Aeroengine elastic support device and aeroengine test bench

Abstract

The present invention discloses an aircraft engine elastic support device and an aircraft engine test bench, wherein the aircraft engine elastic support device includes a support base, an elastic support assembly provided on the support base, two hinged seats provided on opposite sides of the elastic support assembly, and a connecting rod spanning the hinged seat and the elastic support assembly; the connecting rods are provided with two, the first ends of the two connecting rods are hinged to the two hinged seats in a one-to-one correspondence, the second ends of the two connecting rods are hinged to the elastic support assembly and are elastically supported and fixed vertically upward by the elastic support assembly, the middle parts of the two connecting rods are provided with support members, and the support members on the two connecting rods are respectively used to support different positions of the aircraft engine. The aircraft engine elastic support device provided by the present invention can effectively eliminate the vibration, stress and micro-deformation caused by thermal expansion generated by the aircraft engine during the test process, and has a good vibration reduction effect.

Description

Technical Field

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

[0002] Currently, due to the high speed, high thermal parameters, high power-to-weight ratio, long life, low fuel consumption, and high reliability characteristics of turboshaft engines, a large number of new technologies, new structures, new materials, and new processes are being adopted in the design and manufacture of aircraft engines. Consequently, extensive verification testing is required to verify the engine's parameters, performance, and reliability. According to statistics, the development of a new turboshaft engine requires over 10,000 hours of full-machine testing. Full-machine testing is crucial to determine the compatibility of the overall structure and performance, the interaction between engine components, and changes in engine performance and stability caused by changes in external conditions. The service life of the entire engine and its various structural components also requires extensive full-machine testing. However, the support structures of existing test benches typically serve only to secure the aircraft engine, resulting in large installation and commissioning errors and difficulty in movement. These structures are unable to reduce vibration or eliminate micro-deformations caused by thermal expansion.

[0003] In this regard, Chinese utility model patent CN211504670U provides an aircraft engine test bench, which includes a shock-absorbing seat, the upper end of which is connected to a fixed seat, fixed frames installed on both sides of the upper end of the fixed seat, and protective frames installed on the sides of the fixed frames. The aircraft engine test bench is equipped with a shock-absorbing seat for shock absorption. Two sets of shock-absorbing cylinders are provided at the upper ends of the first support plate and the second support plate for buffering and shock absorption. Shock-absorbing rubber is used between the two aluminum alloy support columns for buffering and shock absorption. Shock-absorbing springs are used for spring shock absorption. Multiple shock absorption effectively improves the shock absorption effect. However, since the shock-absorbing seat is also equipped with a fixed seat, a fixed frame, and a protective frame, the load on the shock-absorbing seat is relatively large, affecting the vibration absorption effect. It also causes the fixed seat, fixed frame, and protective frame to resonate and swing left and right as a whole, affecting the installation stability of the aircraft engine. Summary of the Invention

[0004] The present invention primarily provides an elastic support device for an aero-engine to solve the technical problem that existing aero-engine test benches cannot achieve a good vibration reduction effect.

[0005] The present invention also provides an aero-engine test bench, which adopts the aero-engine elastic support device.

[0006] According to one aspect of the present invention, there is provided an elastic support device for an aircraft engine, comprising a support base, an elastic support assembly arranged on the support base, two hinged seats arranged on opposite sides of the elastic support assembly, and a connecting rod spanning the hinged seat and the elastic support assembly; the connecting rods are provided with two, the first ends of the two connecting rods are hinged to the two hinged seats in a one-to-one correspondence, the second ends of the two connecting rods are hinged to the elastic support assembly and are elastically supported and fixed vertically upward by the elastic support assembly, the middle parts of the two connecting rods are provided with support members, and the support members on the two connecting rods are respectively used to support different positions of the aircraft engine.

[0007] Preferably, the elastic support assembly includes a compression spring arranged vertically, a pressure plate that presses the compression spring against the support base from above the compression spring, and a connecting bolt that is sequentially passed through the pressure plate and the compression spring and connected to the support base; a through hole is provided on the pressure plate for the connection bolt to pass through, and two hinge parts are provided on the top surface of the pressure plate, and the two hinge parts are symmetrically arranged on opposite sides of the through hole relative to the axis of the through hole, and the second ends of the two connecting rods are hinged to the two hinge parts one by one.

