Aero-engine elastic supporting device and aero-engine test bed

Abstract

The invention discloses an aero-engine elastic supporting device and an aero-engine test bench, and the aero-engine elastic supporting device comprises a supporting pedestal, an elastic supporting assembly disposed on the supporting pedestal, and two hinge seats disposed on the two opposite sides of the elastic supporting assembly. The connecting rod is arranged between the hinge seat and the elastic supporting assembly in a crossing manner; the number of the connecting rods is two, the first ends of the two connecting rods are hinged to the two hinge bases in a one-to-one correspondence mode, the second ends of the two connecting rods are hinged to the elastic supporting assembly and are elastically supported and fixed upwards in the vertical direction through the elastic supporting assembly, and supporting pieces are arranged in the middles of the two connecting rods. The supporting pieces on the two connecting rods are used for supporting different positions of the aero-engine respectively. The elastic supporting device for the aero-engine can effectively eliminate vibration, stress and micro-deformation caused by thermal expansion generated in the test process of the aero-engine, and the vibration reduction effect is good.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine test runs, and in particular, to an elastic support device for an aero-engine, and an aero-engine test bench using the elastic support device for an aero-engine. Background Art

[0002] At present, due to the characteristics of high rotational speed, high thermal parameters, high power-to-weight ratio, long service life, low fuel consumption and high reliability required by turboshaft engines, a large number of new technologies, new structures, new materials and new processes are adopted in the design and manufacture of aero-engines. Therefore, a large number of verification tests are required to test the parameter performance and reliability of the engines. According to statistics, more than 10,000 hours of full-engine tests are required during the development of a new model of turboshaft engine. The overall structure and performance matching, the mutual influence of each component of the engine, and the changes in engine performance and stability caused by changes in external conditions all need to be determined by full-engine tests. The service life of the full engine and each structural component of the engine also requires a large number of full-engine tests for verification. However, the support structure of the existing test vehicle platform usually only serves to fix the aero-engine, with large installation and debugging errors and great difficulty in movement, and it is impossible to achieve vibration reduction and eliminate the micro-deformation caused by thermal expansion.

[0003] In this regard, Chinese Utility Model Patent CN211504670U provides an aero-engine test bench, which includes a shock-absorbing seat. The upper end of the shock-absorbing seat is connected with a fixed seat, and fixed frames are installed on both sides of the upper end of the fixed seat. A protective frame is arranged on the side of the fixed frame. The aero-engine test bench reduces vibration by setting a shock-absorbing seat. The two shock-absorbing cylinders buffer and reduce vibration at the upper ends of the first support plate and the second support plate. The shock-absorbing rubber is used for buffer vibration reduction between the two aluminum alloy support columns, and the shock-absorbing spring is used for spring vibration reduction. Multiple vibration reductions effectively improve the shock-absorbing effect. However, since the fixed seat, the fixed frame and the protective frame are also provided on the shock-absorbing seat, the load of the shock-absorbing seat is large, which affects the shock-absorbing effect, and it will also cause resonance and left-right swing of the fixed seat, the fixed frame and the protective frame as a whole, affecting the installation stability of the aero-engine. Summary of the Invention

[0004] Primarily, the present invention provides an elastic support device for an aero-engine to solve the technical problem that the existing aero-engine test bench cannot achieve a good shock-absorbing effect.

[0005] The present invention also provides an aero-engine test bench using the above elastic support device for an aero-engine.

[0006] According to one aspect of the present invention, an elastic support device for an aeroengine is provided, which includes a support base, an elastic support assembly disposed on the support base, two hinge seats respectively disposed on opposite sides of the elastic support assembly, and a connecting rod spanning between the hinge seats and the elastic support assembly; there are two connecting rods, the first ends of the two connecting rods are respectively and correspondingly hinged to the two hinge seats, the second ends of the two connecting rods are both hinged to the elastic support assembly and are elastically supported and fixed upward in the vertical direction through the elastic support assembly, and support members are respectively provided in the middle of the two connecting rods, and the support members on the two connecting rods are respectively used to support different positions of the aeroengine.

[0007] Preferably, the elastic support assembly includes a compression spring disposed in the vertical direction, a pressing plate that presses the compression spring onto the support base from above the compression spring, and a connecting bolt that sequentially passes through the pressing plate and the compression spring and is connected to the support base; the pressing plate is provided with a through hole for the connecting bolt to pass through, and two hinge portions are provided on the top surface of the pressing plate, and the two hinge portions are symmetrically disposed on opposite sides of the through hole with respect to the axis of the through hole, and the second ends of the two connecting rods are respectively and correspondingly hinged to the two hinge portions.

