CN215719134U

CN215719134U - Vector spray pipe based on self-excitation pulse oscillation jet flow

Info

Publication number: CN215719134U
Application number: CN202121654658.6U
Authority: CN
Inventors: 王士奇; 董芃呈; 张亚华; 罗斌; 贾志刚
Original assignee: China Aero Engine Research Institute
Current assignee: China Aero Engine Research Institute
Priority date: 2021-07-20
Filing date: 2021-07-20
Publication date: 2022-02-01
Anticipated expiration: 2031-07-20

Abstract

The utility model provides a vector spray pipe based on self-excitation pulse oscillation jet flow, which comprises an airflow pipeline, an air source, a switch valve, an exciter, a first pipeline and a second pipeline. The utility model controls the opening and closing of the exciter array on one side by controlling the switch valve, when the oscillator array on one side starts to work and generates oscillating jet flow, the main jet flow at the outlet of the spray pipe deflects towards the side at a certain angle due to the coanda effect, thereby achieving the purpose of adjusting the deflection direction of the main jet flow. Meanwhile, the exciter is a self-excitation pulse oscillator, one steady-state airflow is changed into two pulse jets, so that the flow consumption can be reduced by 50% under the same vector angle control requirement, the main airflow of the engine can be effectively controlled only by using the flow of less than 1% of the engine, and the practical application possibility is provided for implementing the thrust vector control of the engine by adopting the secondary flow.

Description

Vector spray pipe based on self-excitation pulse oscillation jet flow

Technical Field

The utility model belongs to the technical field of active flow control, and particularly relates to a vector spray pipe based on self-excited pulse oscillation jet flow.

Background

Thrust Vector Control (TVC) is a technology that provides a stronger control torque by directly changing the thrust direction through a nozzle, and can greatly enhance the operational efficiency and maneuverability of a fighter. In short, the thrust vector technology is to obtain the lateral force for driving the airplane to turn by directly changing the thrust direction. The advent of thrust vectoring technology has enabled jet aircraft, primarily fighters, to have unprecedented maneuverability, or greater agility, and also to achieve short take-off capability that can take-off at shorter roll distances, yet further reducing or even eliminating the aircraft's aerodynamic rudder, thereby reducing aircraft aerodynamic drag and reducing aircraft mass. Therefore, the thrust vector technology is undoubtedly an advanced air jet fighter control technology.

The vector spray pipe mainly comprises two shapes, wherein the section of one of the two shapes is circular (axially symmetric), the jet flow of the vector spray pipe can deflect in the direction of 360 degrees along the circumferential direction under a certain included angle with the axis, the vector control flexibility is higher, but the mechanism is extremely complex; another type of nozzle has a square cross section (two-dimensional type), and the jet flow can only deflect in the upper and lower directions within a certain angle with the axis, so the nozzle is also called a binary vector nozzle. Compared with an axisymmetric nozzle, the structure and the control method are simpler, and the nozzle is applied to an F119 engine of an F-22 warplane.

The traditional thrust vector technology uses a complex mechanical structure to realize the rotation of an engine spray pipe, and obtains the control of the thrust vector in a mode of changing the angle of the spray pipe and changing the direction of a jet flow. This control method has some significant drawbacks, such as the complex mechanical structure increasing the weight of the aircraft and the difficulty of maintenance of the equipment; the complexity of the control system increases; the material of the nozzle has special requirements; changing the nozzle profile has a hysteresis effect on the control of the thrust vector; is not beneficial to the invisibility of the aircraft. Therefore, over the past 20 years, pneumatic vector propulsion technology has received wide attention from researchers worldwide. Unlike mechanical vectoring nozzles that use actuation hardware to direct jet flow from an engine nozzle, pneumatic thrust vectoring nozzles use secondary flow injection or extraction to control the primary jet flow, enabling effective vectoring of the primary jet flow from the engine nozzle. The most intuitive difference of a pneumatic vectoring nozzle over a mechanical vectoring nozzle is the fixed profile and the absence of mechanical actuating means, which is believed to have the potential for a reduction of 60% to 70% in mass with very good reliability and life expectancy.

An important approach in pneumatic vector propulsion is the co-current method. The technical basis for a co-current type pneumatic thrust vectoring nozzle is the Coanda (Coanda) effect. The coanda effect is the tendency of a fluid (liquid or gas) to flow along a convex object surface when it flows over the convex object surface, deviating from the original flow direction. The cocurrent flow type aerodynamic vector jet pipe utilizes the Coanda effect of secondary flow and the wall surface of the jet pipe to inject the secondary flow in the direction parallel to the main flow, thereby deflecting the main flow.