[0008] Preferably, the connecting rod includes two connecting arms that are parallel and spaced apart, 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 are all passed through the two connecting arms. The hinge seat, the support member and the hinge part are all clamped between the two connecting arms, the first connecting pin is passed through the hinge seat, the second connecting pin is passed through the support member, and the third connecting pin is passed through the hinge part.

[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 spaced along the length direction of the connecting rod, and the connecting holes are used to connect to the aircraft engine.

[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 provided above the first adjustment seat and abuts 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 second adjustment seat adjusts its height, and the elastic support assembly and the hinged seat are both provided on the second adjustment seat.

[0011] Preferably, the support base also includes a support plate, a limit plate and an adjusting screw, the support plate is provided with a slide rail along the connecting line direction of the two hinged seats, the first adjusting seat is slidably provided on the slide rail, the limit plate is provided at at least one end of the slide rail and is used to abut 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 can be rotatably mounted on the first adjusting seat and axially fixed relative to the first adjusting seat, the second end of the adjusting screw is threadedly connected to the adjusting screw hole preset on the limit plate, and the adjusting screw 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 when rotating.

[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 opened on the first adjustment seat, and a waist-shaped hole is opened on the second adjustment seat along the inclination direction of the first inclined surface. The first end of the first positioning bolt is rotatably connected to the first adjustment seat and is axially fixed relative to the first adjustment seat, the second end of the first positioning bolt is sequentially passed through the first positioning hole and the waist-shaped hole, and the first positioning nut is arranged on the end of the first positioning bolt that passes through the waist-shaped hole and is used to tighten the upper surface of the second adjustment seat.

[0013] Preferably, the first adjustment seat is provided with a first positioning plate at one end along its width direction, the first inclined surface is provided with a notch exposing the first positioning plate, the second adjustment seat is provided with a second positioning plate facing the first positioning plate, the first positioning plate and the second positioning plate are both arranged in the vertical direction, and the second adjustment 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, and the positioning assembly also includes a second positioning bolt which is sequentially passed through the first positioning plate and the second positioning plate in the horizontal direction and locks the first positioning plate and the second positioning plate.

[0014] Preferably, the second positioning bolt is provided in the middle of the first adjustment seat, and two first positioning bolts are provided, and the two first positioning bolts are provided on opposite sides of the second positioning bolt along the length direction of the first adjustment seat.

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

[0016] The present invention has the following beneficial effects:

[0017] In the elastic support device for an aircraft engine provided by the present invention, two connecting rods are connected into a whole by an elastic support assembly and the second ends of the two connecting rods are elastically supported and fixed at the same time, so that the two connecting rods can swing up and down around the corresponding hinged seat, and the support members on the two connecting rods respectively support different positions of the aircraft engine, thereby realizing elastic support and fixation of the aircraft engine. When the aircraft engine generates micro-deformations caused by vibration, stress and thermal expansion during the test, the elastic deformation of the elastic support assembly can allow the connecting rod to swing at a corresponding angle to eliminate the micro-deformations, thereby ensuring the safe and stable conduct of the aircraft engine test. The overall structure is simple and efficient, and compared with the annular support structure, it is more convenient to disassemble and adjust the installation position of the aircraft engine. In addition, since the elastic support force of the elastic support assembly can directly act on the aircraft engine through the cooperation of the two connecting rods and the support member, there is no need to set a large fixed seat in the middle, and the vibration reduction effect is better. More importantly, by using an elastic support component to elastically support and fix the two connecting rods at the same time, the forces on the two connecting rods can be balanced, so that the supports on the two connecting rods remain in a centered state to stably fix the aircraft engine. The swing amplitudes of the two connecting rods can be consistent and the swing directions can be opposite, which can offset each other's stress and effectively improve the vibration reduction effect.