[0008] Preferably, the connecting rod includes two connecting arms disposed in parallel and at intervals, and a first connecting pin, a second connecting pin, and a third connecting pin that are arranged along the length direction of the connecting arms and all pass through the two connecting arms, the hinge seat, the support member, and the hinge portion are all clamped between the two connecting arms, the first connecting pin passes through the hinge seat, the second connecting pin passes through the support member, and the third connecting pin passes through the hinge portion.

[0009] Preferably, the first end of the support member is hinged to the middle of the connecting rod, the second end of the support member extends upward and is provided with a plurality of connecting holes at intervals along the length direction of the connecting rod, and the connecting holes are used to connect with the aeroengine.

[0010] Preferably, the support base includes a first adjustment seat, a second adjustment seat, and a positioning assembly, the top surface of the first adjustment seat is provided with a first inclined surface, the bottom surface of the second adjustment seat is provided with a second inclined surface, the second adjustment seat is disposed above the first adjustment seat and abuts and fits against the first inclined surface through the second inclined surface, the second adjustment seat is used to move along the inclination direction of the first inclined surface and adjust the height of the second adjustment seat through the cooperation of the first inclined surface and the second inclined surface, the positioning assembly is connected to the second adjustment seat and is used to lock and fix the second adjustment seat after the height of the second adjustment seat is adjusted, and the elastic support assembly and the hinge seat are both disposed on the second adjustment seat.

[0011] Preferably, the support base further includes a support plate, a limiting plate, and an adjusting screw rod. The support plate is provided with a slide rail along the direction of the connection line of the two hinge seats. The first adjusting seat is slidably disposed on the slide rail. The limiting plate is disposed at at least one end of the slide rail and is used to abut against the first adjusting seat to limit the sliding stroke of the first adjusting seat along the slide rail. The first end of the adjusting screw rod is rotatably installed on the first adjusting seat and is axially fixed relative to the first adjusting seat. The second end of the adjusting screw rod is threadedly connected to an adjusting screw hole preset on the limiting plate. The adjusting screw rod is used to be driven to rotate and drive the first adjusting seat to translate and adjust its position along the slide rail through threaded cooperation.

[0012] Preferably, the positioning assembly includes a first positioning bolt arranged vertically and a first positioning nut threadedly connected to the first positioning bolt. A first positioning hole is formed on the first adjusting seat. The second adjusting seat is provided with a waist-shaped hole along the inclined direction of the first inclined surface. The first end of the first positioning bolt is rotatably connected to the first adjusting seat and is axially fixed relative to the first adjusting seat. The second end of the first positioning bolt sequentially passes through the first positioning hole and the waist-shaped hole. The first positioning nut is disposed at one end of the first positioning bolt passing through the waist-shaped hole and is used to tightly press the upper surface of the second adjusting seat.

[0013] Preferably, a first positioning plate is provided at one end of the first adjusting seat in its width direction. The first inclined surface is provided with a notch exposing the first positioning plate. The second adjusting seat is provided with a second positioning plate facing the first positioning plate. Both the first positioning plate and the second positioning plate are arranged vertically. The second adjusting seat is used to adjust the distance between the second positioning plate and the first positioning plate when moving relative to the first inclined surface. The positioning assembly further includes a second positioning bolt sequentially passing through the first positioning plate and the second positioning plate in the horizontal direction and locking and fixing the first positioning plate and the second positioning plate.

[0014] Preferably, the second positioning bolt is disposed in the middle of the first adjusting seat. There are two first positioning bolts, and the two first positioning bolts are respectively arranged on opposite sides of the second positioning bolt along the length direction of the first adjusting seat.

[0015] As a second aspect, the present invention further provides an aeroengine test bench, including the above-mentioned aeroengine elastic support device.

