CN216284297U

CN216284297U - Test run rack for aero-engine

Info

Publication number: CN216284297U
Application number: CN202122252604.3U
Authority: CN
Inventors: 朱凤朝; 苏涵; 苏镜元; 郭霞
Original assignee: Beijing Aerospace Yisen Wind Tunnel Engineering Technology Co ltd
Current assignee: Beijing Aerospace Yisen Wind Tunnel Engineering Technology Co ltd
Priority date: 2021-09-16
Filing date: 2021-09-16
Publication date: 2022-04-12
Anticipated expiration: 2031-09-16

Abstract

The utility model provides a test run rack for aeroengine, including supporting base, backup pad and the supporting mechanism who is used for supporting aeroengine, two the backup pad sets up respectively supporting mechanism's both sides are still closed including can covering two at least part covers in the backup pad aeroengine's protection casing. The protective cover can effectively weaken huge noise caused by starting of the engine in the process of testing the engine, and can protect the hearing of workers in the field from being damaged.

Description

Test run rack for aero-engine

Technical Field

The utility model relates to an aviation test technical field especially relates to a test run rack for aeroengine.

Background

The test run bench is a special experimental device for testing and testing the reliability, durability and other performances of the engine. The aero-engine works under extremely harsh conditions of high temperature, high pressure, high rotating speed, high load and the like, and in order to ensure the reliability of the aero-engine and a system thereof, the whole machine must be tested before the delivery of the engine.

The existing test run rack has certain defects; because the engine needs to be started to work during testing, the working engine can generate larger noise, and the hearing of the personnel for assisting the experiment can be damaged if the noise reduction treatment is not carried out.

SUMMERY OF THE UTILITY MODEL

The present disclosure provides a test run rack for an aircraft engine to at least solve the above technical problems existing in the prior art.

According to the first aspect of the present disclosure, a test run rack for an aircraft engine is provided, including a support base, support plates and a support mechanism for supporting the aircraft engine, two the support plates are respectively arranged on two sides of the support mechanism, and the test run rack further includes a protective cover capable of covering two of the support plates to at least partially cover the aircraft engine.

In an implementation mode, the supporting base is further provided with a monitoring device and a flame baffle, the monitoring device comprises an installation shell, one surface of the installation shell facing the supporting mechanism, the flame baffle and the two supporting plates form an accommodating space with one open end, the supporting mechanism is arranged in the accommodating space, and the protective cover is arranged at the opening.

In an embodiment, a sound absorption layer is disposed on a side of the protective cover facing the accommodating space.

In an embodiment, the protective cover has a first length side and a second length side, the first length side and the second length side are connected through an arc-shaped side, the lengths of the first length side and the second length side are equal to the length of the support plates, and the distance between the first length side and the second length side is equal to the distance between the two support plates.

In an embodiment, the protective cover is configured as an arc-shaped structure, and the first length side and the second length side are connected through an arc-shaped side.

In one embodiment, the first length edge is movably connected with the top of one of the support plates through a hinge, and the second length edge is detachably connected with the top of the other support plate.

In an implementation manner, the supporting mechanism comprises a first supporting component and a second supporting component which have the same structure, the first supporting component and the second supporting component are arranged along the length direction of the supporting base, the first supporting component comprises two supports arranged along the width direction of the supporting base, and the distance between the two supports is adjustable.

In an implementation mode, first supporting component is still including connecting support the drive case on the base, follow in the drive case the width direction who supports the base is provided with two-way lead screw, two-way lead screw includes levogyration screw thread portion and dextrorotation screw thread portion, one the bottom threaded connection of support is in levogyration screw thread portion, another support threaded connection is in dextrorotation screw thread portion, the top of drive case is provided with spacing spout, two the support is followed spacing spout upwards wears out, just spacing spout can restrict the support is followed the length direction swing of supporting the base.

In one embodiment, one end of the bidirectional threaded spindle extends out of the drive box and is provided with a drive wheel.

In an implementation mode, one surface of the installation shell, which deviates from the accommodating space, is provided with a plurality of data display screens, and a temperature monitoring module, a pressure monitoring module and a torque monitoring module are arranged inside the installation shell.

The test run rack for the aero-engine disclosed by the invention can effectively weaken huge noise caused by starting of the engine in the process of testing the engine by using the protective cover, and can protect the hearing of workers in the field from being damaged.

It should be understood that the statements in this section do not necessarily identify key or critical features of the embodiments of the present disclosure, nor do they limit the scope of the present disclosure. Other features of the present disclosure will become apparent from the following description.

Drawings

The above and other objects, features and advantages of exemplary embodiments of the present disclosure will become readily apparent from the following detailed description read in conjunction with the accompanying drawings. Several embodiments of the present disclosure are illustrated by way of example, and not by way of limitation, in the figures of the accompanying drawings and in which:

in the drawings, the same or corresponding reference numerals indicate the same or corresponding parts.

FIG. 1 shows a schematic structural view of a test run stand for an aircraft engine in one embodiment of the present disclosure;

fig. 2 shows a schematic structural diagram of a first support assembly of one embodiment of the present disclosure.