[0018] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0020] Figure 1 A schematic structural diagram of an aero-engine test bench provided in an embodiment of the present invention;

[0021] Figure 2 for Figure 1 A front view of an aero-engine elastic support device in an aero-engine test bench is shown;

[0022] Figure 3 for Figure 2 A three-dimensional view of the elastic support assembly in the elastic support device of the aircraft engine shown;

[0023] Figure 4 for Figure 2 The assembly structure diagram of the hinge seat, connecting rod and support member in the elastic support device of the aircraft engine shown;

[0024] Figure 5 for Figure 2The cross-sectional structure diagram of the support base in the aircraft engine elastic support device is shown.

[0025] Legend:

[0026] 1000. Aircraft engine test bench;

[0027] 1. Aircraft engine elastic support device; 11. Support base; 111. First adjustment seat; 1111. First inclined surface; 1112. First positioning hole; 1113. First positioning plate; 112. Second adjustment seat; 1121. Second inclined surface; 1122. Waist-shaped hole; 1123. Second positioning plate; 113. Positioning assembly; 1131. First positioning bolt; 1132. First positioning nut; 1133. Second positioning bolt; 1134. Second positioning nut; 114. Support plate; 1141. Slide rail; 115. Limit plate ; 116, adjusting screw; 117, column; 118, mounting plate; 12, elastic support assembly; 121, compression spring; 122, pressure plate; 1221, through hole; 1222, hinged portion; 1223, sleeve; 123, connecting bolt; 124, connecting nut; 125, abutment plate; 13, hinged 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;

[0028] 2. Base plate; 3. Support column; 4. Installation section. DETAILED DESCRIPTION

[0029] The following detailed description of embodiments of the present invention is provided in conjunction with the accompanying drawings. However, the present invention may be implemented in a variety of different ways as defined and covered below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are illustrative and are intended only to explain the present invention and are not to be construed as limiting the present invention.

[0030] Those skilled in the art will understand that, unless expressly stated otherwise, the term "comprising" used in the description of the present invention refers to the presence of the features, integers, steps, operations, parts and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, parts, components and / or combinations thereof. It should be understood that when we refer to a component as being "connected" to another component, it can be directly connected to the other component or connected through an intermediate component. The term "and / or" used here includes all or any unit and all combinations of one or more associated listed items. The terms "first" and "second" and the like in the description and claims of the present invention are used to distinguish different objects, rather than to describe a specific order.

[0031] Figures 1 to 5 The figures collectively show an elastic support device for an aircraft engine provided by an embodiment of the present invention, which is used to be arranged on an aircraft engine test bench and support a local position of the aircraft engine. It can effectively eliminate the working vibration, stress and thermal expansion of the aircraft engine during the test, ensuring that the aircraft engine test is carried out safely and stably.

[0032] Please combine Figure 1 and Figure 2 The aircraft engine elastic support device 1 includes a support base 11, an elastic support assembly 12, two hinged 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 of the support base 11, and the two hinged seats 13 are arranged on 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 hinged to the two hinged seats 13 one by one, and the second ends of the two connecting rods 14 are hinged to the elastic support assembly 12 and are elastically supported and fixed vertically upward by the elastic support assembly 12, that is, the connecting rod 14 is spanned between the hinged seat 13 and the elastic support assembly 12, and the two support members 15 are arranged one by one in the middle of the two connecting rods 14. The support members 15 on the two connecting rods 14 are respectively used to support different positions of the aircraft engine.

[0033] In the elastic support device 1 of the aircraft engine, the two connecting rods 14 are connected into a whole by the elastic support component 12 and the second ends of the two connecting rods 14 are elastically supported and fixed at the same time, so that the two connecting rods 14 can swing up and down around the corresponding hinge seat 13, and the support members 15 on the two connecting rods 14 respectively support different positions of the aircraft engine, thereby realizing elastic support and fixation of the aircraft engine. When the aircraft engine generates micro-deformation caused by vibration, stress and thermal expansion during the test, the elastic deformation of the elastic support component 12 can allow the connecting rod 14 to swing at a corresponding angle to eliminate it, thereby ensuring the safe and stable conduct of the aircraft engine test. The overall structure is simple and efficient. Compared with the annular support structure, it is more convenient to disassemble and adjust the installation position of the aircraft engine. In addition, since the elastic supporting force of the elastic support component 12 can directly act on the aircraft engine through the cooperation of the two connecting rods 14 and the support member 15, there is no need to set a large fixed seat in the middle, and the vibration reduction effect is better. More importantly, by using an elastic support component 12 to elastically support and fix the two connecting rods 14 at the same time, the forces on the two connecting rods 14 can be balanced, so that the support members 15 on the two connecting rods 14 remain in a centered state to stably fix the aircraft engine. The two connecting rods 14 can also have the same swing amplitude and opposite swing directions, which can offset each other's stress and effectively improve the vibration reduction effect.

