Aero-engine casing strength test device

Abstract

The invention provides an aero-engine casing strength test device, the test device comprises a casing assembly and an external cavity assembly, the casing assembly comprises a test piece switching section and a casing, and the test piece switching section is used for fixing the casing; the external cavity assembly is installed outside the cartridge receiver assembly, the upper end of the cartridge receiver assembly and the upper end of the external cavity assembly are in clearance tolerance fit to form a matching surface, and a sealing structure is arranged on the matching surface, so that a closed load containing cavity is formed between the external cavity assembly and the cartridge receiver assembly; and when the pressure in the load accommodating cavity is increased, the matching surface between the upper end part of the external cavity assembly and the upper end part of the cartridge receiver assembly generates axial displacement. According to the aero-engine casing strength test device, no additional axial force or other loads are generated when external pressure is applied to the casing in the casing strength test process.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine strength testing, and in particular to an aircraft engine casing strength testing device. Background Art

[0002] In the static strength test of aircraft engines, it is necessary to conduct buckling analysis on the engine casings that may buckle overall or locally to verify whether the casing can avoid buckling instability under the target load within the working envelope, including the first-guide inner support casing. The first-guide inner support casing of aircraft engines is used to support the first-stage guide vanes and withstand the airflow pressure from the casing cavity.

[0003] Therefore, in order to simulate the strength results of a missile internal support casing under pressure load, it is necessary to carry out a strength test of the missile internal support casing to verify whether it meets the requirements of buckling strength.

[0004] Usually, the first-guide inner support casing needs to withstand the pressure load from the outside to the inside. In the static test of the first-guide inner support of an aircraft engine, an external cavity is set to wrap the casing. During the test, it is necessary to ensure that the test loading structure does not generate additional axial force and other loads that affect the test casing.

[0005] At the same time, the inner support casing of the first-guide is relatively small, and a test device structure that can improve the convenience of the operating space is required. During the disassembly process after the test, there is still a situation where residual hydraulic oil overflows and makes it inconvenient to clean up.

[0006] Therefore, the inventor of the present application has designed an aircraft engine casing strength testing device in order to overcome the above-mentioned technical problems. Summary of the invention

[0007] The technical problem to be solved by the present invention is to provide an aircraft engine casing strength test device in order to overcome the defect in the prior art that other loads such as additional axial force generated by the test loading structure during the casing strength test affect the test casing.

[0008] The present invention solves the above technical problems through the following technical solutions:

[0009] The present invention provides an aircraft engine casing strength test device, which is characterized in that the test device comprises a casing assembly and an external cavity assembly, the casing assembly comprises a test piece transition section and a casing, the test piece transition section is used to fix the casing; the external cavity assembly is installed outside the casing assembly, and the clearance tolerance between the upper end portion of the casing assembly and the upper end portion of the external cavity assembly is matched to form a matching surface, a sealing structure is provided on the matching surface, so that a closed load-bearing cavity is formed between the external cavity assembly and the casing assembly; when the pressure in the load-bearing cavity increases, the matching surface between the upper end portion of the external cavity assembly and the upper end portion of the casing assembly undergoes axial displacement.

[0010] According to one embodiment of the present invention, the test piece transition section includes a test piece upper transition section and a test piece lower transition section, the test piece upper transition section is installed on the upper part of the casing, and the test piece lower transition section is installed on the lower part of the casing.

[0011] According to one embodiment of the present invention, the external chamber assembly includes an upper pressure cylinder and a lower pressure cylinder, and the upper pressure cylinder is detachably connected to the lower pressure cylinder.

[0012] According to one embodiment of the present invention, the upper end of the external cavity assembly has a mounting edge, and the upper end of the receiver assembly has a mounting edge. The mounting edge of the upper end of the external cavity assembly and the mounting edge of the upper end of the receiver assembly are matched with clearance tolerance to form a matching surface.

[0013] According to one embodiment of the present invention, the external cavity assembly has an oil inlet and outlet for returning hydraulic oil.