Fig. 3 shows a schematic structural view of the sound absorption layer and the protective cover after being separated according to one embodiment of the present disclosure.

Wherein the figures include the following reference numerals:

1. a support base; 2. a support plate; 3. a support mechanism; 31. a first support assembly; 311. a support; 312. a drive box; 3121. a limiting chute; 313. a drive wheel; 32. a second support assembly; 4. a protective cover; 41. a first length edge; 42. a second length edge; 5. a monitoring device; 51. a data display screen; 6. a flame barrier; 7. and a sound absorbing layer.

Detailed Description

In order to make the objects, features and advantages of the present disclosure more apparent and understandable, the technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present disclosure, and it is apparent that the described embodiments are only a part of the embodiments of the present disclosure, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.

Referring to fig. 1, the present disclosure provides a test run rack for an aircraft engine, including a supporting base 1, supporting plates 2 and a supporting mechanism 3 for supporting the aircraft engine, wherein the two supporting plates 2 are respectively arranged at two sides of the supporting mechanism 3, a protective cover 4 capable of being covered is arranged at the top of the two supporting plates 2, and the protective cover 4 can effectively weaken the huge noise caused by the starting of the engine in the process of testing the engine, so that the hearing of workers at the site is protected from being damaged.

In the embodiment of this disclosure, still be provided with monitoring devices 5 and flame board 6 on the support base 1, monitoring devices 5 and flame board 6 set up relatively, monitoring devices is including installing the shell, be provided with a plurality of data display screen 51 on the installation shell, the inside temperature monitoring module that is provided with of installation shell, pressure monitoring module and moment of torsion monitoring module, monitoring devices 5 can be to the temperature of aeroengine during operation, aspects such as pressure and moment of torsion are monitored, and the data display record with the monitoring is on data display screen 51, look over for the tester. The one side of installation shell orientation supporting mechanism 3 and keep off flame board 6 and two backup pad 2 and enclose into open-top's accommodation space, and supporting mechanism 3 sets up in above-mentioned accommodation space, and makes protection casing 4 can cover the opening at accommodation space top to reach aeroengine when starting, its all around can both be sheltered from with the top effectively, play better noise reduction effect.

Referring to fig. 1 and 2, in the embodiment of the present disclosure, a sound absorption layer 7 is disposed on a side of the protective cover 4 facing the accommodating space, the sound absorption layer 7 is made of one or more materials selected from polyester, metal and melamine, and the sound absorption layer 7 plays a role in absorbing noise generated during operation of the aircraft engine, so as to further block a propagation path of the noise.

In the embodiment of the present disclosure, the protection cover 4 is configured to be an arc-shaped structure, the protection cover 4 has a first length edge 41 and a second length edge 42, the first length edge 41 and the second length edge 42 are connected by an arc-shaped edge, and a concave portion of the arc-shaped edge faces the accommodating space, so that the arc-shaped edge can better fit with a waveform transmitted by sound waves, and a better noise blocking effect is achieved. The lengths of the first length edge 41 and the second length edge 42 are equal to the length of the support plate 2, the distance between the first length edge 41 and the second length edge 42 is equal to the distance between the two support plates 2, and when the protective cover 4 is in a covering state, the path of noise generated between the two support plates 2 and transmitted from the top of the test bed can be effectively isolated.

In the embodiment of the present disclosure, the first length edge 41 is movably connected to the top of one of the support plates 2 through a hinge, the second length edge 42 is detachably connected to the top of the other support plate 2, the iron bar is fixedly connected to the second length edge 42, the magnetic strip is embedded in the top of the support plate 2 connected to the second length edge 42, and when the protection cover 4 is in a closed state, the iron bar is adsorbed to the magnetic strip, so that the phenomenon that the protection cover 4 moves can be avoided.

In an embodiment not shown, the second length side 42 of the hood 4 is connected to the support plate 2 by means of a snap connection.

Referring to fig. 1 and 3, in the embodiment of the present disclosure, the supporting mechanism 3 includes a first supporting component 31 and a second supporting component 32 having the same structure, the first supporting component 31 and the second supporting component 32 are disposed along the length direction of the supporting base 1, the first supporting component 31 includes two supporting seats 311 disposed along the width direction of the supporting base 1, and the distance between the two supporting seats 311 is adjustable, so as to achieve the purpose of supporting aeroengines of different models.

In the embodiment of the present disclosure, the first supporting assembly 31 further includes a driving box 312 connected to the supporting base 1, the driving box 312 is connected to the supporting base 1 by bolts, a bidirectional screw rod is disposed in the driving box 312 along the width direction of the supporting base 1, the bidirectional screw rod includes a left-handed screw portion and a right-handed screw portion, the bottom of one support 311 is screwed to the left-handed screw portion, the other support 311 is screwed to the right-handed screw portion, a limit sliding slot 3121 is disposed at the top of the driving box 312, the two supports 311 protrude upwards from the limit sliding slot 3121, the limit sliding slot 3121 can limit the support 311 from swinging along the length direction of the supporting base 1, one end of the bidirectional screw rod protrudes from the driving box 312, and a driving wheel 313 is disposed at the end, after the driving wheel 313 is rotated, the two supports 311 connected to the same bidirectional screw rod can be far away from or close to each other, so as to adjust the distance between the two supports 311, the purpose of bearing aero-engines of different models is achieved.

