阅读说明：本技术 一种机翼无气源振荡射流流动控制装置 (Wing airless source oscillation jet flow control device ) 是由 温新 周銮良 刘应征 张鑫 于 2021-02-22 设计创作，主要内容包括：本发明涉及一种机翼无气源振荡射流流动控制装置,包括：进气口,设于机翼前端下表面,其中机翼上设有襟翼；第一振荡射流器阵列,设于机翼内前端,且输出端连通至机翼上表面,输入端通过第一进气通道连接至进气口；第二振荡射流器阵列,设于机翼内后端,且输出端连通至机翼上表面,输入端通过第二进气通道连接至进气口；第一振荡射流器阵列均由多个振荡射流器组成,振荡射流器包括依次连通的气流入口、振荡器入口喉部、渐扩式的振荡器主通道、振荡器出口喉部和气流出口,以及两个分别位于振荡器主通道两侧反馈通道,反馈通道的输入端连通至振荡器出口喉部,输出端连通至振荡器入口喉部。与现有技术相比,本发明具有无需额外气源等优点。(The invention relates to a wing airless oscillating jet flow control device, which comprises: the air inlet is arranged on the lower surface of the front end of the wing, and a flap is arranged on the wing; the first oscillation ejector array is arranged at the inner front end of the wing, the output end of the first oscillation ejector array is communicated to the upper surface of the wing, and the input end of the first oscillation ejector array is connected to the air inlet through a first air inlet channel; the second oscillation ejector array is arranged at the inner rear end of the wing, the output end of the second oscillation ejector array is communicated to the upper surface of the wing, and the input end of the second oscillation ejector array is connected to the air inlet through a second air inlet channel; the first oscillation ejector array is composed of a plurality of oscillation ejectors, each oscillation ejector comprises an airflow inlet, an oscillator inlet throat, a gradually-expanding oscillator main channel, an oscillator outlet throat and an airflow outlet which are sequentially communicated, and two feedback channels which are respectively positioned on two sides of the oscillator main channel, wherein the input end of each feedback channel is communicated to the oscillator outlet throat, and the output end of each feedback channel is communicated to the oscillator inlet throat. Compared with the prior art, the invention has the advantages of no need of additional air source and the like.)

1. A wing airless oscillating jet flow control device, comprising:

the air inlet is arranged on the lower surface of the front end of the wing, and a flap is arranged on the wing;

the first oscillation ejector array is arranged at the inner front end of the wing, the output end of the first oscillation ejector array is communicated to the upper surface of the wing, and the input end of the first oscillation ejector array is connected to the air inlet through a first air inlet channel;

the second oscillation ejector array is arranged at the inner rear end of the wing, the output end of the second oscillation ejector array is communicated to the upper surface of the wing, and the input end of the second oscillation ejector array is connected to the air inlet through a second air inlet channel;

the first oscillation ejector array is composed of a plurality of oscillation ejectors, each oscillation ejector comprises an airflow inlet, an oscillator inlet throat, a gradually-expanding oscillator main channel, an oscillator outlet throat and an airflow outlet which are sequentially communicated, and two feedback channels which are respectively positioned on two sides of the oscillator main channel, wherein the input end of each feedback channel is communicated to the oscillator outlet throat, and the output end of each feedback channel is communicated to the oscillator inlet throat.

2. The airfoil airless oscillating jet flow control device of claim 1 wherein the first array of oscillating ejectors is located at 25-35% chord length of the airfoil.

3. The airfoil airless oscillating jet flow control device of claim 2 wherein the first array of oscillating ejectors is located at 30% chord length of the airfoil.

4. The airfoil airless oscillating jet flow control device of claim 1 wherein the second oscillating ejector array is located 65-75% of the chord length of the airfoil.

5. The airfoil airless oscillating jet flow control device of claim 4 wherein the second oscillating ejector array is located at 70% chord length of the airfoil.

6. The airfoil airless oscillating jet flow control device of claim 1, wherein the air scoop is located at 5-20% chord length of the airfoil.

7. The airfoil airless oscillating jet flow control device of claim 1, wherein the air scoop is located at 10-15% chord length of the airfoil.

8. The airfoil airless oscillating jet flow control device of claim 1 wherein the oscillator main channel and the feedback channel are separated by an island divider, the island divider being smoothly L-shaped with a break-off angle toward the outer wall of the feedback channel, the break-off angle being disposed near the oscillator inlet throat.

9. The winged airless oscillating jet flow control device of claim 1 wherein a first cavity is provided in the first inlet channel, the output of the first cavity being in communication with the input of all of the oscillating jets in the first array of oscillating jets.

10. The winged airless oscillating jet flow control device of claim 1 wherein a second cavity is provided in the second inlet channel, the output of the second cavity being in communication with the input of all oscillating jets in the second array of oscillating jets.

Technical Field

The invention relates to a wing flow control device, in particular to a wing airless oscillating jet flow control device.