[0014] According to one embodiment of the present invention, a sealing structure is provided at the connection interface between the upper pressure cylinder and the lower pressure cylinder.

[0015] According to one embodiment of the present invention, in the load chamber, the lower pressure cylinder is provided with a concave structure for carrying hydraulic oil.

[0016] According to one embodiment of the present invention, it also includes a constraint mechanism, which includes a lifting and adjusting component and a base, one end of the lifting and adjusting component is connected to the bottom of the external cavity assembly, and the other end of the lifting and adjusting component is movably connected to the base, so that the lifting and adjusting component can adjust the height up and down along the base.

[0017] According to an embodiment of the present invention, the other end of the lifting and lowering adjustment component is provided with an external thread, and is threadably connected to the base via the external thread.

[0018] The positive and progressive effects of the present invention are:

[0019] When external pressure is applied to the casing of the aircraft engine casing strength test device of the present invention, no additional axial force or other loads will affect the test casing. The bottom of the casing is connected to a lifting and adjusting component, which can control the working height of the test platform and improve the convenience of the operating space. The lower pressure cylinder of the external cavity is designed to be concave, which avoids the overflow of residual hydraulic oil during the disassembly of the tooling and the test piece at the end of the test, improves the operability of the test on and off the platform, and reduces labor costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] 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:

[0021] Figure 1 It is a three-dimensional schematic diagram of an aircraft engine casing strength testing device of the present invention.

[0022] Figure 2 It is a cross-sectional schematic diagram of an aircraft engine casing strength testing device of the present invention.

[0023] Figure 3A It is a cross-sectional schematic diagram of a casing assembly of an aircraft engine casing strength testing device of the present invention.

[0024] Figure 3B It is a cross-sectional schematic diagram of the external cavity assembly of the aircraft engine casing strength testing device of the present invention.

[0025] [Reference Signs]

[0026] Receiver assembly 100

[0027] Test piece transition section 110

[0028] Test piece upper transition section 111

[0029] Test piece lower transition section 112

[0030] Receiver 120

[0031] Installation side 130

[0032] External cavity assembly 200

[0033] Upper pressure cylinder 210

[0034] Ring 211

[0035] Bottom wall 212

[0036] External mounting edge 213

[0037] Mounting edge 214

[0038] Opening 215

[0039] Lower pressure cylinder 220

[0040] Top wall 221

[0041] External mounting edge 222

[0042] Oil inlet and outlet 223

[0043] Concave structure 224

[0044] Restraint mechanism 300

[0045] Lifting and adjusting component 310

[0046] Base 320

[0047] Bolt 330

[0048] Bolt 400

[0049] Sealing structure 500

[0050] Sealing structure 600

[0051] Load chamber S

[0052] Matching surface F DETAILED DESCRIPTION

[0053] 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.

[0054] 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.

[0055] 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.

[0056] 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.

[0057] like Figure 1 , Figure 2 , Figure 3A and Figure 3BAs shown, the present invention discloses an aircraft engine casing strength test device, the test device includes a casing assembly 100 and an external cavity assembly 200. The casing assembly 100 includes a test piece transition section 110 and a casing 120, and the test piece transition section 110 is used to fix the casing 120. The external cavity assembly 200 is installed outside the casing assembly 100, and the clearance tolerance between the upper end of the casing assembly 100 and the upper end of the external cavity assembly 200 is matched to form a mating surface F, and a sealing structure 500 is provided at the mating surface F, so that a closed load chamber S is formed between the external cavity assembly 200 and the casing assembly 100.

[0058] When the pressure in the load chamber S increases, the mating surface F between the upper end of the external chamber assembly 200 and the upper end of the casing assembly 100 is axially displaced.

[0059] The casing 120 is connected to the test piece transition section 110 to form a casing assembly 100 . The test piece transition section 110 is connected to the external cavity assembly 200 , so that the casing 120 is fixed on the external cavity assembly 200 .

