Test device for aeroengine load casing

Abstract

The application provides a test device for an aero-engine load-bearing casing, which comprises an annular outer casing, an annular inner casing, a plurality of supporting plates, a plurality of heating devices and a plurality of cooling devices. The outer casing is sleeved outside the inner casing, the supporting plates are connected between the outer casing and the inner casing, the heating devices are respectively installed at the maximum temperature positions of the corresponding supporting plates and are used for heating the test piece, and the cooling devices are respectively installed on the corresponding outer casing and inner casing and are used for cooling the test piece. The temperature gradient is formed in the load-bearing casing through the heating devices and the cooling devices. The application can apply the same temperature field to the test piece as in the service process, simultaneously improves the loading mode of the radial load of the load-bearing casing, saves the test device space in the load-bearing casing, provides convenience for the heating and cooling devices, reduces the difference between the test temperature and the actual service temperature of the aero-engine load-bearing casing, and makes the test result more reliable.

Description

Technical Field

[0001] This invention relates to the field of load-bearing casings for aero engines, and particularly to a test apparatus for load-bearing casings for aero engines. Background Technology

[0002] During the development of aero-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 stiffness of the corresponding support points of the load-bearing casing, and provide a basis for rotor dynamics analysis.

[0003] In actual service, load-bearing casings, especially the interstage casings and turbine rear casings located at the hot end of the aero-engine, have a high temperature gradient along the radial direction. However, in load-bearing casing tests, the effect of temperature is often not considered, or a uniform temperature field is applied. This is quite different from the actual operating conditions and may cause a large discrepancy between the test results and the actual situation, resulting in invalid tests.

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

[0005] In view of this, the inventors of this application have designed a test device for a load-bearing casing of an aero-engine 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 that the test temperature and the actual service temperature are greatly different in the test of the load-bearing casing of the aero-engine in the prior art, and to provide a test device for the load-bearing casing of the aero-engine.

[0007] The present invention solves the above-mentioned technical problems through the following technical solution:

[0008] This invention provides a test device for a load-bearing casing of an aero-engine, characterized in that the test device includes an annular outer casing, an annular inner casing, several support plates, several heating devices, and several cooling devices. The outer casing is fitted over 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 for heating the test piece.

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

[0010] According to one embodiment of the present invention, the testing apparatus further includes a first adapter section, a test bench, and a second adapter section, wherein one end of the first adapter 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, where a radial load is applied.

[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 pipe.

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

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

[0015] According to one embodiment of the present invention, the load-bearing casing is provided with a plurality of temperature sensors for measuring the temperature of the area of ​​interest.

[0016] According to one embodiment of the present invention, the test apparatus further includes a spherical loading device 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 includes a loading ball and at least one loading cable, and at least one first pre-formed hole is provided on the simulated loading area on the second transition section, and at least one second pre-formed hole is provided on the first transition section;

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

[0019] The other end of the loading cable passes through the corresponding first pre-drilled hole and the second pre-drilled hole in sequence and extends outward.

[0020] According to one embodiment of the present invention, the first pre-drilled hole and the second pre-drilled hole are on the same vertically upward straight line.

[0021] According to one embodiment of the present invention, the diameter of the first pre-drilled hole is smaller than the diameter of the loading ball, and a loading device is used to pull the loading cable, thereby applying a radial load to the test piece by pulling the loading ball through the loading cable.

[0022] According to one embodiment of the present invention, the spherical loading device includes a loading ball, at least one loading cable, a loading rod, and a lever fulcrum. The loading ball is disposed within the simulated loading area, and one end of the loading rod is horizontally inserted into the simulated loading area and in contact with the loading ball.

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

[0024] The first transition section has at least one pre-made hole, one end of each loading cable is connected to the other end of the loading rod, and the other end of each loading cable extends outward through the corresponding pre-made hole.

[0025] The positive and progressive effects of this invention are as follows:

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

[0027] First, it can apply the same temperature field to the test piece as during service, while improving the loading method of radial load on the load-bearing casing, saving space for the test device inside the load-bearing casing, and providing convenience for heating and cooling devices.