[0034] Please combine 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 the top end of the compression spring 121 and 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 that the pressure plate 122 is locked and fixed by the connecting bolt 123 and the compression spring 121 is radially limited. The connection structure is simple and efficient. The pressure plate 122 can be raised and lowered by adjusting the locking height of the connecting bolt 123, thereby flexibly adjusting the compression amount of the compression spring 121 to meet the elastic support requirements of different specifications.

[0035] Preferably, the pressure plate 122 is provided with a through hole 1221 for the connecting bolt 123 to pass through, and the top surface of the pressure plate 122 is provided with two hinged portions 1222, which are symmetrically arranged on 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 hingedly connected to the two hinged portions 1222 in a one-to-one correspondence. That is, the two connecting rods 14 are symmetrically arranged along the axis of the compression spring 121, so that the downward force exerted on the two connecting rods 14 can be evenly transmitted to the compression spring 121, thereby preventing the compression spring 121 from tilting toward one of the connecting rods 14. Secondly, since the second ends of the two connecting rods 14 are installed through different hinge parts 1222 respectively, the hinge positions of the two connecting rods 14 are staggered, which makes assembly more convenient and can also stagger the elastic positions of the two connecting rods 14, thereby avoiding mutual constraints between the two connecting rods 14 and allowing the two connecting rods 14 to swing slightly in the horizontal direction, further improving the vibration reduction effect.

[0036] Furthermore, a sleeve 1223 is provided on the top surface of the pressure plate 122, and the through hole 1221 is opened in the sleeve 1223 along the axial direction of the sleeve 1223. The two hinged parts 1222 are arranged on opposite sides of the sleeve 1223 and are integrally formed with the sleeve 1223. The two hinged parts 1222 are strengthened and fixed by the sleeve 1223 to avoid breakage of the two hinged parts 1222.

[0037] Furthermore, the elastic support assembly 12 also includes a connecting nut 124, which is threadedly connected to the connecting bolt 123 and pressed against the top 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.

[0038] Furthermore, the elastic support assembly 12 also includes an abutment plate 125, which is arranged 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 abutment 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.

[0039] Please combine Figure 2 and Figure 4The connecting rod 14 includes two parallel and spaced connecting arms 141, and a first connecting pin 142, a second connecting pin 143 and a third connecting pin 144 which are spaced along the length direction of the connecting arms 141 and are all passed through the two connecting arms 141. The hinge seat 13, the support member 15 and the hinge part 1222 are all clamped between the two connecting arms 141, the first connecting pin 142 is passed through the hinge seat 13, the second connecting pin 143 is passed through the support member 15, and the third connecting pin 144 is passed through the hinge part 1222.

[0040] Specifically, the connecting rod 14 is clamped on opposite sides of the hinge seat 13, the support member 15 and the hinge part 1222 through 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 part 1222 as a whole through the third connecting pin 144, thereby realizing three-point hinged installation respectively. The two connecting arms 141 can be used for clamping and limiting to improve the installation stability, and the two connecting arms 141 can also improve the structural strength and ensure uniform force, thereby improving the supporting effect and vibration reduction effect of the support member 15.

[0041] Preferably, the first end of the support member 15 is hingedly connected to the middle portion of the connecting rod 14 via 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 spaced apart along the length of the connecting rod 14. These connecting holes 151 are used for connection to the aircraft engine. Because the support member 15 is hingedly connected to the connecting rod 14, it can adaptively rotate to different installation angles, allowing the connecting holes 151 to adapt to the mounting position on the aircraft engine. The rotation of the support member 15 can also release stress during vibration reduction, thereby preventing stress from being generated at the mounting position of the aircraft engine.

