Testing device for force bearing casing of aero-engine

Abstract

The invention provides a test device for an aero-engine bearing casing, which comprises an annular outer casing, an annular inner casing, a plurality of support plates, a plurality of heating devices and a plurality of cooling devices, and is characterized in that the outer casing is sleeved outside the inner casing, the support plates are connected between the outer casing and the inner casing, the heating devices are respectively arranged at the maximum temperature positions of the corresponding support plates, and the cooling devices are respectively arranged at the maximum temperature positions of the support plates. The heater is used for heating a test piece; the cooling devices are respectively arranged on the corresponding outer casing and the inner casing and are used for cooling the test piece; and a temperature gradient is formed in the force bearing casing through the heating equipment and the cooling equipment. According to the invention, the same temperature field as that in the service process can be applied to the test piece, the loading mode of the radial load of the bearing case is improved, the space of the test device in the bearing case is saved, and convenience is provided for heating and cooling the device. And the difference between the test temperature and the actual service temperature of the aero-engine bearing case is reduced, so that the test result is more reliable.

Description

Technical Field

[0001] The invention relates to the field of aero-engine load-bearing casings, and in particular to a test device for aero-engine load-bearing casings. Background Art

[0002] During the development of aircraft engines, it is necessary to conduct strength and stiffness tests on the load-bearing casing. The main purpose is to verify the strength performance of the load-bearing casing under relevant loads, measure the fulcrum stiffness corresponding to the load-bearing casing, and provide a basis for rotor dynamics analysis.

[0003] During actual service, the load-bearing casing, especially the interstage casing and turbine rear casing at the hot end of the aircraft engine, has a high temperature gradient along the radial direction. However, the temperature effect is often not considered in the load-bearing casing test, or a uniform temperature field is applied, which is quite different from the actual working conditions and may cause a large difference between the test results and the actual situation, rendering the test invalid.

[0004] Therefore, in the load-bearing casing test, in order to ensure the accuracy of the test, it is necessary to apply the same temperature field to the test piece as that during service.

[0005] In view of this, the inventor of the present application has designed a test device for an aircraft engine load-bearing casing in order to overcome the above-mentioned technical problems. Summary of the invention

[0006] The technical problem to be solved by the present invention is to overcome the defect in the prior art that the test temperature in the aircraft engine load-bearing casing test is quite different from the actual service temperature, and to provide a test device for the aircraft engine load-bearing casing.

[0007] The present invention solves the above technical problems through the following technical solutions:

[0008] The present invention provides a test device for an aircraft engine load-bearing casing, which is characterized in that the test device comprises an annular outer casing, an annular inner casing, a plurality of support plates, a plurality of heating devices and a plurality of cooling devices, the outer casing is sleeved on the outside of the inner casing, the support plates are connected between the outer casing and the inner casing, and the heating devices are respectively installed at the maximum temperature of the corresponding support plates to heat the test piece;

[0009] The cooling devices are respectively installed on the corresponding outer casing and the inner casing to cool down the test piece; a temperature gradient is formed in the load-bearing casing through the heating device and the cooling device.

[0010] According to one embodiment of the present invention, the test device further comprises a first transition section, a test bench and a second transition section, wherein one end of the first transition section is connected to the outer casing, and the other end is connected to the test bench;

[0011] One end of the second transition section is connected to the inner casing, and the other end is provided with a simulated loading area, and a radial load is loaded at the simulated loading area.

[0012] According to one embodiment of the present invention, the heating device is a resistance wire for heating, and the cooling device is a cooling tube.

[0013] According to one embodiment of the present invention, the heating device is arranged along the corresponding support plate, and the cooling device is arranged on the outside of the outer casing and the inner wall of the inner casing.

[0014] According to an embodiment of the present invention, the heating device and the cooling device are controlled separately.

[0015] According to one embodiment of the present invention, a plurality of temperature sensors are provided on the load-bearing casing to measure the temperature of the area requiring attention.

[0016] According to one embodiment of the present invention, the test device further comprises a spherical loading device, which is installed in the simulated loading area to apply a radial load to the load-bearing casing.

