Aircraft engine on-wing test field guide wall with double-layer structure

Abstract

The utility model discloses an aircraft engine on-wing test field flow guide wall with a double-layer structure, which comprises an outer wall body and an inner wall body which are arranged in parallel and obliquely, and a plurality of flow guide units are arranged on the outer wall body and the inner wall body. High-speed wake flow impacted on the inner wall body can be guided downwards and subjected to first-time speed reduction, the outer wall body can continue to guide airflow penetrating through the inner wall body downwards and carry out second-time speed reduction, and the high-speed wake flow generated during full stress application of an aircraft engine is guided downwards and decelerated twice in sequence. It can be ensured that airflow conducted to the outer side of the outer wall body is located in a low-height area and keeps a low flow speed, the safety distance behind the flow guide wall is shortened, and space is saved; by arranging the first sliding grooves and the second sliding grooves, proper adjustment can be conveniently made according to different inclination angles of the wall body, deformation and movement spaces are reserved for the mounting plate, the supporting rods and the reinforcing beams when the mounting plate, the supporting rods and the reinforcing beams are stressed, breakage or damage of all structural parts is avoided and relieved, and the stability of the inner wall body and the outer wall body is ensured.

Description

Technical Field

[0001] The utility model relates to the technical field of diversion walls, in particular to a diversion wall for an in-wing test site of an aircraft engine with a double-layer structure. Background Art

[0002] The diversion wall of the in-wing test site of an aircraft is a device that can guide the air flow to pass smoothly during the in-wing test of the test engine and reduce the air flow speed by changing the air flow direction.

[0003] At present, the key protection position of the diversion wall is the area below 2 meters in height behind the diversion wall. This height is slightly higher than the height of most people, which can achieve the purpose of protecting the operators behind the diversion wall during the test run. In actual test runs, when the aircraft engine is fully started, although the diversion wall can reduce the wind speed in the space below 2 meters in height behind it, the horizontal radiation range of the air flow is relatively wide, and generally, a safe operation distance is considered to be more than 5 meters away from the diversion wall. Therefore, the floor area of the in-wing test site is relatively large. Summary of the Utility Model

[0004] In view of the problems existing in the above-mentioned prior art, the utility model provides a diversion wall for an in-wing test site of an aircraft engine with a double-layer structure. The wall structure is stable, which can reduce the air flow speed twice during the test of the in-wing test site of the aircraft engine, guide the air flow to a lower height area and maintain a lower flow rate, shorten the safety distance behind the diversion wall, and save space.

[0005] To solve the above technical problems, a technical solution adopted by the utility model is as follows:

[0006] A diversion wall for an in-wing test site of an aircraft engine with a double-layer structure, comprising an outer wall and an inner wall that are arranged in parallel on a support member and extend obliquely towards the in-wing test site. The inner wall is closer to the in-wing test site and its height is greater than that of the outer wall, and the height of the outer wall is greater than or equal to two meters; both the outer wall and the inner wall include a plurality of diversion units that are arranged in sequence along the transverse direction and are detachably fixedly connected. Each diversion unit includes a bottom plate, two mounting plates, two support rods, and a plurality of diversion plates. Both ends of each bottom plate are detachably fixed on the support member. The two mounting plates are arranged in parallel and are respectively installed at one end of a bottom plate and extend obliquely towards the direction close to the in-wing test site. The two support rods are respectively vertically installed on the support member and one end of each of them abuts against one of the mounting plates. The plurality of diversion plates are horizontally arranged and evenly erected between the two mounting plates and are evenly arranged along their extension direction. Each diversion plate is formed with an arc-shaped diversion surface; two adjacent diversion units are detachably fixedly connected.

[0007] As a further elaboration of the above technical solution:

[0008] In the above technical solution, one or more reinforcing beams are further provided on each of the flow guiding units of the inner wall body. One end of each reinforcing beam is arranged on one of the mounting plates, and the other end is arranged on one of the support rods.

[0009] In the above technical solution, first chutes extending in the same direction as the reinforcing beams are further provided at both ends of each reinforcing beam. A locking member is provided on each first chute. Each locking member can slide on one of the first chutes and can pass through one of the reinforcing beams to be fixed on one of the mounting plates or the support rods.