[0060] The external cavity assembly 200 wraps around the casing assembly 100. In this embodiment, the sealing structure 500 is preferably a sealing ring, which is arranged at the upper end of the external cavity assembly 200, so that the upper end of the casing assembly 100 is sealed with the upper end of the external cavity assembly 200, so that a closed load chamber S is formed between the external cavity assembly 200 and the casing assembly 100.

[0061] A pressure load is generated in the load chamber S by injecting hydraulic oil or the like, and the generated pressure load is applied to the casing 120 to perform a strength test of the casing 120. In order to release the additional axial force generated by the pressure load in the load chamber S on the casing 120, a portion of the upper portion of the casing assembly 100 is not completely wrapped by the external cavity assembly 200, that is, an opening 215 is provided at the upper portion of the external cavity assembly 200, providing space for the upper end portion of the casing assembly 100 and the upper end portion of the external cavity assembly 200 to slide against each other and generate displacement.

[0062] In addition, due to the clearance tolerance between the upper end of the external cavity assembly 200 and the upper end of the casing assembly 100, the mating surface F between the upper end of the external cavity assembly 200 and the upper end of the casing assembly 100 can be axially displaced.

[0063] When the pressure in the load chamber S increases, the axial load generated by the pressure causes the external chamber assembly 200 to deform axially, and the upper end of the external chamber assembly 200 is axially displaced relative to the upper end of the casing assembly 100 and can slide freely up and down along the mating surface F without generating axial constraints, thereby releasing the additional axial force caused by the pressure load.

[0064] Since no axial constraint is generated between the upper end of the external cavity assembly 200 and the upper end of the casing assembly 100, the additional axial force on the casing assembly 100 caused by the pressure load is released, thereby solving the problem of other loads such as the additional axial force generated by the test loading structure during the test affecting the casing 120.

[0065] like Figure 2 , Figure 3A As shown, as a preferred embodiment, the test piece transition section 110 includes a test piece upper transition section 111 and a test piece lower transition section 112 , the test piece upper transition section 111 is installed on the upper part of the casing 120 , and the test piece lower transition section 112 is installed on the lower part of the casing 120 .

[0066] For example, the upper mounting edge of the casing 120 is connected to the upper transition section 111 of the test piece by bolts, buckles, etc., and the lower mounting edge of the casing 120 is connected to the lower transition section 112 of the test piece by bolts, buckles, etc., and the three components constitute the casing assembly 100. The bottom of the lower transition section 112 of the test piece is fixedly connected to the bottom of the external cavity assembly 200 by bolts, etc., so that the casing assembly 100 is fixed inside the external cavity assembly 200.

[0067] The upper transition section 111 of the test piece provides a side for connection with the external cavity assembly 200, and the lower transition section 112 of the test piece enables the casing 120 to be fixed inside the external cavity assembly 200, so that the pressure load applied in the load chamber S can act on the casing 120 as a whole, ensuring the stability of the test structure and the accuracy of the casing strength test.

[0068] like Figure 1 , Figure 2 , Figure 3B As shown, as a preferred embodiment, the external chamber assembly 200 includes an upper pressure cylinder 210 and a lower pressure cylinder 220, and the upper pressure cylinder 210 and the lower pressure cylinder 220 are detachably connected.

[0069] For example, the bottom cylinder wall 212 of the upper pressure cylinder 210 radially extends an outer mounting edge 213 to the outside of the cylinder body, and the top cylinder wall 221 of the lower pressure cylinder 220 radially extends an outer mounting edge 222 to the outside of the cylinder body, and the outer mounting edge 213 and the outer mounting edge 222 are flange-connected, that is, a plurality of bolts 400 pass through the outer mounting edge 213 and the outer mounting edge 222 at the same time, thereby fixing the upper pressure cylinder 210 and the lower pressure cylinder 220. When disassembling, the bolts 400 are screwed out from the outer mounting edge 213 and the outer mounting edge 222, so that the upper pressure cylinder 210 and the lower pressure cylinder 220 can be separated.

