CN215436990U - High-strength guide wall of aircraft engine in wing test yard - Google Patents
High-strength guide wall of aircraft engine in wing test yard Download PDFInfo
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- CN215436990U CN215436990U CN202121828115.1U CN202121828115U CN215436990U CN 215436990 U CN215436990 U CN 215436990U CN 202121828115 U CN202121828115 U CN 202121828115U CN 215436990 U CN215436990 U CN 215436990U
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- 239000010959 steel Substances 0.000 claims description 6
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- 230000000694 effects Effects 0.000 description 4
- 230000003014 reinforcing Effects 0.000 description 4
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Abstract
The utility model provides a high-strength guide wall of an aircraft engine in a wing test field, which comprises a plurality of support frames arranged in parallel and a plurality of guide plates arranged in parallel, wherein each support frame comprises a longitudinal support connecting rod and a transverse support connecting rod, each guide plate comprises two support plates and a plurality of arc-shaped guide vanes, the top ends of the longitudinal support connecting rods are fixedly connected between the two adjacent support plates, and the transverse support connecting rods are fixed between the support plates and the longitudinal support connecting rods. When engine airflow passes through the arc-shaped guide vane, the airflow flow direction is changed, an area with relatively low air pressure is formed behind the guide wall, and the air speed in a certain range behind the lee side of the guide wall during airplane test can be reduced by deflecting the air direction and reducing the air speed, so that surrounding facilities are protected. The guide plate is supported through the longitudinal support connecting rods and the transverse support connecting rods, the structural stability can be enhanced, the guide wall is prevented from being damaged, and the service life is long.
Description
Technical Field
The utility model relates to the field of guide walls, in particular to a guide wall of a high-strength aircraft engine in a wing test field.
Background
The airplane test run flow guide wall is a device which can enable a test run engine to smoothly pass through airflow and change the airflow direction and effectively reduce the airflow speed when a wing is in test run, the existing test run is mostly a wind shield wall with functional products, the load to be borne is large, the wind shield wall is easy to stabilize, maintenance is frequently needed, and the maintenance difficulty is high.
Disclosure of Invention
The utility model aims to solve the problem of providing a high-strength guide wall of an aircraft engine in a wing test field, improving the stability of the guide wall, well guiding the wind direction and reducing the wind speed.
The utility model provides a guide wall of a high-strength aircraft engine on a wing test bed, which is used for solving the technical problems and comprises a plurality of support frames and a plurality of guide plates, wherein the support frames are transversely arranged in parallel, the guide plates are transversely arranged in parallel, each support frame comprises a longitudinal support connecting rod and a transverse support connecting rod, the transverse support connecting rods are vertically and fixedly connected to one side of the longitudinal support connecting rods, each guide plate comprises two support plates arranged in parallel, and a plurality of arc guide vanes arranged between two adjacent support plates in parallel, the support plates are obliquely arranged towards one side of the top ends of the longitudinal support connecting rods, the top ends of the longitudinal support connecting rods are fixedly connected between two adjacent support plates, one ends of the transverse support connecting rods are fixedly connected between two adjacent support plates, and the two adjacent support plates are fixedly connected.
Preferably, the bottom ends of the longitudinal support connecting rod and the support plate are welded with a support bottom plate, and the bottom of the support bottom plate is fixedly connected with a plurality of ground-binding reinforcing steel bars.
Preferably, a first connecting plate is welded on one side of the longitudinal support connecting rod, a second connecting plate is welded between every two adjacent support plates, and two ends of the transverse support connecting rod are respectively connected to the first connecting plate and the second connecting plate through bolts.
Preferably, a plurality of strip-shaped screw holes are arranged on the supporting plate in a penetrating mode, and every two adjacent strip-shaped screw holes are fixedly connected through bolts.
Preferably, the support plate is a steel channel.
Preferably, the distance between two adjacent arc-shaped guide vanes is 250mm-500 mm.
Preferably, the thickness of the arc-shaped guide vane is 4-10 mm.