The pneumatic vector propulsion technology consumes the secondary flow, so that the overall propulsion efficiency is negatively affected. The smaller the consumed secondary flow rate, the more efficient the aerodynamic vector propulsion control. A great deal of research has shown that compared with steady-state jet flow, the flow control efficiency can be greatly improved by adopting unsteady-state disturbance, and the traditional unsteady-state fluid excitation at present mainly comprises a synthetic jet flow exciter, a plasma exciter and the like. However, the working conditions in the jet pipe at the tail of the aeroengine are severe, and the reliability requirements on all parts are extremely high, and the traditional unsteady state exciter has the defects of poor safety, low reliability, insufficient excitation strength, difficult electromagnetic protection and the like in practical application, so that the traditional unsteady state exciter is difficult to use in practical working conditions. For example, the conventional direct flow needs to use a slit to inject secondary fluid, which can generate the deflecting effect of the main flow of the engine, but at least 2% of the mass flow of the engine needs to be consumed, even more than 5%, so that the loss ratio of the thrust of the engine is large, and the practical application is difficult.

SUMMERY OF THE UTILITY MODEL

In order to solve at least one of the above technical problems, the present invention provides a vectoring nozzle based on self-excited pulsed oscillating jet, which uses a novel secondary flow exciter having an inlet and two outlets. Under the stable inlet condition, high-frequency and high-speed pulse type oscillating jet flow can be alternately generated at each outlet, the pulse jet flow can greatly enhance the mixing effect of secondary excitation flow and main flow, simultaneously, one flow of the steady-state jet flow is changed into two flows by the exciter, the action range is greatly increased, and therefore the purpose of greatly reducing the secondary flow mass flow consumption is achieved. The purpose of the utility model is realized by the following scheme:

a vector spray pipe based on self-excitation pulse oscillation jet flow comprises an airflow pipeline, an air source, a switch valve, an exciter, a first pipeline and a second pipeline;

the airflow pipeline comprises a first side wall and a second side wall which is corresponding to the first side wall in the axial direction, and a plurality of exciters are arranged on the first side wall and the second side wall; the exciter is a self-excitation pulse oscillator, the exciter on the first side wall is communicated with the first pipeline, and the exciter on the second side wall is communicated with the second pipeline;

the gas source conveys gas to the first pipeline and the second pipeline through the switch valve, and the switch valve is suitable for conducting the first pipeline and closing the second pipeline or conducting the second pipeline and closing the first pipeline;

the actuator ejects gas in a pulsed manner along the first sidewall or the second side plate.

Further, a pressure regulating valve is connected between the air source and the switch valve.

Furthermore, the direction of the nozzle of the exciter is tangent to the first side wall or the second side wall or the nozzle forms an included angle with the first side wall and the second side wall.

Further, the switch valve is a stop valve or a two-position three-way electromagnetic valve.

Further, the actuator includes a first orifice pipe and a second orifice pipe from which the fluid is ejected in a pulse form.

Furthermore, an included angle between the first nozzle pipeline and the second nozzle pipeline is 2 beta degrees, and the beta angle range is 10-50 degrees.

Furthermore, the exciter also comprises an air inlet cavity, a contraction port, a first feedback channel and a second feedback channel; the gas inlet cavity is connected with the first pipeline or the second pipeline, and the gas passing through the contraction opening is suitable for being output from the first spout pipeline or the second spout pipeline; one ends of the first nozzle pipeline, the second nozzle pipeline, the first feedback channel and the second feedback channel are connected with the outlet of the contraction port; the other end of the first feedback channel is connected with the middle of the first nozzle pipeline, and the other end of the second feedback channel is connected with the middle of the second nozzle pipeline.

Furthermore, the exciter also comprises an air inlet cavity, a contraction port, an oscillation cavity, a first feedback channel and a second feedback channel; the gas inlet cavity is connected with the first pipeline or the second pipeline, and gas enters the oscillation cavity through the contraction port; the end part of the oscillation cavity connected with the outlet of the contraction port is also connected with one end of the first feedback channel and one end of the second feedback channel; and the other end part of the oscillation cavity, which is far away from the contraction port, is connected with the other end of the first feedback channel, the other end of the second feedback channel, the first nozzle pipeline and the second nozzle pipeline.