[0070] like Figure 3A , 3BAs shown, the upper end of the external cavity assembly 200 has a mounting edge 214, and the upper end of the casing assembly 100 has a mounting edge 130. The mounting edge 214 at the upper end of the external cavity assembly 200 and the mounting edge 130 at the upper end of the casing assembly 100 are matched with a clearance tolerance to form a matching surface F. A sealing ring is installed between the two mounting edges to achieve the top sealing of the cavity.

[0071] The upper part of the external cavity assembly 200 has a ring portion 211 bent inward, the inner edge of the ring portion 211 forms a mounting edge 214, and the side edge of the transition section 111 on the test piece has a mounting edge 130, and the mounting edge 214 abuts against the mounting edge 130 and the clearance tolerance is matched. A sealing structure 500 is provided between the mounting edge 214 of the inner edge of the ring portion 211 and the mounting edge 130 of the transition section 111 on the test piece. In this embodiment, the sealing structure 500 can preferably be a sealing ring, which is provided on the mounting edge 214 of the inner edge of the ring portion 211 of the external cavity assembly 200, so that a closed load chamber S is formed between the external cavity assembly 200 and the casing assembly 100.

[0072] The mounting edge 214 of the external cavity assembly 200 and the mounting edge 130 of the casing assembly 100 are abutted against each other and matched with clearance tolerance to form a matching surface F. When the pressure in the load chamber S increases, the matching surface F undergoes axial displacement.

[0073] like Figure 2 , Figure 3B As shown, the external chamber assembly 200 has an oil inlet and outlet 223 for returning hydraulic oil.

[0074] The oil inlet and outlet 223 are arranged at the bottom of the external cavity assembly 200 . The oil is pumped into the load chamber S through the oil inlet and outlet 223 . A hydraulic load is generated in the closed load chamber S and applied to the casing 120 to perform a casing strength test.

[0075] When the casing strength test is completed, the hydraulic oil is discharged from the oil inlet and outlet 223 .

[0076] like Figure 2 , Figure 3B As shown, a sealing structure 600 is provided at the connection interface between the upper pressure cylinder 210 and the lower pressure cylinder 220 .

[0077] For example, a sealing ring is installed at the connection interface between the upper pressure cylinder 210 and the lower pressure cylinder 220 to achieve the bottom sealing of the load chamber S and ensure the sealing of the load chamber S. Thus, the pressure applied in the load chamber S will not leak, thereby ensuring the accuracy of the casing strength test.

[0078] like Figure 2 and Figure 3B As shown, in the load chamber S, the lower pressure cylinder 220 is provided with a concave structure 224 for carrying hydraulic oil.

[0079] After the hydraulic oil is discharged through the oil inlet and outlet 223 to complete the oil pressure unloading, there is usually residual hydraulic oil in the load chamber S. Since the lower pressure cylinder 220 has a concave structure 224, after the upper pressure cylinder 210 is disassembled, the residual hydraulic oil can still be contained in the concave structure 224 of the lower pressure cylinder 220. Therefore, compared with the lower pressure cylinder 220 with a planar structure, the lower pressure cylinder 220 with a concave structure 224 can prevent the overflow of hydraulic oil after disassembly, improve the operability of the test platform, and reduce labor costs.

[0080] like Figure 1 and Figure 2 As shown, the aircraft engine casing strength test device also includes a constraint mechanism 300, which includes a lifting and adjusting component 310 and a base 320. One end of the lifting and adjusting component 310 is connected to the bottom of the external cavity assembly 200, and the other end of the lifting and adjusting component 310 is movably connected to the base 320, so that the lifting and adjusting component 310 can be adjusted up and down in height along the base 320.

[0081] For example, the bolt 330 passes through the bottom center of the external cavity assembly 200 and is connected to the lifting and adjusting component 310, thereby fixing the external cavity assembly 200 and the lifting and adjusting component 310 together. The lifting and adjusting component 310 and the external cavity assembly 200 can also be connected by pins, welding, etc.

[0082] The base 320 is used to fix the casing strength test device, and the lifting and adjusting component 310 can adjust the height of the casing strength test device, so as to facilitate the operation of the staff. The restraint mechanism 300 including the lifting and adjusting component 310 can adjust the height of the test platform, and for a casing 120 with a smaller volume, such as an internal support casing of an aircraft engine, the operability of the test is improved.

