阅读说明：本技术 一种改善naca口进气效率的通风冷却进气道 (Ventilation cooling air inlet channel for improving air inlet efficiency of NACA port ) 是由 杨成凤 张宏 于 2021-09-19 设计创作，主要内容包括：本申请属于飞行器设计技术领域,特别涉及一种改善NACA口进气效率的通风冷却进气道。该进气道在短舱或机身表面(1)上,且位于短舱或机身表面(1)附面层之后设置有埋入式的NACA进气口(2),短舱或机身表面(1)的位于NACA进气口(2)的周围安装有若干绕流柱(3),绕流柱(3)轴线方向为沿垂直于短舱或机身表面(1)向外延伸,形成绕流柱顶部,且所述绕流柱(3)的高度被设置为使绕流柱顶部略高于所述附面层。本申请通过在机身表面的埋入式NACA进气口附近布置绕流柱排来改善进气口的进气效率,结构简单,易于实现,同时通过调整绕流柱排的高度、安装角度,可以满足飞行器多状态使用需求,达到通风冷却流量与流动阻力之间的切换性选择。(The utility model belongs to the technical field of aircraft design, in particular to ventilation cooling intake duct of NACA mouth air intake efficiency improves. This intake duct is on nacelle or fuselage surface (1), and is located nacelle or fuselage surface (1) and attaches the surface course and be provided with NACA air inlet (2) of buryying behind the surface course, and a plurality of streams of streaming (3) are installed around being located NACA air inlet (2) on nacelle or fuselage surface (1), and outwards extend for following perpendicular to nacelle or fuselage surface (1) around streaming (3) axis direction, form around streaming top, just the height of streaming (3) is set up to make around streaming top be a little higher than attach the surface course. This application arranges around the flow column row near the formula of burying NACA air inlet at the fuselage surface and improves the air intake efficiency of air inlet, simple structure easily realizes, simultaneously through height, the installation angle of adjustment around the flow column row, can satisfy aircraft multistate user demand, reaches the switching nature between ventilation cooling flow and the flow resistance and selects.)

1. The utility model provides an improve NACA mouth intake efficiency's ventilation cooling intake duct, its characterized in that, on nacelle or fuselage surface (1), and be located nacelle or fuselage surface (1) boundary layer and be provided with NACA air inlet (2) of buryying behind, a plurality of streaming columns (3) are installed around being located NACA air inlet (2) of nacelle or fuselage surface (1), and streaming column (3) axis direction is for outwards extending along perpendicular to nacelle or fuselage surface (1), forms streaming column top, just the height of streaming column (3) is set up to make streaming column top be a little higher than boundary layer.

2. The ventilated cooling air inlet channel for improving the air inlet efficiency of the NACA port as claimed in claim 1, wherein the NACA air inlet (2) comprises an inclined plate (5), two side edges (6) are formed on two sides of the inclined plate (5), a side edge line (4) of the side edge (6) and the nacelle or body surface (1) are in an NACA curve, the two side edges (6) shrink at the front end of the inclined plate (5) to form an interface which is blended into the nacelle or body surface (1), the rear end of the inclined plate (5) obliquely extends into the body to be connected with a cold edge inlet (7) of a radiator, and the flow winding column (3) is arranged outside the side edge (6) of the NACA air inlet.

3. A draft cooling air inlet for improving NACA inlet efficiency according to claim 2 wherein the intersection of the side edges (6) with the nacelle or fuselage surface (1) is a right angle edge without chamfer.

4. The inlet duct for ventilated cooling with improved NACA opening air intake efficiency as claimed in claim 2, wherein at least one row of winding posts (3) is provided outside each lateral edge (6) of the NACA inlet along the extension of the lateral edge line (4) of the lateral edge (6).

5. The inlet duct for ventilated cooling of improving the air intake efficiency of a NACA nozzle as claimed in claim 2, wherein the cross-section of the bypass flow post (3) is drop-shaped, the head of the drop-shaped portion facing the incoming flow direction and the tip of the drop-shaped portion being close to the proximal edge (6).

