable, the current of the coil 31 and the conductor 32 is turned on, and the FBO load F1 is applied instantaneously.

[0056] At the instant the FBO transient impact load is applied, although the fan shaft 2 undergoes significant lateral deformation, the second loading device 4 is connected to the fan shaft 2 via the flexible connector 6, which reduces the constraint reaction force of the FBO transient impact load on the second loading device 4. Simultaneously, the second loading device 4 uses a large-range actuator, ensuring that it will not be damaged due to the load significantly exceeding its range at the instant the reaction force is applied, thus protecting the actuator from damage. Furthermore, the flexible connection ensures that the lateral constraint interference of the three connecting rods is reduced during large deformation of the fan shaft 2, maintaining the unchanged stress pattern of the test piece and preventing changes in the failure mode due to the lateral constraint of the connecting rods.

[0057] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications can still be made to the specific implementation of the present invention or equivalent substitutions can still be made to some technical features without departing from the principle of the present invention, and such modifications and equivalent substitutions should all be covered within the scope of the technical solutions claimed in the present invention.

Claims

1. An aircraft engine fan shaft test apparatus, characterized by, The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device.

2. The aeroengine fan shaft test apparatus of claim 1, wherein, The application relates to a fan shaft loading test device.

3. The aeroengine fan shaft test apparatus of claim 1, wherein, The application relates to a fan shaft loading test device.

4. The aeroengine fan shaft test apparatus of claim 1, wherein, The application relates to a fan shaft loading test device.

5. The aeroengine fan shaft test apparatus of claim 1, wherein, The application relates to a fan shaft loading test device.

6. The aeroengine fan shaft test apparatus of claim 1, wherein, The application relates to a fan shaft loading test device.

7. The aeroengine fan shaft test apparatus of claim 1, wherein, The application relates to a fan shaft loading test device.

8. The aeroengine fan shaft test apparatus of claim 1, wherein, The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. The application relates to a fan shaft loading test device. 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