[0010] In the above technical solution, one end of each mounting plate is screwed to one of the bottom plates, and the other end is screwed to one of the support rods. Each of the support rods and the bottom plates is screwed to the support member.

[0011] In the above technical solution, second chutes extending in the same direction as the support rods are further provided at one end of each support rod. A locking member is provided on each second chute. Each locking member can slide on one of the second chutes and can pass through one of the support rods to be fixed on one of the mounting plates.

[0012] In the above technical solution, both ends of each flow guiding plate are fixedly welded to one of the mounting plates.

[0013] In the above technical solution, the included angles between the outer wall body and the inner wall body and the horizontal plane are both between 50° and 70°.

[0014] In the above technical solution, each of the bottom plates is a channel steel, each of the mounting plates and the support rods is a steel pipe, and each of the flow guiding plates is a steel plate.

[0015] In the above technical solution, the structures of each flow guiding plate on each flow guiding unit are the same, and the end faces facing away from the wing test site are both flat or arc-shaped.

[0016] Compared with the prior art, the beneficial effects of the present utility model are as follows: By setting the flow guiding wall as a double-layer flow guiding wall mechanism composed of an outer wall body and an inner wall body, the high-speed wake flow impacting on the inner wall body can be guided downward and decelerated for the first time. The outer wall body can continue to guide the air flow passing through the inner wall body downward and decelerate it for the second time, realizing the downward guiding and deceleration of the high-speed wake flow generated when the aircraft engine is at full afterburner twice successively, ensuring that the air flow conducted to the outside of the outer wall body is in a lower height area and maintaining a lower flow rate, shortening the safety distance behind the flow guiding wall and saving space; By providing the first chutes and the second chutes, it is not only convenient to make appropriate adjustments according to different wall inclination angles, but also leaves space for deformation and movement when the mounting plates, support rods and reinforcing beams are stressed, avoiding and slowing down the fracture or damage of each structural member and ensuring the stability of the inner wall body and the outer wall body. Brief Description of the Drawings

[0017] Figure 1 is a schematic side view structure diagram of this embodiment;

[0018] Figure 2 is a schematic front view structure diagram of this embodiment;

[0019] Figure 3 is a schematic front view structure diagram of the diversion unit in this embodiment;

[0020] Figure 4 is a schematic cross-sectional structure diagram of the baffle in this embodiment.

[0021] In the figure: 10, support member; 20, outer wall; 30, inner wall; 40, diversion unit; 41, bottom plate; 42, mounting plate; 43, strut; 44, baffle; 45, strengthening beam; 1, diversion surface; 2, first chute; 3, second chute; 4, end face; a, included angle. Detailed Description of the Preferred Embodiment

[0022] The present invention will be further described in detail below with reference to the accompanying drawings.

[0023] The embodiments described with reference to the accompanying drawings are exemplary and are intended to explain the present application, and should not be construed as limiting the present application. In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present application. In addition, the terms "first" and "second" are only used for descriptive purposes and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present application, the meaning of "several" and "a plurality" is two or more, unless otherwise specifically and clearly defined. In the present application, unless otherwise clearly specified and limited, the terms such as "mounted", "connected", "connected to", "fixed" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected, or indirectly connected through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances. In the present application, unless otherwise clearly specified and limited, the first feature being "above" or "below" the second feature may include the direct contact between the first and second features, or may include the situation where the first and second features are not in direct contact but in contact through other features between them. Moreover, the first feature being "above", "over" and "on" the second feature includes that the first feature is directly above and obliquely above the second feature, or merely indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature being "under", "below" and "beneath" the second feature includes that the first feature is directly below and obliquely below the second feature, or merely indicates that the horizontal height of the first feature is lower than that of the second feature.