6. The ventilated cooling air inlet duct for improving the air intake efficiency of the NACA port as claimed in claim 5, wherein the cross-sectional length direction of the flow surrounding columns (3) forms an acute angle with the extension direction of the side edge line (4) of the side edge (6), and the corresponding acute angle of each flow surrounding column (3) is continuously increased from the front end to the rear end of the inclined plate (5), but the cross-sectional axial direction of the last flow surrounding column (3) is parallel to the extension direction of the side edge line (4) of the side edge (6);

wherein, the length direction of the cross section of the circumfluence column refers to the direction from the water drop-shaped head part to the tip part on the cross section (8) of the circumfluence column (3).

7. The ventilated cooling air inlet duct for improving the air intake efficiency of an NACA port of claim 6, wherein the length of the cross section (8) of the bypass column (3) is 1/3 of the maximum width of the inclined plate (5) of the NACA air inlet (2), and the ratio of the maximum width to the length of the cross section (8) of the bypass column (3) is 1/3.5.

8. The inlet duct according to claim 6, characterized in that the post (3) is connected to the driving means under the nacelle or fuselage surface (1) via a rotation axis extending in the axial direction of the post (3), the post (3) being arranged to be rotated about the rotation axis by the driving means so that the acute angle between the length of the cross-section of the post (3) and the direction in which the lateral edge (4) of the lateral edge (6) extends is adjustable.

9. The NACA port intake efficiency-improving ventilated cooling air inlet of claim 8, wherein the bypass post (3) is configured to be moved axially along the bypass post (3) by the driving means to change the height of the bypass post (3) protruding from the nacelle or fuselage surface (1).

10. The ventilated cooling air inlet for improving the air intake efficiency of the NACA port of claim 5, wherein the cross section (8) of the bypass flow post (3) is triangular, airfoil-shaped, rectangular or T-shaped.

Technical Field

The utility model belongs to the technical field of aircraft design, in particular to ventilation cooling intake duct of NACA mouth air intake efficiency improves.

Background

The embedded air inlet channel has no component protruding out of the surface of the aircraft, so that the aircraft can keep a pneumatic surface as clean as possible, and the pneumatic performance of the aircraft cannot be damaged; however, since the embedded air inlet channel works in the boundary layer and has zero capture area for free incoming flow, the flow capacity of the embedded air inlet channel is weak, and the flow field quality is poor, which is a key factor restricting the wide application of the embedded air inlet channel in engineering.

In order to improve the flow capacity of the submerged intake duct, various technical measures have been developed, and these technical measures are mainly classified into two categories, namely, improvement of the inlet-side ridge shape and addition of a vortex generator. The improvement of the inlet side ridge shape has very limited improvement of the flow capacity; the existing vortex generator technology can better improve the flow capacity of the embedded air inlet, but causes damage to the surface flow field of the airplane in different degrees, and increases the resistance of the whole airplane. How to effectively improve the air intake efficiency of the embedded air intake duct and control the outflow resistance caused by the vortex generator becomes a difficult point in technical design.

Disclosure of Invention

In order to solve the technical problem, the application provides a ventilation cooling air inlet channel for improving the air inlet efficiency of an NACA port, and the circulation capacity of an embedded air inlet channel positioned at the middle rear part of a machine body is effectively improved.

The utility model provides an improve NACA mouth air intake efficiency's ventilation cooling intake duct, at nacelle or fuselage on the surface, and be provided with the NACA air inlet of formula of buryying after being located nacelle or fuselage surface boundary layer, a plurality of streams of circling post are installed around being located NACA air inlet on nacelle or fuselage surface, and outwards extend for following perpendicular to nacelle or fuselage surface around the column axis direction of circling, form around the column top, just the height of circling the column is set up to make around the column top a little more than the boundary layer.