The utility model has the beneficial effects that: the utility model provides a guide wall of a high-strength aircraft engine in a wing test field, which is provided with a unique assembly structure, wherein an arc-shaped guide blade is arranged between two adjacent support plates to form a guide plate, when engine airflow passes through the arc-shaped guide blade, the airflow flowing direction is changed, and an area with relatively low air pressure is formed behind the guide wall. Support the backup pad through vertical support connecting rod and consolidate, the horizontal support connecting rod of rethread supports between backup pad and vertical support connecting rod, plays the effect of additional strengthening stability, prevents that the guiding wall is impaired. Its simple structure, structural strength is high, and life is high, can carry out the water conservancy diversion to the wind direction well, reduces the wind speed, and the air current that produces when avoiding the aircraft to test the car causes the damage to near personnel and facility.
Drawings
Fig. 1 illustrates a schematic cross-sectional structure of the present invention.
The reference numbers illustrate: longitudinal support connecting rod 1, horizontal support connecting rod 2, backup pad 3, bar screw 30, arc guide vane 4, supporting baseplate 5, prick ground reinforcing bar 6, first connecting plate 7, second connecting plate 8.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present disclosure more apparent, the technical solutions of the embodiments of the present disclosure will be described clearly and completely with reference to the drawings of the embodiments of the present disclosure. It is to be understood that the described embodiments are only a few embodiments of the present disclosure, and not all embodiments.
All other embodiments of the person skilled in the art, which are obtained without inventive work on the basis of the described embodiments of the present disclosure, are within the scope of protection of the present disclosure.
Refer to fig. 1.
The utility model provides a guide wall of a high-strength aircraft engine in a wing test bed, which comprises a plurality of support frames and a plurality of guide plates, wherein the support frames are transversely arranged in parallel, the guide plates are transversely arranged in parallel, each support frame comprises a longitudinal support connecting rod 1 and a transverse support connecting rod 2, the transverse support connecting rods 2 are vertically and fixedly connected to one side of the longitudinal support connecting rods 1, each guide plate comprises two support plates 3 arranged in parallel and a plurality of arc-shaped guide vanes 4 arranged between two adjacent support plates 3 in parallel, the support plates 3 are obliquely arranged towards one side of the top ends of the longitudinal support connecting rods 1, the top ends of the longitudinal support connecting rods 1 are fixedly connected between two adjacent support plates 3, one ends of the transverse support connecting rods 2 are fixedly connected between two adjacent support plates 3, and two adjacent support plates 3 are fixedly connected.
The specific use principle is as follows: set up arc guide vane 4 between two adjacent backup pads 3 and form the guide plate, when engine air current passes through arc guide vane 4, the air current direction of flow produces the diversion and forms the area that atmospheric pressure is lower relatively behind the guide wall, curved guide vane compares the guide vane of straight piece, it arouses that the deflection angle of air current is bigger, thereby produce the adsorption and lead to the flow of air, can be through deflecting wind direction and reduce the wind speed, to a great extent reduces the wind speed in certain extent behind the guide wall lee face when the aircraft is tried, protect the safety of personnel, vehicle and building behind the guide wall lee face. Support the backup pad 3 that the slope set up through vertical support connecting rod 1 and consolidate, the horizontal support connecting rod 2 of rethread supports between backup pad 3 and vertical support connecting rod 1, plays the effect of additional strengthening stability, prevents that the guide wall is impaired. Its simple structure, structural strength is high, and life is high, can carry out the water conservancy diversion to the wind direction well, reduces the wind speed, and the air current that produces when avoiding the aircraft to test the car causes the damage to near personnel and facility.
Based on above-mentioned embodiment, supporting baseplate 5 has all been welded to vertical support connecting rod 1 and 3 bottoms of backup pad, and 5 bottoms fixedly connected with of supporting baseplate have a plurality of reinforcing bars 6 of pricking ground. When installing this water conservancy diversion wall, will prick ground reinforcing bar 6 and bury underground and pour cement and will prick ground reinforcing bar 6 and fix in the underground, can fix a position vertical support connecting rod 1 and backup pad 3, reinforced structure stability.
Based on the above embodiment, the first connecting plate 7 is welded on one side of the longitudinal support connecting rod 1, the second connecting plate 8 is welded between the two adjacent support plates 3, and the two ends of the transverse support connecting rod 2 are respectively connected to the first connecting plate 7 and the second connecting plate 8 through bolts. The first connecting plate 7 and the second connecting plate 8 are connected with the transverse support connecting rod 2 through bolts, so that the assembly and maintenance are easy, and the assembly position of the transverse support connecting rod 2 is convenient to adjust.