Background

The wing flow control is a classical problem of fluid mechanics, and when an aircraft has a large angle of attack, the airflow originally attached to the surface of the wing generates flow separation due to a large adverse pressure gradient, so that the performance of the aircraft is reduced, and the wing stall can be seriously caused. In a traditional passive control mode, a vortex generator is additionally arranged on the surface of a wing, the shape of the front edge and the rear edge of the wing is changed, and the like, so that the flow separation control on the surface of the wing has a certain effect but is only limited to a specific working condition.

In recent years, the active control mode control shows good superiority, such as direct jet, synthetic jet, pulse jet, plasma, oscillating jet and the like, the effect of 'four and two jacks' can be realized through local small disturbance, energy is injected into a low-energy boundary layer, the mixing degree of the jet and a separation flow is increased, and the airfoil surface separation flow control effect of the active control mode is very obvious. The oscillating ejector can generate periodic sweeping jet with the frequency of several hertz to tens of kilohertz, the jet frequency is only related to the inlet flow rate, and the oscillating ejector has strong robustness and stability.

Disclosure of Invention

The invention aims to provide a wing airless oscillating jet flow control device, which can utilize the separation flow control of natural inlet air at various attack angles during flight by arranging a first oscillating jet device array, a second oscillating jet device array and a corresponding air inlet channel, thereby avoiding the need of additionally providing an air source and corresponding control equipment and reducing the failure rate.

The purpose of the invention can be realized by the following technical scheme:

a wing airless oscillating jet flow control device comprising:

the air inlet is arranged on the lower surface of the front end of the wing, and a flap is arranged on the wing;

the first oscillation ejector array is arranged at the inner front end of the wing, the output end of the first oscillation ejector array is communicated to the upper surface of the wing, and the input end of the first oscillation ejector array is connected to the air inlet through a first air inlet channel;

the second oscillation ejector array is arranged at the inner rear end of the wing, the output end of the second oscillation ejector array is communicated to the upper surface of the wing, and the input end of the second oscillation ejector array is connected to the air inlet through a second air inlet channel;

the first oscillation ejector array is composed of a plurality of oscillation ejectors, each oscillation ejector comprises an airflow inlet, an oscillator inlet throat, a gradually-expanding oscillator main channel, an oscillator outlet throat and an airflow outlet which are sequentially communicated, and two feedback channels which are respectively positioned on two sides of the oscillator main channel, wherein the input end of each feedback channel is communicated to the oscillator outlet throat, and the output end of each feedback channel is communicated to the oscillator inlet throat.

The first oscillating ejector array is located at 25-35% of the chord length of the airfoil.

The first oscillating ejector array is located at 30% chord length of the airfoil.

The second oscillating ejector array is located at 65-75% of the chord length of the airfoil.

The second oscillating ejector array is located at 70% of the chord length of the airfoil.

The air intakes are located at 5-20% of the chord length of the wing.

The air intakes are located at 10-15% of the chord length of the wing.

The oscillator main channel and the feedback channel are separated by an island-shaped separating piece, the outer wall surface of the island-shaped separating piece facing the feedback channel is in an L shape with a smooth folding angle, and the folding angle is arranged close to the throat of the oscillator inlet.

And a first cavity is arranged in the first air inlet channel, and the output end of the first cavity is communicated with the input ends of all the oscillation ejectors in the first oscillation ejector array.

And a second cavity is arranged in the second air inlet channel, and the output end of the second cavity is communicated with the input ends of all the oscillation ejectors in the second oscillation ejector array.

Compared with the prior art, the invention has the following beneficial effects:

1) through setting up first oscillation ejector array and second oscillation ejector array to and corresponding inlet channel, can utilize the separation flow control under the various angle of attack of the natural admit air during flight to need not additionally to provide air supply and corresponding controlgear, reduce the fault rate.

2) The cavity can ensure that the airflow entering each oscillation ejector is uniform and basically keeps the same phase and same frequency sweeping.

Drawings

FIG. 1 is a schematic structural diagram of an embodiment of the present invention;

FIG. 2 is a schematic top view of an embodiment of the present invention;

FIG. 3 is a phase 1 state diagram of an oscillating ejector;

FIG. 4 is a schematic diagram of the phase 2 state of an oscillating ejector;

FIG. 5 is a schematic view of the distribution of inlet air at different angles of attack, wherein (a) to (c) are schematic views at increasing angles of attack;

FIG. 6 is a schematic diagram of a control mechanism;

FIG. 7 is a schematic diagram showing the relationship between the outlet frequency of the oscillation ejector and the wind speed of the wind tunnel incoming flow;

wherein: 1. air inlet, 2, first oscillation ejector array, 3, first air outlet, 4, wing, 5, second oscillation ejector array, 6, second air outlet, 7, flap, 201, airflow inlet, 202, oscillator inlet throat, 203, oscillator main channel, 204, oscillator outlet throat, 205, airflow outlet, 206, feedback channel, 207, island divider.