[0083] like Figure 1 and Figure 2 As shown, the other end of the lifting and adjusting component 310 is provided with an external thread, and is threadedly connected to the base 320 through the external thread.

[0084] The lifting and lowering adjustment component 310 provided with an external thread is a large nut structure, and the height of the casing strength testing device is adjusted by the screwing depth of the external thread, so as to facilitate the operation of the staff.

[0085] The aircraft engine casing strength test device proposed by the present invention is suitable for strength testing of various casings of aircraft engines, and is particularly suitable for an inner support casing of an aircraft engine.

[0086] The present invention provides a structure for applying external pressure to the casing while avoiding the generation of additional axial force; the lifting and lowering adjustment component 310 at the bottom of the casing and the concave structure 224 of the lower pressure cylinder 220 both improve the operability of the test, simplify the on- and off-stage operations of the test, and save labor costs.

[0087] The present invention applies external pressure to the casing, and at the same time, the load chamber S formed after the casing assembly 100 and the external cavity assembly 200 are assembled does not generate additional axial force or other loads that affect the test casing. The bottom of the casing is connected to a lifting and adjusting component 310, which can control the working height of the test platform and improve the convenience of the operating space. The lower pressure cylinder 220 of the external cavity assembly 200 is designed to be concave, which avoids the overflow of residual hydraulic oil during the disassembly of the tooling and the test piece at the end of the test, improves the operability of the test on and off the platform, and reduces labor costs.

[0088] 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. An aircraft engine casing strength test device, characterized in that: The test device comprises a casing assembly and an external cavity assembly. The casing assembly includes a test piece transition section and a casing, wherein the test piece transition section is used to fix the casing; The external cavity assembly is installed outside the casing assembly, and the upper end of the casing assembly and the upper end of the external cavity assembly are matched with each other with a clearance tolerance to form a matching surface, and a sealing structure is provided on the matching surface, so that a closed load-containing cavity is formed between the external cavity assembly and the casing assembly; When the pressure in the load chamber increases, the mating surface between the upper end of the external cavity assembly and the upper end of the casing assembly undergoes axial displacement.

2. The aircraft engine casing strength test device according to claim 1, characterized in that: The test piece transition section comprises an upper test piece transition section and a lower test piece transition section. The upper test piece transition section is installed on the upper part of the casing, and the lower test piece transition section is installed on the lower part of the casing.

3. The aircraft engine casing strength testing device according to claim 2, characterized in that: The external cavity assembly comprises an upper pressure cylinder and a lower pressure cylinder, and the upper pressure cylinder is detachably connected to the lower pressure cylinder.

4. The aircraft engine casing strength testing device according to claim 1, characterized in that: The upper end of the external cavity component has a mounting edge, and the upper end of the casing component has a mounting edge. The mounting edge of the upper end of the external cavity component and the mounting edge of the upper end of the casing component are matched with clearance tolerance to form a matching surface.

5. The aircraft engine casing strength testing device according to claim 1, characterized in that: The external cavity assembly is provided with an oil inlet and an oil outlet for returning hydraulic oil.

6. The aircraft engine casing strength testing device according to claim 3, characterized in that: The connection interface between the upper pressure cylinder and the lower pressure cylinder has a sealing structure.

7. The aircraft engine casing strength testing device according to claim 3, characterized in that: In the load chamber, the lower pressure cylinder is provided with a concave structure for carrying hydraulic oil.

8. The aircraft engine casing strength testing device according to claim 1, characterized in that: It also includes a constraint mechanism, which includes a lifting and adjusting component and a base, one end of the lifting and adjusting component is connected to the bottom of the external cavity assembly, and the other end of the lifting and adjusting component is movably connected to the base, so that the lifting and adjusting component can adjust its height up and down along the base.

9. The aircraft engine casing strength testing device according to claim 8, characterized in that: The other end of the lifting and adjusting component is provided with an external thread, and is threadably connected to the base via the external thread.

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