Preferably, the NACA air inlet includes the swash plate, and the swash plate both sides form two side edges, and the side edge line that side edge and nacelle or fuselage surface meet is the NACA curve, and two side edges shrink at the front end of swash plate, form the interface that fuses into nacelle or fuselage surface, and the swash plate rear end slant stretches into in the fuselage to connect the cold limit entry of radiator, the column setting of streaming is in the side edge outside of NACA air inlet.

Preferably, the junction of the lateral edge and the surface of the nacelle or fuselage is a right-angled edge without a chamfer.

Preferably, at least one row of flow around posts is arranged outside each lateral edge of the NACA air inlet along the extension direction of the lateral edge line of the lateral edge.

Preferably, the cross section of the circumfluence column is in a drop shape, the drop-shaped head faces the incoming flow direction, and the tip is close to the near side edge.

Preferably, the length direction of the cross section of each of the flow winding columns and the extension direction of the lateral edge line of the lateral edge form an acute angle with a set angle, and the acute angle corresponding to each of the flow winding columns is continuously increased from the front end to the rear end of the inclined plate, but the axial direction of the cross section of the last flow winding column is parallel to the extension direction of the lateral edge line of the lateral edge;

the length direction of the cross section of the circumfluence column refers to the direction from the drop-shaped head to the tip on the cross section of the circumfluence column.

Preferably, the length of the bypass flow column cross-section of the bypass flow column is 1/3 the maximum width of the sloping plate of the NACA inlet, and the ratio of the maximum width to the length of the bypass flow column cross-section of the bypass flow column is 1/3.5.

Preferably, the flow around column is connected to a driving device under the surface of the nacelle or the fuselage through a rotating shaft, the rotating shaft extends along the axial direction of the flow around column, and the flow around column is configured to be driven by the driving device to rotate around the rotating shaft, so that the acute included angle between the cross section length direction of the flow around column and the extension direction of the lateral edge line of the lateral edge is adjustable.

Preferably, the bypass flow post is configured to be driven by the drive means to move axially along the bypass flow post to vary the height at which the bypass flow post projects above the surface of the nacelle or fuselage.

Preferably, the cross section of the bypass flow column is triangular, airfoil-shaped, rectangular or T-shaped.

The arrangement of the streaming column belongs to the category of external vortex generators. Through the height to the column row that flows around, the change of installation angle, can realize the aircraft and at the ventilation cooling demand under different flight angles of attack, sideslip angle states, when the cooling flow demand is great, the specific mounting means of column row that flows around can effectively improve the air intake flow of buryying formula intake duct, need sacrifice a certain amount of outflow resistance this moment, when the cooling flow demand is less, change the installation angle of column row that flows around and the height of outstanding organism, can reduce outflow resistance rapidly, rely on NACA air inlet self ability to provide sufficient cooling air alone.

This application arranges around the flow column row near the formula of burying NACA air inlet at the fuselage surface and improves the air intake efficiency of air inlet, simple structure easily realizes, simultaneously through height, the installation angle of adjustment around the flow column row, can satisfy aircraft multistate user demand, reaches the switching nature between ventilation cooling flow and the flow resistance and selects.

Drawings

FIG. 1 is a schematic view of the overall installation of a preferred embodiment of the present invention for a ventilated cooling air inlet that improves the air intake efficiency of the NACA opening.

FIG. 2 is a schematic view of a NACA buried inlet and bypass column bank of the present application.

FIG. 3 is a side view of a NACA buried inlet and bypass leg array of the present application.

FIG. 4 is a schematic view of a single bypass column of the present application.

FIG. 5 is a schematic illustration of the bypass flow post of the present application directing airflow into the NACA air intake.

Wherein, 1-the surface of the nacelle or the fuselage, 2-the NACA air inlet, 3-the streaming column, 4-the side edge line, 5-the sloping plate, 6-the side edge, 7-the cold edge inlet of the radiator, 8-the section of the streaming column.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.