[0016] The present invention has the following beneficial effects: In the elastic support device for an aeroengine provided by the present invention, an elastic support assembly connects two connecting rods into a whole and simultaneously elastically supports and fixes the second ends of the two connecting rods, enabling both connecting rods to swing up and down around the corresponding hinge seats. The different positions of the aeroengine are supported by the support members on the two connecting rods respectively, achieving the elastic support and fixation of the aeroengine. When the aeroengine generates vibrations, stresses, and micro-deformations caused by thermal expansion during the test, the elastic deformation of the elastic support assembly allows the connecting rods to swing at corresponding angles to eliminate them, ensuring the safe and stable progress of the aeroengine test. The overall structure is simple and efficient. Compared with the annular support structure, it is more convenient to disassemble, assemble, and adjust the installation position of the aeroengine. Moreover, since the elastic support force of the elastic support assembly can directly act on the aeroengine through the cooperation of the two connecting rods and the support members, there is no need to set a large fixed seat in the middle, and the vibration damping effect is better. More importantly, by using an elastic support assembly to simultaneously elastically support and fix the two connecting rods, the forces on the two connecting rods can be balanced, enabling the support members on the two connecting rods to maintain a centering state to stably fix the aeroengine. It can also make the swinging amplitudes of the two connecting rods the same and the swinging directions opposite, which can cancel out the stresses with each other and effectively improve the vibration damping effect.

[0017] In addition to the purposes, features, and advantages described above, the present invention has other purposes, features, and advantages. The following will refer to the drawings for a more detailed description of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings: Figure 1 is a schematic structural diagram of an aeroengine test bench provided by an embodiment of the present invention; Figure 2 is Figure 1 the front view of the elastic support device for an aeroengine in the aeroengine test bench shown; Figure 3 is Figure 2 the three-dimensional view of the elastic support assembly in the elastic support device for an aeroengine shown; Figure 4 is Figure 2 the assembly structure diagram of the hinge seat, connecting rod, and support member in the elastic support device for an aeroengine shown; Figure 5 is Figure 2 the sectional structure diagram of the support base in the elastic support device for an aeroengine shown.

[0019] Legend: 1000, Aircraft engine test stand 1. Elastic support device for aircraft engine; 11. Support base; 111. First adjustment seat; 1111. First inclined plane; 1112. First positioning hole; 1113. First positioning plate; 112. Second adjustment seat; 1121. Second inclined plane; 1122. Waist-shaped hole; 1123. Second positioning plate; 113. Positioning component; 1131. First positioning bolt; 1132. First positioning nut; 1133. Second positioning bolt; 1134. Second positioning nut; 114. Support plate; 1141. Slide rail; 115. Limiting plate; 116. Adjusting screw rod; 117. Column; 118. Mounting plate; 12. Elastic support component; 121. Compression spring; 122. Pressure plate; 1221. Through hole; 1222. Hinge part; 1223. Sleeve; 123. Connecting bolt; 124. Connecting nut; 125. Contact plate; 13. Hinge seat; 131. Positioning pin; 132. Mounting hole; 14. Connecting rod; 141. Connecting arm; 142. First connecting pin; 143. Second connecting pin; 144. Third connecting pin; 15. Support member; 151. Connecting hole 2. Bottom plate; 3. Support column; 4. Mounting section Detailed implementation mode

[0020] The following will explain the embodiments of the present invention in detail with reference to the accompanying drawings. However, the present invention can be implemented in many different ways defined and covered by the following. Examples of the embodiments are shown in the drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The embodiments described by referring to the drawings below are exemplary and are only used to explain the present invention, and cannot be construed as a limitation to the present invention

[0021] Those skilled in the art of the present technology can understand that unless specifically stated, the term "including" used in the description of the present invention means the presence of the described features, integers, steps, operations, components and / or assemblies, but does not exclude the presence or addition of one or more other features, integers, steps, operations, components, assemblies and / or their combinations. It should be understood that when we say a component is "connected" to another component, it can be directly connected to other components or connected through intermediate components. The term "and / or" used here includes all or any unit and all combinations of one or more related listed items. The terms "first" and "second" etc. in the description and claims of the present invention are used to distinguish different objects, rather than to describe a specific order

[0022] Figures 1 to 5Collectively shown is an elastic support device for an aero-engine provided by an embodiment of the present invention. It is used to be arranged on an aero-engine test bench and support a local position of the aero-engine, and can effectively eliminate the working vibration, stress and thermal expansion of the aero-engine during the test, ensuring the safe and stable progress of the aero-engine test.

[0023] Please refer to Figure 1 and Figure 2 , the aero-engine elastic support device 1 includes a support base 11, an elastic support assembly 12, two hinge seats 13, two connecting rods 14 and two support members 15. The elastic support assembly 12 is arranged at the middle position of the top end of the support base 11. The two hinge seats 13 are respectively arranged on the opposite sides of the elastic support assembly 12 and are both installed on the support base 11. The first ends of the two connecting rods 14 are respectively hinged to the two hinge seats 13 in a one-to-one correspondence. The second ends of the two connecting rods 14 are both hinged to the elastic support assembly 12 and are elastically supported and fixed upward in the vertical direction through the elastic support assembly 12, that is, the connecting rods 14 straddle between the hinge seats 13 and the elastic support assembly 12. The two support members 15 are respectively arranged at the middle parts of the two connecting rods 14, and the support members 15 on the two connecting rods 14 are respectively used to support different positions of the aero-engine.