[0042] Furthermore, 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 articulated seat 13. The positioning pin 131 is used to be inserted into the pin hole preset on the support base 11 to achieve pre-positioning of the articulated seat 13. The mounting hole 132 is used to pass a bolt and connect with the preset opening on the support base 11 through the bolt to achieve locking and fixation of the articulated seat 13. The cooperation between the positioning pin 131 and the mounting hole 132 can achieve high-precision positioning and high-strength fixation of the articulated seat 13, thereby ensuring the stability of the articulated seat 13.

[0043] Furthermore, the upper end of the hinge seat 13 is configured as a triangular structure that gradually narrows in an upward direction, and the first end of the connecting rod 14 is hinged to the top corner of the triangular structure, so that the connecting rod 14 is stably supported by the triangular structure.

[0044] Please combine Figure 1 and Figure 5 The support base 11 includes a first adjustment seat 111, a second adjustment seat 112 and a positioning assembly 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 the first inclined surface 1111 through the second inclined surface 1121, so that the top surface of the second adjustment seat 112 is in a horizontal state. 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 assembly 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 assembly 12 and the hinged seat 13 are both arranged on the second adjustment seat 112.

[0045] Specifically, the first adjustment seat 111 supports and fixes the second adjustment 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 adjustment seat 111 and the second adjustment seat 112, ensuring the support strength and stability of the second adjustment seat 112, and at the same time making the top surface of the second adjustment seat 112 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 adjustment seat 112 along the inclination direction of the first inclined surface 1111, the height of the second adjustment seat 112 can be adjusted by utilizing the cooperation of the first inclined surface 1111 and the second inclined surface 1121, thereby adjusting the installation height 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.

[0046] Preferably, the support base 11 further includes a support plate 114, a limit plate 115 and an adjusting screw 116. The support plate 114 is provided with a slide rail 1141 along the connecting line direction of the two hinged seats 13. The slide rail 1141 can be specifically provided as a groove or a convex strip. The first adjustment seat 111 can be slidably provided on the slide rail 1141. The limit plate 115 is provided at least at one end of the slide rail 1141 and is used to abut against the first adjustment seat 111 to limit the first adjustment seat 111 from sliding along the slide rail 114. 1, the adjusting screw 116 is arranged along the length direction of the slide rail 1141, the first end of the adjusting screw 116 is rotatably mounted on the first adjusting seat 111 and axially fixed relative to the first adjusting seat 111, and the second end of the adjusting screw 116 is threadedly connected to the preset adjusting screw hole on the limit plate 115. The adjusting screw 116 is used to be driven to rotate and, when rotating, drives the first adjusting seat 111 to translate and adjust its position along the slide rail 1141 through threaded engagement. In the support base 11, the first adjusting seat 111 is driven to translate along the slide rail 1141 by the adjusting screw 116, and the support position of the support member 15 can be adjusted in the horizontal direction, which facilitates the offset of the aircraft engine and improves the convenience of disassembly and assembly. In addition, when the adjusting screw 116 is installed by the limit plate 115, the moving stroke of the first adjusting seat 111 can be limited, thereby preventing the first adjusting seat 111 from moving too much and affecting the assembly accuracy.

[0047] like Figure 5 As shown, the positioning assembly 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 provided on the first adjustment seat 111, and a waist-shaped hole 1122 is provided on the second adjustment seat 112 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 is sequentially passed through the first positioning hole 1112 and the waist-shaped hole 1122. The first positioning nut 1132 is provided on one end of the first positioning bolt 1131 that passes through the waist-shaped hole 1122 and is used to tighten the upper surface of the second adjustment seat 112.

[0048] During use, loosening the first positioning nut 1132 can release the pressing and positioning effect on the second adjustment seat 112. At this time, the second adjustment 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. When the height adjustment is completed, tightening the first positioning nut 1132 can press and fix the second adjustment seat 112 on the first adjustment seat 111, thereby realizing the locking and fixation of the second adjustment seat 112. The locking structure is simple and efficient.