The method comprises the steps that specially designed flow-around column rows are arranged near two side edges of a nacelle/body surface air inlet, when the air inflow of an NACA port is insufficient, more body surface boundary layer air flows are introduced into the NACA air inlet through the flow-around column rows, and when more cooling air is not needed, the height and the installation angle of the flow-around columns are adjusted to reduce the aerodynamic resistance generated by the flow-around columns, so that the selection switching between the flow increase and the control resistance is realized.

The application provides a ventilation cooling air inlet channel for improving the air inlet efficiency of an NACA port, which mainly comprises a nacelle or a fuselage surface 1, an NACA air inlet 2 and a bypass flow column 3, wherein the NACA air inlet 2 is positioned at the rear section of the nacelle or the fuselage surface 1, and the bottom of the bypass flow column 3 is connected with the nacelle or the fuselage surface 1 and two sides of the NACA air inlet 2, as shown in FIGS. 1 and 3.

The NACA air inlet 2 is located at the rear section of the nacelle or the fuselage, does not protrude out of the surface of the fuselage, is an embedded air inlet, is thick in the front boundary layer due to the fact that a windward surface does not exist, is low in air inlet efficiency, is an NACA curve on the side edge line 4 of the NACA air inlet 2, is provided with a long inclined plate 5, is a right-angle edge without a chamfer at the joint of the side edge 6 and the nacelle or the fuselage surface 1, is beneficial to generating edge vortexes, and is used for rolling more boundary layer air flows into a cold edge inlet 7 of the radiator, and is shown in fig. 2 and 3.

The streaming columns 3 are arranged near upper and lower side ridge lines 4 of the NACA air inlet 2, a plurality of rows of streaming columns are arranged in the front and back direction, the streaming column cross sections 8 are in a water droplet shape, the head of the water droplet shape faces the incoming flow direction, the tip (tail) is close to the direction of the side edge 6, the streaming columns 3 and the side edge 6 have certain acute included angles, the certain acute included angles with the incoming flow exist, the multiple rows of streaming columns arranged along the course are sequentially increased from the acute angle of the edge, the last streaming column plays a role in ending control and is parallel to the tangential direction of the edge, the effect is drag reduction, and the arrangement mode is favorable for guiding more boundary layer air flows into the NACA air inlet 2, as shown in fig. 1, fig. 2 and fig. 5.

The length of the bypass column section 8 of the bypass column 3 is about 1/3 of the maximum width of the inclined plate 5 of the NACA air inlet 2, the ratio of the maximum width to the length of the bypass column section 8 of the bypass column 3 is about 1/3.5, and the height of the bypass column 3 is slightly higher than the boundary layer, as shown in FIG. 4.

The cross section 8 of the bypass flow column 3 can be in a drop shape, a triangle shape, an airfoil shape, a rectangle shape, a T shape and other shapes.

The angles of the streaming columns 3 on the upper edge and the lower edge of the NACA air inlet 2 can be symmetrically arranged, the adaptive adjustment can be carried out according to different attack angle sideslip angles, small mechanisms for controlling the streaming columns can be arranged in the streaming columns, and parameters such as the height and the angle of the streaming columns are changed. For example, in one specific embodiment, the streaming cylinder 3 is connected to a driving device below the nacelle or fuselage surface 1 via a rotating shaft, the rotating shaft extends along the axial direction of the streaming cylinder 3, and the streaming cylinder 3 is configured to be driven by the driving device to rotate around the rotating shaft, so that the acute included angle between the cross-sectional length direction of the streaming cylinder 3 and the extending direction of the lateral edge line 4 of the lateral edge 6 is adjustable; similarly, the bypass column 3 may be configured to move axially along the bypass column 3 under the drive of the driving device to change the height of the bypass column 3 protruding from the nacelle or fuselage surface 1.

The windward side of the streaming columns can be changed according to the use condition, when the airflow in the NACA port is enough, the streaming columns can be rotated to the minimum position of the windward side, the front streaming columns and the rear streaming columns are matched into a streamline shape to reduce the overall resistance, and when the airflow in the NACA port is not enough, the streaming columns are rotated to the position.

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