[0024] In the aero-engine elastic support device 1, the elastic support assembly 12 connects the two connecting rods 14 into a whole and at the same time elastically supports and fixes the second ends of the two connecting rods 14, so that the two connecting rods 14 can swing up and down around the corresponding hinge seats 13, and the different positions of the aero-engine are respectively supported by the support members 15 on the two connecting rods 14 to realize the elastic support and fixation of the aero-engine. When the aero-engine generates vibration, stress and micro-deformation caused by thermal expansion during the test, the elastic deformation of the elastic support assembly 12 can allow the connecting rods 14 to swing at corresponding angles to eliminate it, ensuring the safe and stable progress of the aero-engine test. The overall structure is simple and efficient. Compared with the annular support structure, it is more convenient to disassemble, assemble and adjust the installation position of the aero-engine. And because the elastic support force of the elastic support assembly 12 can directly act on the aero-engine through the cooperation of the two connecting rods 14 and the support members 15, there is no need to set a large fixed seat in the middle, and the damping effect is better. More importantly, by using one elastic support assembly 12 to simultaneously elastically support and fix the two connecting rods 14, the forces on the two connecting rods 14 can be balanced, so that the support members 15 on the two connecting rods 14 can maintain a centering state to stably fix the aero-engine, and the swing amplitudes of the two connecting rods 14 are the same and the swing directions are opposite, which can cancel the stress with each other and effectively improve the damping effect.

[0025] Please refer to Figure 2 and Figure 3, the elastic support assembly 12 includes a compression spring 121, a pressure plate 122 and a connecting bolt 123. The compression spring 121 is vertically arranged on the upper surface of the support base 11. The pressure plate 122 abuts against the top end of the compression spring 121 and elastically presses the compression spring 121 onto the support base 11 from above the compression spring 121. The connecting bolt 123 passes through the pressure plate 122 and the compression spring 121 and is connected to the support base 11, so as to lock and fix the pressure plate 122 through the connecting bolt 123 and perform radial limit on the compression spring 121. The connection structure is simple and efficient. The lifting adjustment of the pressure plate 122 can be realized by adjusting the locking height of the connecting bolt 123, so as to flexibly adjust the compression amount of the compression spring 121 and meet the elastic support requirements of different specifications.

[0026] Preferably, the pressure plate 122 is provided with a through hole 1221 for the connecting bolt 123 to pass through. The top surface of the pressure plate 122 is provided with two hinge parts 1222. The two hinge parts 1222 are symmetrically arranged on the opposite sides of the through hole 1221 relative to the axis of the through hole 1221. The second ends of the two connecting rods 14 are respectively and correspondingly hinged to the two hinge parts 1222. That is, the two connecting rods 14 are symmetrically arranged along the axis of the compression spring 121, so that the downward pressure received by the two connecting rods 14 can be evenly transmitted to the compression spring 121, avoiding the compression spring 121 from tilting towards one of the connecting rods 14. Secondly, since the second ends of the two connecting rods 14 are respectively installed through different hinge parts 1222, the hinge positions of the two connecting rods 14 are staggered. While being more convenient for assembly, it can also make the elastic positions of the two connecting rods 14 staggered, thereby avoiding mutual restraint between the two connecting rods 14 and allowing the two connecting rods 14 to swing slightly in the horizontal direction, further improving the vibration damping effect.

[0027] Further, the top surface of the pressure plate 122 is also provided with a sleeve 1223. The through hole 1221 is axially opened in the sleeve 1223. The two hinge parts 1222 are respectively arranged on the opposite sides of the sleeve 1223 and integrally formed with the sleeve 1223. The two hinge parts 1222 are strengthened and fixed through the sleeve 1223, avoiding the two hinge parts 1222 from breaking.

[0028] Further, the elastic support assembly 12 further includes a connecting nut 124. The connecting nut 124 is threadedly connected to the connecting bolt 123 and abuts against the top end of the pressure plate 122, so as to press the pressure plate 122 through the connecting nut 124 and adjust the downward pressure height of the pressure plate 122 to ensure uniform force.