Furthermore, the exciter also comprises an air inlet cavity, a contraction port, a feedback channel, a first control port and a second control port; the gas inlet cavity is connected with the first pipeline or the second pipeline, and the gas passing through the contraction opening is suitable for being output from the first spout pipeline or the second spout pipeline; the first nozzle pipeline, the second nozzle pipeline, the first control port and the second control port are all connected with the outlet of the contraction port; the first control port is connected with the second control port through the feedback channel.

Further, the first pipeline and the second pipeline both comprise air guide cavities, the air source is an engine, main air flow of the engine enters the air flow pipeline, and lateral air flow of the engine enters the air guide cavities.

And the engine further comprises an annular cavity, a plurality of air holes are formed in the outer wall surface of the engine, the annular cavity is covered with the air holes, the lateral air flow output by the engine from the air holes is collected, and the air flow is output to the air-entraining cavity through a second interface on the annular cavity.

Further, sealing rings are arranged on two outer walls of the annular cavity, which are in contact with the outer wall of the engine.

Furthermore, the annular cavity is provided with a fracture, the fracture is provided with two lugs, the locking mechanism implements locking through the locking holes in the lugs, and the gap between the two lugs during locking is smaller than the gap during unlocking.

Compared with the prior art, the utility model has the advantages that: the utility model provides a vector spray pipe based on self-excitation pulse oscillation jet flow, which comprises an airflow pipeline, an air source, a switch valve, an exciter, a first pipeline and a second pipeline, wherein the airflow pipeline is connected with the air source; the gas source delivers gas to the first and second conduits through the on-off valve, and the actuator ejects gas in a pulsed manner along the first sidewall or the second side plate. The utility model controls the opening and closing of the exciter array on one side by controlling the switch valve, when the oscillator array on one side starts to work and generates oscillating jet flow, the main jet flow at the outlet of the spray pipe deflects towards the side at a certain angle due to the coanda effect, thereby achieving the purpose of adjusting the deflection direction of the main jet flow. The utility model adopts the self-excited pulse type oscillator to generate the secondary flow, can greatly reduce the use of the airflow of the engine, can effectively control the main airflow of the engine by using the flow of less than 1 percent of the engine, has no complicated mechanical control structure and increases the reliability. The method provides practical application possibility for implementing engine thrust vector control by using secondary flow.

Drawings

The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the utility model and together with the description serve to explain the principles of the utility model.

FIG. 1 is a schematic diagram of a vectoring nozzle structure based on self-excited pulsed oscillating jet according to the present invention;

FIG. 2 is a schematic view of a portion of the actuator of FIG. 1 in the direction A-A;

FIG. 3 is a schematic view of a portion of the exciter of FIG. 1 in the direction B-B;

FIG. 4 is a schematic diagram of a second embodiment of the actuator of FIG. 1;

fig. 5 is a schematic view of a third embodiment of the actuator of fig. 1.

FIG. 6 is a schematic diagram of an embodiment of the vectoring nozzle of FIG. 1;

FIG. 7 is an axial cross-sectional view of the vector nozzle of FIG. 6;

FIG. 8 is an engine of the vectoring nozzle configuration of FIG. 6;

fig. 9 is a diagram of the effect of the deflection of the main air flow guided by the conventional straight jet and the oscillating jet.

Wherein: 1. a gas source; 2. an on-off valve; 3. a pressure regulating valve; 4. a first conduit; 5. a second conduit; 6. a first side wall; 7. an exciter; 71. an air inlet cavity; 72. a constriction; 73. a first feedback path; 74. a second feedback path; 75. a first spout conduit; 76. a second spout conduit; 81. a constriction; 82. an oscillation cavity; 83. a first feedback path; 84. a second feedback path; 85. a first spout conduit; 86. a second spout conduit; 91. an air inlet cavity; 92. a feedback channel; 93. a first control port; 94. a second control port; 95. a first spout conduit; 96. a second spout conduit; 100. a primary jet; 200. swirling; 401. an airflow outlet; 402. an air introducing cavity; 403. a main flow channel; 404. a first air flow interface; 405. an exciter; 406. an engine; 407. an annular cavity; 408. a second air flow interface; 409. a lug; 410. and (4) air holes.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the utility model. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.

In addition, the embodiments of the present invention and the features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.

Referring to the attached figure 1 of the specification, the utility model provides a vector spray pipe based on self-excitation pulse oscillation jet, which comprises an airflow pipeline, an air source 1, a switch valve 2, an exciter 7, a first pipeline 4 and a second pipeline 5.