[0028] Second, reduce the difference between the test temperature and the actual service temperature of the load-bearing casing of the aero-engine, making the test results more reliable.

[0029] Third, a radial load application method is provided to save space in the test equipment. Attached Figure Description

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

[0031] Figure 1 This is a front view of the load-bearing casing in the test device for the load-bearing casing of the aero-engine of the present invention.

[0032] Figure 2 This is a cross-sectional view of the load-bearing casing in the test apparatus for the load-bearing casing of the aero-engine of the present invention.

[0033] Figure 3 This is a schematic diagram of the mechanical testing assembly of the load-bearing casing in the test device for the load-bearing casing of the aero-engine of the present invention.

[0034] Figure 4 This is a schematic diagram of the load-bearing casing heating device in the test apparatus for the load-bearing casing of the aero-engine of the present invention.

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

[0036] Figure 6 This is a schematic diagram of radial load loading for the test device of the bearing casing of the aero-engine of the present invention.

[0037] Figure 7 for Figure 6 An enlarged schematic diagram of part A in the middle.

[0038] Figure 8 This is a schematic diagram of another radial load application method for the test apparatus of the bearing casing of the aero-engine of the present invention.

[0039] [Attached image labels]

[0040] 200 load-bearing casing

[0041] Outer casing 10

[0042] Inner casing 20

[0043] Support plate 30

[0044] Front flange of outer casing 11

[0045] External casing rear flange 12

[0046] Heating equipment 40

[0047] Cooling equipment 50

[0048] First transition segment 60

[0049] Test bench 70

[0050] Second transition section 80

[0051] Simulated loading area 81

[0052] Standard loading rod 90

[0053] Load ball 100

[0054] Loading cable 110

[0055] First pre-drilled hole 82

[0056] Second pre-drilled hole 61

[0057] Pre-drilled hole 62

[0058] Loading rod 120

[0059] Lever fulcrum 130 Detailed Implementation

[0060] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0061] Embodiments of the invention will now be described in detail with reference to the accompanying drawings. Preferred embodiments of the invention will now be described in detail, examples of which are shown in the drawings. Wherever possible, the same reference numerals will be used in all the drawings to denote the same or similar parts.

[0062] Furthermore, although the terminology used in this invention is selected from commonly known and used terms, some terms mentioned in this specification may have been selected by the applicant in his or her judgment, and their detailed meanings are explained in the relevant sections of the description herein.

[0063] Furthermore, the invention should be understood not only through the actual terminology used, but also through the meaning implied by each term.

[0064] like Figure 1 and Figure 2 As shown, this invention provides a test apparatus for a load-bearing casing of an aero-engine, comprising an annular outer casing 10, an annular inner casing 20, several support plates 30, several heating devices 40, and several cooling devices 50. The outer casing 10 is fitted over the inner casing 20, and the support plates 30 connect 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 for heating the test specimen. The cooling devices 50 are respectively installed on the corresponding outer casing 10 and inner casing 20 for cooling the test specimen. A temperature gradient is formed within the load-bearing casing 200 through the heating devices 40 and the cooling devices 50. The outer casing 10 is provided with a front flange 11 and a rear flange 12.

[0065] like Figure 3 As shown, the test apparatus 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, at which a radial load is applied. The load-bearing casing 200 is fixed to the test bench 70 by connecting to the first transition section 60. The inner casing 20 of the load-bearing casing 200 is connected to the second transition section 80, and a radial load is applied at the simulated loading area 81 during the test.

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

[0067] Based on the temperature distribution of the aero-engine load-bearing casing during operation, the temperature at the support plate 30 is relatively high, while the temperature on the inner and outer sides of the casing (outer casing 10 and inner casing 20) is relatively low. To simulate the actual temperature distribution, heating devices 40 are installed at the corresponding maximum temperature points on each support plate 30. These devices, such as resistance wires, are used to heat the test specimen. Cooling devices 50, such as cooling pipes, are installed at the outer casing 10 and inner casing 20 of the load-bearing casing 200 to cool the test specimen. Through the heating and cooling devices, a temperature gradient is created within the load-bearing casing.