[0029] Further, the elastic support assembly 12 further includes a contact plate 125 which is disposed at the bottom end of the compression spring 121 and abuts against the upper surface of the support base 11, so as to support and fix the compression spring 121 through the contact plate 125, increase the contact area of the compression spring 121 relative to the support base 11, and thus improve the stability of the compression spring 121.

[0030] Please refer to Figure 2 and Figure 4 The connecting rod 14 includes two connecting arms 141 which are arranged in parallel and at intervals, and first connecting pins 142, second connecting pins 143 and third connecting pins 144 which are arranged at intervals along the length direction of the connecting arms 141 and are all inserted through the two connecting arms 141. The hinge seat 13, the support member 15 and the hinge portion 1222 are all clamped between the two connecting arms 141. The first connecting pin 142 is inserted through the hinge seat 13, the second connecting pin 143 is inserted through the support member 15, and the third connecting pin 144 is inserted through the hinge portion 1222.

[0031] Specifically, the connecting rod 14 is respectively clamped on the opposite sides of the hinge seat 13, the support member 15 and the hinge portion 1222 through the two connecting arms 141, and the two connecting arms 141 are connected to the hinge seat 13 as a whole through the first connecting pin 142, the two connecting arms 141 are connected to the support member 15 as a whole through the second connecting pin 143, and the two connecting arms 141 are connected to the hinge portion 1222 as a whole through the third connecting pin 144, so as to realize three hinge installations respectively. The two connecting arms 141 can be used for clamping and limiting, improving the installation stability, and the structural strength can also be improved through the two connecting arms 141 and the force can be ensured to be uniform, so as to improve the support effect and vibration damping effect of the support member 15.

[0032] Preferably, the first end of the support member 15 is hinged to the middle of the connecting rod 14 through the second connecting pin 143. The second end of the support member 15 extends upward and is provided with a plurality of connecting holes 151 at intervals along the length direction of the connecting rod 14. The connecting holes 151 are used for connecting with an aeroengine. Since the support member 15 is hinged to the connecting rod 14, it can adaptively rotate to different installation angles, so that the connecting holes 151 are adapted to the installation positions on the aeroengine, and the stress can be released through the rotation action of the support member 15 during the vibration damping process, avoiding the generation of stress at the installation position of the aeroengine.

[0033] Further, a positioning pin 131 and a plurality of mounting holes 132 arranged around the positioning pin 131 are provided on the bottom surface of the hinge seat 13. The positioning pin 131 is used to be inserted into a preset pin hole in the support base 11 to realize pre-positioning of the hinge seat 13. The mounting holes 132 are used to pass through bolts and connect with preset openings on the support base 11 through the bolts to realize locking and fixing of the hinge seat 13. Through the cooperation of the positioning pin 131 and the mounting holes 132, high-precision positioning and high-strength fixing of the hinge seat 13 can be achieved, ensuring the stability of the hinge seat 13.

[0034] Further, the upper end of the hinge seat 13 is provided with a triangular structure that gradually narrows in the upward direction. The first end of the connecting rod 14 is hinged to the vertex position of the triangular structure, and the connecting rod 14 is stably supported by the triangular structure.

[0035] Please refer to Figure 1 and Figure 5 , the support base 11 includes a first adjusting seat 111, a second adjusting seat 112 and a positioning component 113. A first inclined surface 1111 is provided on the top surface of the first adjusting seat 111. A second inclined surface 1121 is provided on the bottom surface of the second adjusting seat 112. The second adjusting seat 112 is arranged above the first adjusting seat 111 and abuts and fits against the first inclined surface 1111 through the second inclined surface 1121, so that the top surface of the second adjusting seat 112 is in a horizontal state. The second adjusting seat 112 is used to move along the inclined direction of the first inclined surface 1111 and adjust the height of the second adjusting seat 112 through the cooperation of the first inclined surface 1111 and the second inclined surface 1121. The positioning component 113 is connected to the second adjusting seat 112 and is used to lock and fix the second adjusting seat 112 after the height of the second adjusting seat 112 is adjusted. The elastic support component 12 and the hinge seat 13 are both arranged on the second adjusting seat 112.

[0036] Specifically, the first adjusting seat 111 supports and fixes the second adjusting seat 112 through the cooperation of the first inclined surface 1111 and the second inclined surface 1121, ensuring a large contact area between the first adjusting seat 111 and the second adjusting seat 112, guaranteeing the support strength and stability of the second adjusting seat 112, and at the same time enabling the top surface of the second adjusting seat 112 to be in a horizontal state, facilitating the arrangement of the elastic support assembly 12, the hinge seat 13, the connecting rod 14, and the support member 15. More importantly, by translating the second adjusting seat 112 along the inclination direction of the first inclined surface 1111, the height of the second adjusting seat 112 can also be adjusted by the cooperation of the first inclined surface 1111 and the second inclined surface 1121, thereby adjusting the installation heights of the elastic support assembly 12, the hinge seat 13, the connecting rod 14, and the support member 15 to meet different support height requirements.