[0017] According to one embodiment of the present invention, the spherical loading device comprises a loading ball and at least one loading rope, at least one first prefabricated hole is provided on the simulated loading area on the second transition section, and at least one second prefabricated hole is provided on the first transition section;

[0018] The loading ball is connected to one end of the loading cable and is located in the simulated loading area;

[0019] The other end of the loading cable passes through the corresponding first prefabricated hole and the second prefabricated hole in sequence and extends to the outside.

[0020] According to one embodiment of the present invention, the first prefabricated hole and the second prefabricated hole are on the same vertical straight line.

[0021] According to an embodiment of the present invention, the diameter of the first prefabricated hole is smaller than the diameter of the loading ball, and a loading device is used to pull the loading cable, and the loading cable pulls the loading ball to apply a radial load to the test piece.

[0022] According to one embodiment of the present invention, the spherical loading device comprises a loading ball, at least one loading cable, a loading rod and a lever fulcrum, the loading ball is arranged in the simulated loading area, and one end of the loading rod is horizontally inserted into the simulated loading area and contacts the loading ball;

[0023] One end of the lever fulcrum is fixed to the inner wall surface of the test bench, and the other end is connected to the loading rod;

[0024] At least one prefabricated hole is formed on the first transition section, one end of each of the loading cables is connected to the other end of the loading rod, and the other end of each of the loading cables passes through the corresponding prefabricated hole and extends outward.

[0025] The positive and progressive effects of the present invention are:

[0026] The test device for the load-bearing casing of an aircraft engine of the present invention has the following advantages:

[0027] 1. The same temperature field as that in the service process can be applied to the test piece, and at the same time, the loading method of the radial load of the load-bearing casing can be improved, saving the space of the test device inside the load-bearing casing and providing convenience for the heating and cooling devices.

[0028] 2. Reduce the difference between the test temperature of the aircraft engine bearing casing and the actual service temperature to make the test results more reliable.

[0029] 3. Provide a radial load loading method to save test device space. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always represent the same features, wherein:

[0031] Figure 1 The present invention is a front view of a load-bearing casing in a test device for an aircraft engine load-bearing casing.

[0032] Figure 2 The present invention is a cross-sectional view of a load-bearing casing of an aircraft engine in a test device for the load-bearing casing of the present invention.

[0033] Figure 3 The present invention is a schematic diagram of the mechanical test assembly of the load-bearing casing of an aircraft engine in the test device of the load-bearing casing of the present invention.

[0034] Figure 4 The present invention is a schematic diagram of a load-bearing casing heating device in a test device for an aircraft engine load-bearing casing.

[0035] Figure 5 Schematic diagram of the traditional loading method of the test device for the load-bearing casing of an aircraft engine.

[0036] Figure 6 The present invention is a schematic diagram of radial load loading of a test device for an aircraft engine load-bearing casing.

[0037] Figure 7 for Figure 6 Enlarged schematic diagram of part A.

[0038] Figure 8 Another schematic diagram of radial load loading of the test device for the load-bearing casing of an aero-engine of the present invention

[0039] [Reference Signs]

[0040] Bearing Receiver 200

[0041] Outer Receiver 10

[0042] Inner Receiver 20

[0043] Support plate 30

[0044] Outer casing front flange 11

[0045] Outer casing rear flange 12

[0046] Heating equipment 40

[0047] Cooling equipment 50

[0048] First transition section 60

[0049] Test bench 70

[0050] Second transition section 80

[0051] Simulation loading area 81

[0052] Conventional loading rod 90

[0053] Loading ball 100

[0054] Loading cable 110

[0055] The first prefabricated hole 82

[0056] Second prefabricated hole 61

[0057] Prefabricated hole 62

[0058] Loading rod 120

[0059] Lever fulcrum 130 DETAILED DESCRIPTION

[0060] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0061] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to preferred embodiments of the present invention, examples of which are shown in the accompanying drawings. Wherever possible, the same reference numerals will be used throughout the drawings to represent the same or similar parts.