In the embodiment of the disclosure, a plurality of rollers are further installed at the bottom of the supporting base 1, the position of the aeroengine test bed frame of the embodiment can be moved through the rollers according to the requirement of a test scene, the operation is convenient, and the movement is labor-saving.

In the working process of the test run stand of the aero-engine of the present example, the size of the aero-engine is tested as required to respectively rotate the driving wheels 313 on the first support assembly 31 and the second support assembly 32, and the driving wheels 313 can drive the bidirectional screw to rotate after rotating, so that the two supports 311 sleeved on the bidirectional screw move relatively, the distance between the two supports 311 is enlarged or reduced, and the aero-engines of different models are supported; rotating the protective cover 4 along the hinge, and contacting the second length edge 42 of the protective cover 4 with the supporting plate 2 connected with the iron bar to achieve the purpose of shielding the aircraft engine; the sound absorption layer 7 in the protective cover 4 plays a role in absorbing noise generated when the aircraft engine works, and the transmission of the noise is reduced; after the aero-engine is fixed, the monitoring device 5 is started to work, so that the aero-engine plays a role in monitoring the temperature, the pressure, the torque and the like of the aero-engine during working, monitored data are displayed and recorded on the data display screen 51, and the data are conveniently checked by a tester.

It should be understood that various forms of the flows shown above may be used, with steps reordered, added, or deleted. For example, the steps described in the present disclosure may be executed in parallel, sequentially, or in different orders, as long as the desired results of the technical solutions disclosed in the present disclosure can be achieved, and the present disclosure is not limited herein.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present disclosure, "a plurality" means two or more unless specifically limited otherwise.

The above description is only for the specific embodiments of the present disclosure, but the scope of the present disclosure is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present disclosure, and all the changes or substitutions should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.

Claims

1. The utility model provides a test run rack for aeroengine, its characterized in that, including supporting base (1), backup pad (2) and supporting mechanism (3) that are used for supporting aeroengine, two backup pad (2) set up respectively the both sides of supporting mechanism (3), still including can cover and close two at least part covers on backup pad (2) aeroengine's protection casing (4).

2. The test run rack according to claim 1, wherein a monitoring device (5) and a flame baffle (6) are further arranged on the support base (1), the monitoring device (5) comprises a mounting shell, one surface of the mounting shell facing the support mechanism (3), the flame baffle (6) and the two support plates (2) define an accommodating space with an opening at one end, the support mechanism (3) is arranged in the accommodating space, and the protective cover (4) covers the opening.

3. The test run bench according to claim 1, characterized in that a sound absorbing layer (7) is arranged on the side of the protective cover (4) facing the receiving space.

4. The commissioning bench of claim 1, wherein the protective cover (4) has a first length side (41) and a second length side (42), the length of each of the first length side (41) and the second length side (42) being equal to the length of the support plate (2), the distance between the first length side (41) and the second length side (42) being equal to the distance between two support plates (2).

5. The test run bench according to claim 4, wherein the protective cover (4) is arranged in an arc-shaped structure, and the first length side (41) and the second length side (42) are connected through an arc-shaped side.

6. The test run bench according to claim 4, wherein the first length edge (41) is movably connected with the top of one of the support plates (2) through a hinge, and the second length edge (42) is detachably connected with the top of the other support plate (2).

7. The test-run bench according to claim 2, wherein the supporting mechanism (3) comprises a first supporting component (31) and a second supporting component (32) which have the same structure, the first supporting component (31) and the second supporting component (32) are arranged along the length direction of the supporting base (1), the first supporting component (31) comprises two supports (311) arranged along the width direction of the supporting base (1), and the distance between the two supports (311) is adjustable.

8. The test bed frame of claim 7, wherein the first support assembly (31) further comprises a drive box (312) connected to the support base (1), a bidirectional screw is arranged in the drive box (312) along the width direction of the support base (1), the bidirectional screw comprises a left-handed thread part and a right-handed thread part, one of the two-handed thread part is in threaded connection with the bottom of the support (311), the other one of the two-handed thread part is in threaded connection with the support (311), a limit sliding groove (3121) is arranged at the top of the drive box (312), the two supports (311) penetrate out of the limit sliding groove (3121) upwards, and the limit sliding groove (3121) can limit the support (311) to swing along the length direction of the support base (1).

9. The commissioning bench of claim 8 wherein one end of the bidirectional lead screw passes out of the drive box (312) and is provided with a drive wheel (313) at that end.

10. The test run rack according to claim 2, wherein a plurality of data display screens (51) are arranged on one surface of the mounting shell, which is far away from the accommodating space, and a temperature monitoring module, a pressure monitoring module and a torque monitoring module are arranged inside the mounting shell.