[0037] Preferably, the support base 11 further includes a support plate 114, a limiting plate 115, and an adjusting screw rod 116. The support plate 114 is provided with a slide rail 1141 along the connection line direction of the two hinge seats 13. The slide rail 1141 can be specifically set as a groove or a rib. The first adjusting seat 111 is slidably arranged on the slide rail 1141. The limiting plate 115 is arranged at at least one end of the slide rail 1141 and is used to abut against the first adjusting seat 111 to limit the sliding stroke of the first adjusting seat 111 along the slide rail 1141. The adjusting screw rod 116 is arranged along the length direction of the slide rail 1141. The first end of the adjusting screw rod 116 is rotatably installed on the first adjusting seat 111 and is axially fixed relative to the first adjusting seat 111. The second end of the adjusting screw rod 116 is in threaded connection with an adjusting screw hole preset on the limiting plate 115. The adjusting screw rod 116 is used to be driven to rotate and drive the first adjusting seat 111 to translate and adjust its position along the slide rail 1141 through threaded cooperation. In the support base 11, driving the first adjusting seat 111 to translate along the slide rail 1141 by the adjusting screw rod 116 can horizontally move and adjust the support position of the support member 15, facilitating the offset of the aeroengine and improving the disassembly and assembly convenience. Moreover, while installing the adjusting screw rod 116 through the limiting plate 115, the moving stroke of the first adjusting seat 111 can also be limited to prevent the first adjusting seat 111 from moving too much and affecting the assembly accuracy.

[0038] Such as Figure 5As shown, the positioning component 113 includes a first positioning bolt 1131 arranged vertically and a first positioning nut 1132 threadedly connected to the first positioning bolt 1131. A first positioning hole 1112 is formed in the first adjusting seat 111. The second adjusting seat 112 is provided with a waist-shaped hole 1122 along the inclination direction of the first inclined surface 1111. The first end of the first positioning bolt 1131 is rotatably connected to the first adjusting seat 111 and axially fixed relative to the first adjusting seat 111. The second end of the first positioning bolt 1131 passes through the first positioning hole 1112 and the waist-shaped hole 1122 in sequence. The first positioning nut 1132 is arranged at one end of the first positioning bolt 1131 that passes out of the waist-shaped hole 1122 and is used to press against the upper surface of the second adjusting seat 112.

[0039] During use, loosening the first positioning nut 1132 can release the pressing and positioning effect on the second adjusting seat 112. At this time, the second adjusting seat 112 can be moved along the first inclined surface 1111 to adjust the height, and move along the first positioning bolt 1131 through the waist-shaped hole 1122. After the height adjustment is completed, tightening the first positioning nut 1132 can press and fix the second adjusting seat 112 on the first adjusting seat 111, realizing the locking and fixing of the second adjusting seat 112. The locking structure is simple and efficient.

[0040] Please refer to Figure 2 and Figure 5 , one end of the first adjusting seat 111 in its width direction is provided with a first positioning plate 1113. The first inclined surface 1111 is provided with a notch exposing the first positioning plate 1113. The second adjusting seat 112 is provided with a second positioning plate 1123 facing the first positioning plate 1113. The first positioning plate 1113 and the second positioning plate 1123 are both arranged vertically. The second adjusting seat 112 is used to adjust the distance between the second positioning plate 1123 and the first positioning plate 1113 when moving relative to the first inclined surface 1111. The positioning component 113 further includes a second positioning bolt 1133 that passes through the first positioning plate 1113 and the second positioning plate 1123 in sequence in the horizontal direction and locks and fixes the first positioning plate 1113 and the second positioning plate 1123.

[0041] Specifically, the first positioning plate 1113 and the second positioning plate 1123 are arranged along the inclination direction of the first inclined surface 1111. When the second adjusting seat 112 moves along the first inclined surface 1111 to adjust the height, the distance between the second positioning plate 1123 and the first positioning plate 1113 will change synchronously. After the adjustment is completed, the first positioning plate 1113 and the second positioning plate 1123 are locked and fixed by the second positioning bolt 1133, so as to strengthen the fixation of the second adjusting seat 112 in the horizontal direction.