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

[0069] To maintain a consistent temperature gradient within the load-bearing casing during testing, precise temperature control is required. Therefore, the number of heating and cooling devices can be increased, and each device can be individually controlled. For example, the flow rate and volume of coolant in each cooling pipe can be controlled to achieve multi-zone temperature regulation.

[0070] Additionally, multiple temperature sensors (not shown in the figure) can be installed on the load-bearing casing to measure the temperature of areas of interest. For example, multiple temperature-critical zones can be selected on the load-bearing casing, and temperature sensors can be installed at these zones. These temperature-critical zones refer to areas where the temperature is of interest or areas that significantly affect the overall temperature distribution during the test. By monitoring temperature values, the heating and cooling systems can be adjusted in real time to maintain the temperature gradient.

[0071] like Figure 5 As shown, when applying mechanical loads to the load-bearing casing, axial members are typically inserted from inside the inner casing 20 into the loading area, and then the load is applied via an actuator or similar device. Radial loads are applied to the test piece using a conventional loading rod 90. However, this loading method occupies a significant amount of space within the inner casing, potentially affecting the layout and control of the cooling system. Therefore, this invention proposes a novel radial load loading method that saves space in the testing equipment, avoids impacting the temperature control system, and facilitates the measurement of temperature data at the inner casing.

[0072] like Figure 6 and Figure 7 As shown, the test apparatus also includes a spherical loading device, which is installed in the simulated loading zone 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 pre-drilled hole 82 is formed in the simulated loading area 81 on the second transition section 80, and at least one second pre-drilled 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 within the simulated loading area 81. The other end of the loading cable 110 passes sequentially through the corresponding first pre-drilled hole 82 and second pre-drilled hole 61 and extends outward.

[0074] The first pre-drilled hole 82 and the second pre-drilled hole 61 are preferably arranged on the same vertically upward straight line.

[0075] The diameter of the first pre-drilled hole 82 is smaller than the diameter of the loading ball 100. The loading device pulls the loading cable 110, and the loading ball 100 is pulled by the loading cable 110 to apply a radial load to the test piece.

[0076] Radial loads are applied to the load-bearing casing using the spherical loading device. The loading cable 110 passes through a first pre-drilled hole 82 on the simulated loading area 81 of the second transition section 80 and extends outwards through a second pre-drilled hole 61 on the corresponding radial section 60. The diameter of the second pre-drilled hole 61 is smaller than the diameter of the loading ball 100. The loading cable 110 is pulled using an actuator or other loading device, and a radial load is applied to the test piece through the loading ball 100 connected to the loading cable 110. Because the mechanical test of the load-bearing casing may require the application of radial loads in multiple directions, it is necessary to do so separately.

[0077] Therefore, the loading ball 100 can be connected to multiple loading cables 110, and multiple radially opposite pre-drilled holes are provided on both the simulated loading area 81 and the first transition section 60. Before the test, all loading cables 110 are passed through the corresponding pre-drilled holes. During loading, the loading cables 110 in the corresponding direction are pulled, and the loading cables 110 in other directions are released to avoid the load-bearing casing having to be reloaded and reheated due to 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 placed in the simulated loading area 81, and one end of the loading rod 120 is horizontally inserted into the simulated loading area 81, contacting the loading ball 100. One end of the lever fulcrum 130 is fixed to the inner wall of the test bench 70, and the other end is connected to the loading rod 120. At least one pre-drilled hole 62 is provided 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, with the other end of each loading cable 110 extending outward through the corresponding pre-drilled hole 62.