[0062] Furthermore, although the terms used in the present invention are selected from well-known and commonly used terms, some terms mentioned in the present invention specification may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this document.

[0063] Furthermore, it is required that the present invention be understood not only by the actual terms used but also by the meanings connoted by each term.

[0064] like Figure 1 and Figure 2 As shown, the present invention provides a test device for an aircraft engine load-bearing casing, which includes an annular outer casing 10, an annular inner casing 20, a plurality of support plates 30, a plurality of heating devices 40 and a plurality of cooling devices 50. The outer casing 10 is sleeved on the outside of the inner casing 20, and the support plates 30 are connected between the outer casing 10 and the inner casing 20. The heating devices 40 are respectively installed at the maximum temperature of the corresponding support plates 30, and are used to heat the test piece. The cooling devices 50 are respectively installed on the corresponding outer casing 10 and the inner casing 20, and are used to cool the test piece. A temperature gradient is formed in the load-bearing casing 200 by the heating devices 40 and the cooling devices 50. The outer casing 10 is provided with an outer casing front flange 11 and an outer casing rear flange 12.

[0065] like Figure 3 As shown, the test device further includes a first transition section 60, a test bench 70 and a second transition section 80. One end of the first transition section 60 is connected to the outer casing 10, and the other end is connected to the test bench 70. One end of the second transition section 80 is connected to the inner casing 20, and the other end is provided with a simulated loading area 81, and a radial load is loaded at the simulated loading area 81. The load-bearing casing 200 is connected to the first transition section 60 and fixed on the test bench 70. The inner casing 20 of the load-bearing casing 200 is connected to the second transition section 80, and a radial load is loaded at the simulated loading area 81 during the test.

[0066] like Figure 4 As shown, the heating device 40 is arranged along the corresponding support plate 30, and the cooling device 50 is arranged on the outside of the outer casing 10 and the inner wall of the inner casing 20. For example, the heating device 40 here is preferably a resistance wire for heating, and the cooling device 50 is preferably a cooling pipe.

[0067] According to the temperature distribution of the load-bearing casing of the aircraft engine during operation, the temperature at the support plate 30 is relatively high, and the temperature at both sides of the casing (the outer casing 10 and the inner casing 20) is relatively low. In order to simulate the actual temperature distribution state, a heating device 40 is installed at the corresponding maximum temperature on each support plate 30. For example, a resistance wire for heating is used to heat the test piece. A cooling device 50 is installed at the outer casing 10 and the inner casing 20 of the load-bearing casing 200, such as a cooling pipe, to cool the test piece. The purpose of forming a temperature gradient in the load-bearing casing is achieved through the heating device and the cooling device.

[0068] Preferably, the heating device 40 and the cooling device 50 are controlled individually here.

[0069] In order to keep the temperature gradient of the bearing casing at a constant temperature during the test, the temperature needs to be precisely controlled. Therefore, the number of heating and cooling devices can be increased, and each heating device and each cooling device can be controlled separately. For example, the flow rate and flow rate of the coolant in each cooling pipe can be controlled to achieve multi-zone temperature control.

[0070] In addition, multiple temperature sensors (not shown) can be installed on the load-bearing casing to measure the temperature of the area that needs attention. For example, multiple temperature critical areas are selected on the load-bearing casing, and temperature sensors are installed in the critical areas. The temperature critical area here refers to the area where the temperature needs to be paid attention to or the area that has a greater impact on the overall temperature distribution during the test. By monitoring the temperature value, the heating and cooling device system is controlled in real time to achieve the effect of maintaining the temperature gradient.

[0071] like Figure 5 As shown, when the load-bearing casing is loaded with a mechanical load, the axial rod is usually inserted from the inside of the inner casing 20 into the loading area, and then the load is loaded through an actuator and other equipment. A radial load is applied to the test piece through a conventional loading rod 90. However, this loading method occupies more space inside the inner casing, which may affect the layout and regulation of the cooling device. Therefore, the present invention proposes a new radial load loading method, which saves test equipment space, avoids affecting the temperature device, and also facilitates the measurement of temperature data at the inner casing.