Detailed Description

The invention is described in detail below with reference to the figures and specific embodiments. The present embodiment is implemented on the premise of the technical solution of the present invention, and a detailed implementation manner and a specific operation process are given, but the scope of the present invention is not limited to the following embodiments.

An airfoil 4 non-air-source oscillatory jet flow control device, as shown in fig. 1 and 2, comprising:

the air inlet 1 is arranged on the lower surface of the front end of the wing 4, wherein the wing 4 is provided with a flap;

the first oscillation ejector array 2 is arranged at the front end in the wing 4, the output end of the first oscillation ejector array is communicated to a first air outlet 3 on the upper surface of the wing 4, and the input end of the first oscillation ejector array is connected to the air inlet 1 through a first air inlet channel;

the second oscillation ejector array 5 is arranged at the inner rear end of the wing 4, the output end of the second oscillation ejector array is communicated to a second air outlet 6 on the upper surface of the wing 4, and the input end of the second oscillation ejector array is connected to the air inlet 1 through a second air inlet channel;

the first oscillation ejector array 2 is composed of a plurality of oscillation ejectors, specifically, the structure of the oscillator is as shown in fig. 3 and fig. 4, the oscillation ejectors include an airflow inlet 201, an oscillator inlet throat 202, a divergent oscillator main channel 203, an oscillator outlet throat 204, an airflow outlet 205, and two feedback channels 206 respectively located at two sides of the oscillator main channel 203, the input ends of the feedback channels 206 are communicated to the oscillator outlet throat 204, and the output ends are communicated to the oscillator inlet throat 202. The oscillator main channel 203 and the feedback channel 206 are separated by an island-shaped partition 207, and the outer wall surface of the island-shaped partition 207 facing the feedback channel 206 is in an L shape with a smooth bend angle, and the bend angle is arranged near the oscillator inlet throat 202. When the fluid entering the oscillating jet depends on one Coanda surface, the adjacent feedback channel 206 forms a backflow and acts on the jet at the inlet to force the fluid to leave the current Coanda surface and attach to the opposite Coanda surface and form a backflow in the opposite feedback loop, and so on, and the two processes attaching to the two opposite Coanda surfaces correspond to the two phases of the oscillating jet process in sequence. As shown in fig. 7, which is a schematic diagram of a relationship between an outlet frequency of an oscillation ejector and an incoming wind speed of a wind tunnel, it can be seen that the oscillation frequency changes linearly with an inlet flow rate and presents an obvious frequency doubling, which indicates that the oscillation process is substantially distributed in a sinusoidal signal form, and a regular and uniform swept jet can be presented at an outlet of the oscillator.

In some embodiments, the first oscillating ejector array 2 is located at 25-35% chord length of the airfoil 4 and the second oscillating ejector array 5 is located at 65-75% chord length of the airfoil 4, wherein in one embodiment the first oscillating ejector array 2 is located at 30% chord length of the airfoil 4 and the second oscillating ejector array 5 is located at 70% chord length of the airfoil 4. When the angle of attack is small, as shown in fig. 5 (a), a delay in separating the angle of attack can be achieved by the flap alone; when the angle of attack is continuously increased, as shown in fig. 5 (b), separation is first generated on the flap surface, that is, separation is performed at about the second oscillation jet array 5, so that at this time, more airflow enters the second oscillation jet array 5 by the action of the incoming flow air inlet 1, periodic sweeping jet flow is generated on the flap surface by the second oscillation jet array 5, and flow separation control of the flap surface is performed by injecting energy into a low-energy boundary layer; when the attack angle is larger, as shown in (c) of fig. 5, the control of the sweeping jet flow at the flap and the flap is not enough to enable the separation flow to be attached to the surface of the wing 4 again, the separation point is advanced to the first oscillating jet device array 2, and the oscillating jet flow entering the first oscillating jet device array 2 is more under the action of the inflow air port, so that the control of the separation flow is mainly achieved. The specific control mechanism is shown in fig. 6.

In some embodiments, the air scoop 1 is located at 5-20% of the chord length of the airfoil 4, and preferably, the air scoop 1 is located at 10-15% of the chord length of the airfoil 4.

In some embodiments, a first cavity is provided in the first air inlet channel, an output end of the first cavity is communicated with input ends of all oscillation ejectors in the first oscillation ejector array 2, a second cavity is provided in the second air inlet channel, and an output end of the second cavity is communicated with input ends of all oscillation ejectors in the second oscillation ejector array 5, so that the air flow entering each oscillator is ensured to be uniform, and the same-phase and same-frequency sweep is basically kept, wherein when the air inlet 1 distributes the air flow to the array oscillators, the air flow is uniform, and the same frequency and the same phase of the oscillators can be basically ensured.