[0049] Please combine Figure 2 and Figure 5 The first adjustment seat 111 is provided with a first positioning plate 1113 at one end along its width direction, the first inclined surface 1111 is provided with a notch exposing the first positioning plate 1113, and the second adjustment 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 in the vertical direction, and the second adjustment 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, and the positioning assembly 113 also includes a second positioning bolt 1133 that is sequentially passed through the first positioning plate 1113 and the second positioning plate 1123 in the horizontal direction and locks the first positioning plate 1113 and the second positioning plate 1123.

[0050] 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 adjustment 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 to strengthen the fixation of the second adjustment seat 112 in the horizontal direction.

[0051] Furthermore, the positioning assembly 113 also includes a second positioning nut 1134, which is threadedly connected to the second positioning bolt 1133 and clamps the first positioning plate 1113 and the second positioning plate 1123 together through cooperation. The locking and positioning structure is simple and efficient.

[0052] Preferably, the second positioning bolt 1133 is arranged in the middle part of the first adjustment seat 111 along the length direction, and there are two first positioning bolts 1131. The two first positioning bolts 1131 are arranged on opposite sides of the second positioning bolt 1133 along the length direction of the first adjustment seat 111. Through the cooperation of the two first positioning bolts 1131 and the second positioning bolt 1133, the positioning and fixation of the second adjustment seat 112 can be achieved from multiple directions, effectively improving the stability of the second adjustment seat 112 and avoiding loosening.

[0053] like Figure 2 As shown, the support base 11 also includes a column 117 and a mounting plate 118 provided on the upper surface of the second adjustment seat 112. The column 117 is provided between the second adjustment seat 112 and the mounting plate 118 and supports and fixes the mounting plate 118. A plurality of columns 117 are provided at intervals along the length direction of the second adjustment seat 112. The elastic support assembly 12, the hinge seat 13, the connecting rod 14 and the support member 15 are all provided on the mounting plate 118. The mounting plate 118 is supported to a preset height position by the column 117, thereby ensuring support stability while meeting the support height requirements of the aircraft engine.

[0054] like Figure 1 As shown, as a second aspect, the present invention further provides an aircraft engine test bench 1000, comprising the aircraft engine elastic support device 1. The aircraft engine test bench 1000 elastically supports the aircraft engine through the aircraft engine elastic support device 1, effectively eliminating vibration, stress, and micro-deformation caused by thermal expansion during the test, thereby ensuring safe and stable aircraft engine testing.

[0055] Furthermore, the aircraft engine test bench 1000 also includes a base plate 2, two support columns 3 arranged at the front end of the base plate 2 and on opposite sides of the base plate 2, and mounting nodes 4 provided on the support columns 3. The mounting nodes 4 on the two support columns 3 are arranged opposite to each other and are used to connect with opposite sides of the accessory transmission casing of the aircraft engine; the aircraft engine elastic support device 1 is installed at the rear end of the base plate 2 and is used to connect to the turbine casing of the aircraft engine. The aircraft engine is supported by the cooperation of the aircraft engine elastic support device 1 and the two support columns 3, and the aircraft engine elastic support device 1 eliminates the working vibration, stress and thermal expansion of the turbine casing, thereby improving the test effect.

[0056] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. An elastic support device for an aircraft engine, characterized in that: The invention comprises a support base (11), an elastic support assembly (12) arranged on the support base (11), two hinged seats (13) respectively arranged on opposite sides of the elastic support assembly (12), and a connecting rod (14) spanning between the hinged seat (13) and the elastic support assembly (12); the connecting rod (14) is provided with two, the first ends of the two connecting rods (14) are hinged to the two hinged seats (13) in a one-to-one correspondence, the second ends of the two connecting rods (14) are hinged to the elastic support assembly (12) and are elastically supported and fixed in a vertically upward direction by the elastic support assembly (12), the middle parts of the two connecting rods (14) are provided with a support member (15), and the support members (15) on the two connecting rods (14) are respectively used to support different positions of the aircraft engine; The elastic support assembly (12) includes a compression spring (121) arranged vertically, a pressure plate (122) for pressing the compression spring (121) onto the support base (11) from above the compression spring (121), and a connecting bolt (123) that is sequentially passed through the pressure plate (122) and the compression spring (121) and connected to the support base (11); The pressure plate (122) is provided with a through hole (1221) for the connecting bolt (123) to pass through, and the top surface of the pressure plate (122) is provided with two hinged parts (1222). The two hinged parts (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 hinged to the two hinged parts (1222) in a one-to-one correspondence.