[0042] Furthermore, the positioning assembly 113 further includes a second positioning nut 1134. The second positioning nut 1134 is threadedly connected to the second positioning bolt 1133, and the first positioning plate 1113 and the second positioning plate 1123 are clamped and fixed through their cooperation, and the locking and positioning structure is simple and efficient.

[0043] Preferably, the second positioning bolt 1133 is arranged in the middle of the first adjusting seat 111 along the length direction. There are two first positioning bolts 1131, and the two first positioning bolts 1131 are arranged on the opposite sides of the second positioning bolt 1133 along the length direction of the first adjusting seat 111. The second adjusting seat 112 is positioned and fixed from multiple directions through the cooperation of the two first positioning bolts 1131 and the second positioning bolt 1133, effectively improving the stability of the second adjusting seat 112 and avoiding loosening.

[0044] As Figure 2 shown, the support base 11 further includes a column 117 and a mounting plate 118 arranged on the upper surface of the second adjusting seat 112. The column 117 is arranged between the second adjusting seat 112 and the mounting plate 118 and supports and fixes the mounting plate 118. A plurality of columns 117 are arranged at intervals along the length direction of the second adjusting seat 112. The elastic support assembly 12, the hinge seat 13, the connecting rod 14 and the support member 15 are all arranged on the mounting plate 118. The mounting plate 118 is supported to a preset height position by the column 117, while ensuring the support stability and meeting the support height requirements of the aeroengine.

[0045] As Figure 1 shown, as a second aspect, the present invention further provides an aeroengine test bench 1000, including the above-mentioned aeroengine elastic support device 1. The aeroengine test bench 1000 elastically supports the aeroengine through the aeroengine elastic support device 1, and can effectively eliminate the vibration, stress and micro-deformation caused by thermal expansion during the test, ensuring the safe and stable progress of the aeroengine test.

[0046] Furthermore, the aero-engine test bed 1000 further includes a bottom plate 2, two support columns 3 provided at the front end of the bottom plate 2 and disposed on opposite sides of the bottom plate 2, and a mounting section 4 provided on the support columns 3. The mounting sections 4 on the two support columns 3 are oppositely arranged and are used to connect to opposite sides of the accessory drive casing of the aero-engine; the aero-engine elastic support device 1 is installed at the rear end of the bottom plate 2 and is used to connect to the turbine casing of the aero-engine. The aero-engine is supported by the cooperation of the aero-engine elastic support device 1 and the two support columns 3, and the working vibration, stress and thermal expansion of the turbine casing are eliminated through the aero-engine elastic support device 1, improving the test effect.

[0047] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. An elastic support device for an aeroengine, characterized in that, It includes a support base (11), an elastic support assembly (12) provided on the support base (11), two hinge seats (13) respectively provided on opposite sides of the elastic support assembly (12), and a connecting rod (14) spanning between the hinge seats (13) and the elastic support assembly (12); there are two connecting rods (14), the first ends of the two connecting rods (14) are respectively and correspondingly hinged to the two hinge seats (13), the second ends of the two connecting rods (14) are both hinged to the elastic support assembly (12) and are elastically supported and fixed upward in the vertical direction by the elastic support assembly (12), support members (15) are respectively provided in the middle of the two connecting rods (14), and the support members (15) on the two connecting rods (14) are respectively used to support different positions of the aeroengine.

2. The elastic support device for an aeroengine according to claim 1, wherein The elastic support assembly (12) includes a compression spring (121) arranged vertically, a pressing plate (122) that presses the compression spring (121) onto the support base (11) from above the compression spring (121), and a connecting bolt (123) sequentially passing through the pressing plate (122) and the compression spring (121) and connecting to the support base (11); The pressing plate (122) is provided with through holes (1221) for the connecting bolts (123) to pass through, and two hinge portions (1222) are provided on the top surface of the pressing plate (122), and the two hinge portions (1222) are symmetrically arranged on opposite sides of the through hole (1221) relative to the axis of the through hole (1221), and the second ends of the two connecting rods (14) are respectively and correspondingly hinged to the two hinge portions (1222).

3. The elastic support device for an aero-engine according to claim 2, characterized in that The connecting rod (14) includes two connecting arms (141) arranged in parallel and at intervals, and a first connecting pin (142), a second connecting pin (143) and a third connecting pin (144) arranged along the length direction of the connecting arms (141) and all passing through the two connecting arms (141), the hinge seat (13), the support member (15) and the hinge portion (1222) are all clamped between the two connecting arms (141), the first connecting pin (142) passes through the hinge seat (13), the second connecting pin (143) passes through the support member (15), and the third connecting pin (144) passes through the hinge portion (1222).