[0024] As Figures 1-3As shown in the figure, a flow deflector wall for an in-wing test stand of a double-layer structure aircraft engine includes an outer wall 20 and an inner wall 30 that are arranged in parallel on a support member 10 and extend obliquely towards the in-wing test stand. The inner wall 30 is close to the in-wing test stand and its height is greater than that of the outer wall 20. The height of the outer wall 20 is greater than or equal to two meters. Both the outer wall 20 and the inner wall 30 include a number of flow deflector units 40 arranged in sequence along the transverse direction and detachably connected. Each flow deflector unit 40 includes a bottom plate 41, two mounting plates 42, two support rods 43 and a number of flow deflector plates 44. Both ends of each bottom plate 41 are detachably fixed on the support member 10. The two mounting plates 42 are arranged in parallel and are respectively installed at one end of a bottom plate 42 and extend obliquely towards the direction close to the in-wing test stand. The two support rods 43 are respectively vertically installed on the support member 10 and one end of each of them abuts against one mounting plate 42 respectively. The number of flow deflector plates 44 are arranged horizontally and evenly spanned between the two mounting plates 42 and are evenly arranged along their extending direction. An arc-shaped flow deflector surface 1 is formed on each flow deflector plate 44. Two adjacent flow deflector units 40 are detachably connected to each other.

[0025] In the utility model, by setting the flow deflector wall as a double-layer flow deflector wall mechanism composed of an outer wall 20 and an inner wall 30, the high-speed wake flow impacting on the inner wall 30 can be guided downward for the first deceleration. The outer wall 20 can continue to guide the air flow passing through the inner wall 30 downward for the second deceleration, realizing the downward guiding and deceleration of the high-speed wake flow generated when the aircraft engine is at full afterburner twice successively, ensuring that the air flow conducted to the outside of the outer wall 20 is in a lower height area and maintaining a lower flow rate, shortening the safety distance behind the flow deflector wall and saving space.

[0026] Further, as Figure 2 shown in the figure, one or more strengthening beams 45 are also provided on each flow deflector unit 40 of the inner wall 30. One end of each strengthening beam 45 is arranged on one mounting plate 42, and the other end is arranged on one support rod 43. At both ends of each strengthening beam 45, a first sliding groove 2 extending in the same direction is also provided. There is a locking member on each first sliding groove 2. Each locking member can slide on a first sliding groove 2 and can pass through a strengthening beam 45 and then be fixed on a mounting plate 42 or a support rod 43.

[0027] It can be understood that the higher inner wall 30 can intercept and guide downward the high-speed wake flow within a larger area. The mounting plate 42 and the support rod 43 thereon also bear greater shear forces. The arrangement of the strengthening beam 45 can further enhance its stability, thereby ensuring the stable support for the flow guiding unit 40 thereon and ensuring the speed reduction effect. Moreover, the first chute 2 thereon reserves an adjustment space for the installation and relative movement of the strengthening beam 45, which is not only convenient for making appropriate adjustments according to different wall inclination angles, but also reserves a space for deformation and movement when the mounting plate 42, the support rod 43 and the strengthening beam 45 are stressed, avoiding and slowing down the fracture or damage of each structural member and ensuring the stability of the inner wall 30. In this embodiment, the height of the inner wall 30 is five meters, and the height of the outer wall 20 is three meters.

[0028] Furthermore, as Figure 2 shown, one end of each mounting plate 42 is screwed to a bottom plate 41, and the other end is screwed to a support rod 43. Each support rod 43 and the bottom plate 41 are screwed to the support member 10. One end of each support rod 43 is also provided with a second chute 3 extending in the same direction as it. Each second chute 3 is provided with a locking member. Each locking member can slide on a second chute 3 and can pass through a support rod 43 and be fixed on a mounting plate 42.

[0029] It can be understood that the arrangement of the second chute 3 reserves an adjustment space for the connection and relative movement of the mounting plate 42 and the support rod 43, which is not only convenient for making appropriate adjustments according to different wall inclination angles, but also reserves a space for deformation and movement when the mounting plate 42 and the support rod 43 are stressed, avoiding and slowing down the fracture or damage of each structural member and ensuring the stability of the outer wall 20 and the inner wall 30.