Based on the above embodiment, the support plate 3 is provided with a plurality of bar-shaped screw holes 30 in a penetrating manner, and two adjacent bar-shaped screw holes 30 are fixedly connected through bolts. Through setting up bar screw 30, can avoid the connection difficulty that two adjacent backup pads 3 and the installation height on ground lead to differently, improve assembly operability.
Based on the above embodiment, the support plate 3 is a steel trough. The steel groove has good structural strength, and 4 tip of arc guide vane can clamp on the steel groove, improve arc guide vane 4's assembly strength, improve overall structure intensity.
Based on the above embodiment, the distance between two adjacent arc guide vanes 4 is 250mm-500mm, which can guide and reduce the airflow direction well while ensuring lower resistance, and improve the airflow guiding effect.
Based on the above embodiment, the thickness of the arc-shaped guide vane 4 is 4-10mm, which can well guide the airflow direction while ensuring sufficient strength.
The above embodiments are merely illustrative of the preferred embodiments of the present invention, and not restrictive, and various changes and modifications to the technical solutions of the present invention may be made by those skilled in the art without departing from the spirit of the present invention, and the technical solutions of the present invention are intended to fall within the scope of the present invention defined by the appended claims.
Claims (7)
1. The high-strength guide wall of the aircraft engine in the wing test yard is characterized by comprising a plurality of support frames and a plurality of guide plates, wherein the support frames are transversely arranged in parallel, the guide plates are transversely arranged in parallel, each support frame comprises a longitudinal support connecting rod (1) and a transverse support connecting rod (2), the transverse support connecting rods (2) are vertically and fixedly connected to one side of the longitudinal support connecting rods (1), each guide plate comprises two support plates (3) arranged in parallel and a plurality of arc-shaped guide vanes (4) arranged between every two adjacent support plates (3), the support plates (3) are obliquely arranged towards one side of the top end of each longitudinal support connecting rod (1), the top ends of the longitudinal support connecting rods (1) are fixedly connected between every two adjacent support plates (3), one end of each transverse support connecting rod (2) is fixedly connected between every two adjacent support plates (3), two adjacent supporting plates (3) are fixedly connected.
2. The wing test bed flow guide wall of the high-strength aircraft engine according to claim 1, characterized in that a support bottom plate (5) is welded at the bottom ends of the longitudinal support connecting rod (1) and the support plate (3), and a plurality of ground penetrating steel bars (6) are fixedly connected to the bottom of the support bottom plate (5).
3. The wing test bed flow guide wall of the high-strength aircraft engine according to claim 2, characterized in that a first connecting plate (7) is welded on one side of the longitudinal support connecting rod (1), a second connecting plate (8) is welded between two adjacent support plates (3), and two ends of the transverse support connecting rod (2) are respectively connected to the first connecting plate (7) and the second connecting plate (8) through bolts.
4. The wing test field guide wall of a high-strength aircraft engine according to claim 3, characterized in that a plurality of strip-shaped screw holes (30) are arranged on the support plate (3) in a penetrating manner, and two adjacent strip-shaped screw holes (30) are fixedly connected through bolts.
5. A high strength aircraft engine on-wing test yard diaphragm wall as claimed in claim 4, characterized in that said support plate (3) is a steel groove.
6. The guide wall of the wing test bed for the high-strength aircraft engine according to claim 5, characterized in that the distance between two adjacent arc-shaped guide vanes (4) is 250mm-500 mm.
7. The guide wall for the wing test bed of the high-strength aircraft engine according to claim 6, characterized in that the thickness of the arc-shaped guide vane (4) is 4-10 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121828115.1U CN215436990U (en) | 2021-08-05 | 2021-08-05 | High-strength guide wall of aircraft engine in wing test yard |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121828115.1U CN215436990U (en) | 2021-08-05 | 2021-08-05 | High-strength guide wall of aircraft engine in wing test yard |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215436990U true CN215436990U (en) | 2022-01-07 |
Family
ID=79691986
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121828115.1U Active CN215436990U (en) | 2021-08-05 | 2021-08-05 | High-strength guide wall of aircraft engine in wing test yard |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215436990U (en) |
-
2021
- 2021-08-05 CN CN202121828115.1U patent/CN215436990U/en active Active
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