[0072] like Figure 6 and Figure 7 As shown, the test device also includes a spherical loading device, which is installed in the simulated loading area 81 to apply a radial load to the load-bearing casing.

[0073] In one embodiment, the spherical loading device includes a loading ball 100 and at least one loading cable 110, at least one first prefabricated hole 82 is provided on the simulated loading area 81 on the second transition section 80, and at least one second prefabricated hole 61 is provided on the first transition section 60. The loading ball 100 is connected to one end of the loading cable 110 and is located in the simulated loading area 81. The other end of the loading cable 110 passes through the corresponding first prefabricated hole 82 and second prefabricated hole 61 in sequence and extends to the outside.

[0074] The first preformed hole 82 and the second preformed hole 61 are preferably arranged on the same vertical straight line.

[0075] The diameter of the first prefabricated hole 82 is smaller than the diameter of the loading ball 100 . The loading device is used to pull the loading cable 110 , and the loading cable 110 pulls the loading ball 100 to apply a radial load to the test piece.

[0076] A radial load is applied to the load-bearing casing by the spherical loading device. The loading cable 110 extends outward through the first prefabricated hole 82 on the simulated loading area 81 on the second transition section 80 and the second prefabricated hole 61 on the first transition section 60 corresponding to the first prefabricated hole 82 in a radial direction. The diameter of the second prefabricated hole 61 is smaller than the diameter of the loading ball 100. The loading cable 110 is pulled by a loading device such as an actuator, and a radial load is applied to the test piece by the loading ball 100 connected to the loading cable 110. In the mechanical test of the load-bearing casing, radial loads in multiple directions may need to be applied separately.

[0077] Therefore, the loading ball 100 can be connected to a plurality of loading cables 110, and a plurality of radially opposite prefabricated holes are provided on the simulated loading area 81 and the first transition section 60. Before the test, all the loading cables 110 are passed through the corresponding prefabricated holes. When loading, the loading cables 110 in the corresponding direction are pulled, and the loading cables 110 in other directions are relaxed, so as to avoid the load-bearing casing from being reloaded and reheated due to loading loads in different directions during the test.

[0078] like Figure 8 As shown, in another embodiment, the spherical loading device includes a loading ball 100, at least one loading cable 110, a loading rod 120 and a lever fulcrum 130. The loading ball 100 is set in the simulated loading area 81, and one end of the loading rod 120 is horizontally inserted into the simulated loading area 81 to contact the loading ball 100. One end of the lever fulcrum 130 is fixed to the inner wall surface of the test bench 70, and the other end is connected to the loading rod 120. At least one prefabricated hole 62 is opened on the first transition section 60, and one end of each loading cable 110 is connected to the other end of the loading rod 120, and the other end of each loading cable 110 extends outward through the corresponding prefabricated hole 62.

[0079] The lever fulcrum 130 is fixed on the test bench 70, and the loading rod 120 is connected to the lever fulcrum 130 and the loading cable 110. The loading cable 110 extends toward the loading device through the prefabricated hole 62 on the first transition section. By applying a load to the loading cable 110, the loading rod 120 indirectly applies a radial load to the simulated loading area 81.

[0080] During the mechanical test of the load-bearing casing, radial loads in multiple directions may need to be applied separately. Therefore, the loading rod 120 can be connected to multiple loading cables 110, and multiple prefabricated holes 62 are set at the corresponding directions of the first transition section. Before the test, all loading cables 110 are passed through the corresponding prefabricated holes. During loading, only the loading cables 110 corresponding to the direction where the radial load needs to be applied are pulled, and the loading cables 110 in other directions are relaxed, so as to avoid the load-bearing casing from being reloaded and reheated due to the loading of loads in different directions during the test.

[0081] In summary, the test device for the load-bearing casing of an aircraft engine of the present invention has the following advantages:

[0082] 1. The same temperature field as that in the service process can be applied to the test piece, and at the same time, the loading method of the radial load of the load-bearing casing can be improved, saving the space of the test device inside the load-bearing casing and providing convenience for the heating and cooling devices.