4. The elastic support device for an aeroengine according to claim 1, characterized in that, The first end of the support member (15) is hinged to the middle of the connecting rod (14), the second end of the support member (15) extends upward and is provided with a plurality of connecting holes (151) arranged at intervals along the length direction of the connecting rod (14), and the connecting holes (151) are used to connect to the aeroengine.

5. The elastic support device for an aeroengine according to claim 1, characterized in that The support base (11) includes a first adjustment seat (111), a second adjustment seat (112) and a positioning component (113). The top surface of the first adjustment seat (111) is provided with a first inclined surface (1111), and the bottom surface of the second adjustment seat (112) is provided with a second inclined surface (1121). The second adjustment seat (112) is arranged above the first adjustment seat (111) and abuts against and fits the first inclined surface (1111) through the second inclined surface (1121). The second adjustment seat (112) is used to move along the inclination direction of the first inclined surface (1111) and adjust the height of the second adjustment seat (112) through the cooperation of the first inclined surface (1111) and the second inclined surface (1121). The positioning component (113) is connected to the second adjustment seat (112) and is used to lock and fix the second adjustment seat (112) after the height of the second adjustment seat (112) is adjusted. The elastic support component (12) and the hinge seat (13) are both arranged on the second adjustment seat (112).

6. The elastic support device for an aeroengine according to claim 5, characterized in that, The support base (11) further includes a support plate (114), a limit plate (115) and an adjustment screw rod (116). The support plate (114) is provided with a slide rail (1141) along the connection direction of the two hinge seats (13). The first adjustment seat (111) is slidably arranged on the slide rail (1141). The limit plate (115) is arranged at at least one end of the slide rail (1141) and is used to abut against the first adjustment seat (111) to limit the sliding stroke of the first adjustment seat (111) along the slide rail (1141). The first end of the adjustment screw rod (116) is rotatably installed on the first adjustment seat (111) and is axially fixed relative to the first adjustment seat (111). The second end of the adjustment screw rod (116) is in threaded connection with an adjustment screw hole preset on the limit plate (115). The adjustment screw rod (116) is used to be driven to rotate and drive the first adjustment seat (111) to translate and adjust the position along the slide rail (1141) through threaded cooperation when rotating.

7. The elastic support device for an aeroengine according to claim 5, characterized in that, The positioning component (113) includes a first positioning bolt (1131) arranged vertically and a first positioning nut (1132) threadedly connected to the first positioning bolt (1131). A first positioning hole (1112) is formed on the first adjustment seat (111). The second adjustment seat (112) is provided with an oblong hole (1122) along the inclination direction of the first inclined surface (1111). The first end of the first positioning bolt (1131) is rotatably connected to the first adjustment seat (111) and is axially fixed relative to the first adjustment seat (111). The second end of the first positioning bolt (1131) sequentially passes through the first positioning hole (1112) and the oblong hole (1122). The first positioning nut (1132) is arranged at one end of the first positioning bolt (1131) passing through the oblong hole (1122) and is used to abut against the upper surface of the second adjustment seat (112).

8. The elastic support device for an aeroengine according to claim 7, wherein One end of the first adjusting seat (111) in its width direction is provided with a first positioning plate (1113). The first inclined surface (1111) is provided with a notch exposing the first positioning plate (1113). The second adjusting seat (112) is provided with a second positioning plate (1123) facing the first positioning plate (1113). Both the first positioning plate (1113) and the second positioning plate (1123) are arranged in the vertical direction. The second adjusting seat (112) is used to adjust the distance between the second positioning plate (1123) and the first positioning plate (1113) when moving relative to the first inclined surface (1111). The positioning component (113) further includes a second positioning bolt (1133) horizontally passing through the first positioning plate (1113) and the second positioning plate (1123) in sequence and locking and fixing the first positioning plate (1113) and the second positioning plate (1123).

9. The elastic support device for an aeroengine according to claim 8, wherein, The second positioning bolt (1133) is arranged at the middle of the first adjusting seat (111). There are two first positioning bolts (1131). The two first positioning bolts (1131) are respectively arranged on opposite sides of the second positioning bolt (1133) along the length direction of the first adjusting seat (111).

10. An aeroengine test bench, characterized in that, Comprising the aero-engine elastic support device according to any one of claims 1 to 9.

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