2. The elastic support device for an aircraft engine according to claim 1, characterized in that: The connecting rod (14) includes two connecting arms (141) that are parallel and spaced apart, and a first connecting pin (142), a second connecting pin (143) and a third connecting pin (144) that are arranged along the length direction of the connecting arms (141) and are all passed 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 passed through the hinge seat (13); the second connecting pin (143) is passed through the support member (15); and the third connecting pin (144) is passed through the hinge portion (1222).

3. The elastic support device for an aircraft engine 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), and the second end of the support member (15) is extended upward and provided with a plurality of connecting holes (151) spaced apart along the length direction of the connecting rod (14). The connecting holes (151) are used for connecting to the aircraft engine.

4. The elastic support device for an aircraft engine according to claim 1, characterized in that: The support base (11) comprises a first adjustment seat (111), a second adjustment seat (112) and a positioning assembly (113); the top surface of the first adjustment seat (111) is provided with a first inclined surface (1111); 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 the first inclined surface (1111) through the second inclined surface (1121); the second adjustment seat (112) is used to The second adjustment seat (112) is moved along the inclination direction of the first inclined surface (1111) and the height of the second adjustment seat (112) is adjusted by the cooperation of the first inclined surface (1111) and the second inclined surface (1121). The positioning assembly (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 assembly (12) and the hinge seat (13) are both provided on the second adjustment seat (112).

5. The aircraft engine elastic support device according to claim 4, characterized in that: The support base (11) further comprises a support plate (114), a limit plate (115) and an adjusting screw rod (116); the support plate (114) is provided with a slide rail (1141) along the connecting line direction of the two hinge seats (13); the first adjusting seat (111) is slidably provided on the slide rail (1141); the limit plate (115) is provided at at least one end of the slide rail (1141) and is used to abut against the first adjusting seat (111) to limit the first adjusting seat (111) from sliding along the hinge seat (13); The sliding stroke of the slide rail (1141), the first end of the adjusting screw rod (116) is rotatably mounted on the first adjusting seat (111) and axially fixed relative to the first adjusting seat (111), the second end of the adjusting screw rod (116) is threadedly connected to the preset adjusting screw hole on the limit plate (115), and the adjusting screw rod (116) is used to be driven to rotate and drive the first adjusting seat (111) to translate and adjust the position along the slide rail (1141) through threaded engagement when rotating.

6. The elastic support device for an aircraft engine according to claim 4, characterized in that: The positioning assembly (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 provided on the first adjustment seat (111); a waist-shaped hole (1122) is provided on the second adjustment seat (112) along the inclination direction of the first inclined surface (1111); a 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); a second end of the first positioning bolt (1131) is sequentially passed through the first positioning hole (1112) and the waist-shaped hole (1122); the first positioning nut (1132) is provided on one end of the first positioning bolt (1131) passing through the waist-shaped hole (1122) and is used to tighten the upper surface of the second adjustment seat (112).

7. The aircraft engine elastic support device according to claim 6, characterized in that: The first adjustment seat (111) is provided with a first positioning plate (1113) at one end along the width direction thereof, the first inclined surface (1111) is provided with a notch exposing the first positioning plate (1113), the second adjustment 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 in the vertical direction, the second adjustment 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 assembly (113) also includes a second positioning bolt (1133) which is sequentially passed through the first positioning plate (1113) and the second positioning plate (1123) in the horizontal direction and locks and fixes the first positioning plate (1113) and the second positioning plate (1123).

8. The elastic support device for an aircraft engine according to claim 7, characterized in that: The second positioning bolt (1133) is arranged in the middle of the first adjustment seat (111), and two first positioning bolts (1131) are provided. The two first positioning bolts (1131) are arranged on opposite sides of the second positioning bolt (1133) along the length direction of the first adjustment seat (111).

9. An aircraft engine test bench, characterized in that: The invention comprises an elastic support device for an aircraft engine as claimed in any one of claims 1 to 8.

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