[0083] 2. Reduce the difference between the test temperature of the aircraft engine bearing casing and the actual service temperature to make the test results more reliable.

[0084] 3. Provide a radial load loading method to save test device space.

[0085] For those skilled in the art, the above invention disclosure is only used as an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary implementation of the present application.

[0086] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0087] Although the specific embodiments of the present invention are described above, it should be understood by those skilled in the art that these are only examples, and the protection scope of the present invention is defined by the appended claims. Those skilled in the art may make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. A test device for an aircraft engine bearing casing, characterized in that: The test device comprises an annular outer casing, an annular inner casing, a plurality of support plates, a plurality of heating devices and a plurality of cooling devices, wherein the outer casing is sleeved on the outside of the inner casing, the support plates are connected between the outer casing and the inner casing, and the heating devices are respectively installed at the maximum temperature of the corresponding support plates to heat the test piece; The cooling devices are respectively installed on the corresponding outer casing and the inner casing to cool down the test piece; a temperature gradient is formed in the load-bearing casing through the heating device and the cooling device.

2. The test device for the load-bearing casing of an aircraft engine as claimed in claim 1, characterized in that: The test device further comprises a first transition section, a test bench and a second transition section, wherein one end of the first transition section is connected to the outer casing, and the other end is connected to the test bench; One end of the second transition section is connected to the inner casing, and the other end is provided with a simulated loading area, and a radial load is loaded at the simulated loading area.

3. The test device for the load-bearing casing of an aircraft engine as claimed in claim 1, characterized in that: The heating device is a resistance wire for heating, and the cooling device is a cooling tube.

4. The test device for the load-bearing casing of an aircraft engine as claimed in claim 1, characterized in that: The heating device is arranged along the corresponding support plate, and the cooling device is arranged on the outside of the outer casing and the inner wall of the inner casing.

5. The test device for the load-bearing casing of an aircraft engine as claimed in claim 1, characterized in that: The heating device and the cooling device are controlled independently.

6. The test device for the load-bearing casing of an aircraft engine as claimed in claim 1, characterized in that: A plurality of temperature sensors are arranged on the load-bearing casing to measure the temperature of the area requiring attention.

7. The test device for the load-bearing casing of an aircraft engine as claimed in claim 2, characterized in that: The test device also includes a spherical loading device, which is installed in the simulated loading area to apply a radial load to the load-bearing casing.

8. The test device for the load-bearing casing of an aircraft engine as claimed in claim 7, characterized in that: The spherical loading device comprises a loading ball and at least one loading rope, at least one first prefabricated hole is provided on the simulated loading area on the second transition section, and at least one second prefabricated hole is provided on the first transition section; The loading ball is connected to one end of the loading cable and is located in the simulated loading area; The other end of the loading cable passes through the corresponding first prefabricated hole and the second prefabricated hole in sequence and extends to the outside.

9. The test device for the load-bearing casing of an aircraft engine as claimed in claim 8, characterized in that: The first prefabricated hole and the second prefabricated hole are on the same vertical straight line.

10. The test device for the load-bearing casing of an aircraft engine according to claim 8, characterized in that: The diameter of the first prefabricated hole is smaller than the diameter of the loading ball. A loading device is used to pull the loading cable, and the loading cable pulls the loading ball to apply a radial load to the test piece.

11. The test device for the load-bearing casing of an aircraft engine according to claim 7, characterized in that: The spherical loading device comprises a loading ball, at least one loading cable, a loading rod and a lever fulcrum, wherein the loading ball is arranged in the simulated loading area, and one end of the loading rod is horizontally inserted into the simulated loading area and contacts the loading ball; One end of the lever fulcrum is fixed to the inner wall surface of the test bench, and the other end is connected to the loading rod; At least one prefabricated hole is formed on the first transition section, one end of each of the loading cables is connected to the other end of the loading rod, and the other end of each of the loading cables passes through the corresponding prefabricated hole and extends outward.

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