[0079] The lever fulcrum 130 is fixed on the test bench 70. The loading rod 120 is connected to the lever fulcrum 130 and the loading cable 110. The loading cable 110 extends to the loading device through the pre-made 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] Because the mechanical testing of the load-bearing casing may require the application of radial loads in multiple directions, the loading rod 120 can be connected to multiple loading cables 110, and multiple pre-drilled holes 62 are provided in the corresponding directions of the first transition section. Before the test, all loading cables 110 are passed through the corresponding pre-drilled holes. During loading, only the loading cable 110 in the direction corresponding to which the radial load needs to be applied is pulled, while the loading cables 110 in other directions are released, to avoid the load-bearing casing needing to be reloaded and reheated during the test due to the application of loads in different directions.

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

[0082] First, it can apply the same temperature field to the test piece as during service, while improving the loading method of radial load on the load-bearing casing, saving space for the test device inside the load-bearing casing, and providing convenience for heating and cooling devices.

[0083] Second, reduce the difference between the test temperature and the actual service temperature of the load-bearing casing of the aero-engine, making the test results more reliable.

[0084] Third, a radial load application method is provided to save space in the test equipment.

[0085] For those skilled in the art, the above disclosure is merely illustrative and does not constitute a limitation of this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are suggested in this application and therefore remain within the spirit and scope of the exemplary embodiments of this application.

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

[0087] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A test apparatus for a load-bearing casing of an aero-engine, characterized in that, The test apparatus includes an annular outer casing, an annular inner casing, several support plates, several heating devices, and several cooling devices. The outer casing is fitted over the inner casing. The support plates are connected between the outer casing and the inner casing. The heating devices are installed at the maximum temperature of the corresponding support plates for heating the test piece. The cooling devices are respectively installed on the corresponding outer casing and inner casing to cool the test piece; the heating device and the cooling device create a temperature gradient inside the load-bearing casing; The test apparatus further includes a first transition section, a test bench, and a second transition section. 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, where a radial load is applied; The test apparatus also includes a spherical loading device, which is installed in the simulated loading area to apply a radial load to the load-bearing casing.

2. The test apparatus for the load-bearing casing of an aero-engine as described in claim 1, characterized in that, The heating device is a resistance wire used for heating, and the cooling device is a cooling pipe.

3. The test apparatus for the load-bearing casing of an aero-engine as described in claim 1, characterized in that, The heating device is arranged around 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.

4. The test apparatus for the load-bearing casing of an aero-engine as described in claim 1, characterized in that, The heating device and the cooling device are controlled separately.

5. The test apparatus for the load-bearing casing of an aero-engine as described in claim 1, characterized in that, The load-bearing casing is equipped with multiple temperature sensors to measure the temperature of the area of ​​interest.

6. The test apparatus for the load-bearing casing of an aero-engine as described in claim 1, characterized in that, The spherical loading device includes a loading ball and at least one loading cable. At least one first pre-made hole is provided on the simulated loading area on the second transition section, and at least one second pre-made hole is provided on the first transition section. The loading ball is connected to one end of the loading cable and is located within the simulated loading area; The other end of the loading cable passes through the corresponding first pre-drilled hole and the second pre-drilled hole in sequence and extends outward.

7. The test apparatus for the load-bearing casing of an aero-engine as described in claim 6, characterized in that, The first pre-drilled hole and the second pre-drilled hole are on the same vertically upward straight line.

8. The test apparatus for the load-bearing casing of an aero-engine as described in claim 6, characterized in that, The diameter of the first pre-drilled hole is smaller than the diameter of the loading ball. A loading device is used to pull the loading cable, and the loading ball is pulled by the loading cable to apply a radial load to the test piece.

9. The test apparatus for the load-bearing casing of an aero-engine as described in claim 1, characterized in that, The spherical loading device includes a loading ball, at least one loading cable, a loading rod, and a lever fulcrum. The loading ball is disposed within the simulated loading area, and one end of the loading rod is horizontally inserted into the simulated loading area and in contact with the loading ball. One end of the lever fulcrum is fixed to the inner wall of the test bench, and the other end is connected to the loading rod; The first transition section has at least one pre-made hole, one end of each loading cable is connected to the other end of the loading rod, and the other end of each loading cable extends outward through the corresponding pre-made hole.

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