[0030] Furthermore, both ends of each flow guiding plate 44 are fixedly welded to a mounting plate 42. Each bottom plate 41 is a channel steel, each mounting plate 42 and the support rod 43 are steel pipes, and each flow guiding plate 44 is a steel plate. The included angles a between the outer wall 20 and the inner wall 30 and the horizontal plane are both between 50° and 70°.

[0031] In this embodiment, the included angles a between the outer wall 20 and the inner wall 30 and the horizontal plane are both 60°.

[0032] Furthermore, as Figures 3-4 shown, the structures of each flow guiding plate 44 on each flow guiding unit 40 are the same, and its end face 4 facing towards and / or away from the wing test site is a plane or a curved surface.

[0033] In application, the windward side and / or the leeward side of the flow guiding plate 44 can be set as a plane or a curved surface according to the actual site design requirements, so as to obtain the optimal flow guiding and speed reduction effect on the premise of ensuring the overall stability of the wall.

[0034] The above does not impose any limitation on the technical scope of the present utility model. Any modification, equivalent change, and modification made to the above embodiments based on the technical essence of the present utility model still fall within the scope of the technical solution of the present utility model.

Claims

1. A double-layered guide wall for an aircraft engine on-wing test field, characterized in that: It comprises an outer wall and an inner wall which are arranged in parallel on a support and extend obliquely toward an on-wing test field, the inner wall is close to the on-wing test field and its height is greater than that of the outer wall, and the height of the outer wall is greater than or equal to two meters; the outer wall and the inner wall each comprise a plurality of guide units which are arranged in sequence in a transverse direction and are detachably connected, each of the guide units comprises a base plate, two mounting plates, two struts and a plurality of guide plates, both ends of each of the base plates are detachably fixed on the support, the two mounting plates are arranged in parallel and are respectively mounted on one end of a base plate and extend obliquely toward the direction close to the on-wing test field, the two struts are respectively mounted vertically on the support and one end thereof are respectively abutted against one mounting plate, a plurality of guide plates are horizontally arranged and evenly erected between the two mounting plates and evenly arranged along their extension direction, and an arc-shaped guide surface is formed on each of the guide plates; each of the adjacent guide units is detachably connected.

2. The double-layered guide wall for an aircraft engine on-wing test field according to claim 1, characterized in that: Each of the guide units of the inner wall is also provided with one or more reinforcing beams, one end of each of the reinforcing beams is arranged on a mounting plate, and the other end is arranged on a support rod.

3. The double-layered aircraft engine on-wing test field guide wall according to claim 2, characterized in that: Both ends of each reinforcement beam are also provided with a first slide groove extending in the same direction therewith, and each of the first slide grooves is provided with a locking piece. Each of the locking pieces can slide on a first slide groove and can pass through a reinforcement beam and be fixed on a mounting plate or a support rod.

4. The double-layered aircraft engine on-wing test field guide wall according to claim 1, characterized in that: One end of each mounting plate is screwed to a base plate, and the other end is screwed to a support rod. Each support rod and the base plate are screwed to the support member.

5. The double-layered aircraft engine on-wing test field guide wall according to claim 1, characterized in that: One end of each strut is also provided with a second slide groove extending in the same direction as the strut, and each of the second slide grooves is provided with a locking piece. Each of the locking pieces can slide on a second slide groove and can pass through a strut to be fixed on a mounting plate.

6. The double-layered aircraft engine on-wing test field guide wall according to claim 1, characterized in that: Both ends of each guide plate are welded and fixed to a mounting plate.

7. The double-layered guide wall for an aircraft engine on-wing test field according to claim 1, characterized in that: The included angles between the outer wall and the inner wall and the horizontal plane are both between 50° and 70°.

8. A double-layered guide wall for an aircraft engine on-wing test field according to any one of claims 1 to 7, characterized in that: Each of the bottom plates is a channel steel, each of the mounting plates and the support rod is a steel pipe, and each of the guide plates is a steel plate.

9. The double-layered guide wall for an aircraft engine on-wing test field according to claim 8, characterized in that: The structure of each guide plate on each guide unit is the same, and the end surface thereof facing away from the on-wing test track is a flat surface or a curved surface.

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