The airflow duct is used for jetting high-speed airflow to the outside so as to propel the aircraft. In order to realize vector control, n (n is more than or equal to 1) pulse type fluid oscillation exciters 7 are symmetrically arranged on the coanda surface configurations on the two sides of the outlet of the spray pipe of the airflow pipeline, and the pulse type fluid oscillation exciters 7 on the two sides can independently generate pulse type oscillation jet flow with certain frequency. When the oscillator array on one side starts to work and generates oscillating jets, the main jet 100 at the nozzle outlet is deflected in an angular direction towards that side due to the coanda effect, thereby adjusting the direction of deflection of the main jet 100. The utility model can ensure that the speed absolute value of the main jet flow at the outlet does not change under the condition of steady inlet, namely the condition that the inlet flow does not change, but the direction of the main jet flow can realize deflection at a larger angle.

Specifically, the airflow pipeline comprises a first side wall 6 and a second side wall corresponding to the first side wall 6, and a plurality of exciters 7 are arranged on the first side wall 6 and the second side wall. An exciter 7 on the first side wall 6 communicates with the first conduit 4 and an exciter 7 on the second side wall communicates with the second conduit 5. The gas source 1 delivers gas to the first pipe 4 and the second pipe 5 through the on-off valve 2. The switching valve 2 has at least two configurations, one of which will open the first duct 4 and close the second duct 5, so that the actuator 7 on the first side wall 6 communicating with the first duct 4 emits a high-velocity gas flow, guiding the main flow through the gas flow duct to be deflected in the direction of the first side wall 6. Another configuration of the switching valve 2 is to open the second duct 5 and close the first duct 4, thereby effecting a deflection of the main flow towards the second side wall. Thereby achieving the aim of controlling the spraying direction of the vectoring nozzle. Of course, the switching valve 2 can also have a third mode in which it conducts neither the first duct 4 nor the second duct 5. The switch valve 2 is preferably a stop valve or a two-position three-way solenoid valve.

The control structure and the control method of the pneumatic thrust vectoring nozzle adopt a flow control strategy, have simple structure, high reliability and strong adaptability, do not need to utilize a complex mechanical structure to change the appearance of the nozzle, and reduce the weight of an aircraft; the resistance of the aircraft can not be increased due to the change of the shape of the spray pipe, and the stealth performance of the aircraft can be obviously improved.

In a preferred embodiment, a pressure regulating valve 3 is further connected between the gas source 1 and the on-off valve 2. The inlet pressure and the flow rate of the exciter 7 are adjusted by controlling the pressure regulating valve 3, so that the deflection angle of the main jet 100 is controlled, and the deflection angle gamma of the main jet 100 can be increased by increasing the inlet pressure and the flow rate. As the flow rate and quantity of the fluid output by the actuator 7 becomes greater, the greater its effect on the primary jet 100, and therefore the greater the deflection of the injected flow. In one embodiment, the direction of the orifice of the actuator is tangential to the first or second side wall. The deflection angle γ of the main air flow can be maximized at the same excitation pressure and flow rate.

In another embodiment, the direction of the orifice of the actuator is arranged at an angle α to said first or second side wall. The angle alpha is preferably + -15 degrees. Through the angle design, the response rule between the main air flow deflection angle gamma and the inlet pressure and the flow can be changed.

In a further preferred embodiment, the outlet of the gas flow line is flared. Specifically, the outlet assumes a gradually expanding shape from the direction of the flow of the gas stream. The horn-shaped outlet can further increase the swing angle of the airflow at the tail part of the vectoring nozzle. And the air flow is attached by utilizing the coanda effect. By using coanda equidirectional flow control, the angular deflection range of the main jet can be enlarged, and thrust vectorization is realized to the maximum extent. Preferably, the first side wall and the second side wall are both shaped as circular arcs with a radius R (R >0.1m) and a circular arc angle b (5 ° < b <70 °). The nozzle position of the actuator is the starting position of the arc.

The exciter can be in various forms, such as a double feedback channel oscillation cavity-free pulse oscillator shown in figures 2-3, a double feedback channel oscillation cavity-free pulse oscillator shown in figure 4, and a single feedback channel oscillation cavity-free pulse oscillator shown in figure 5. The above exciter can use the oscillation jet exciter as an exciting device for the Conda cocurrent flow control to generate jet flow with the frequency of dozens of hertz to tens of thousands of hertz, and because the exciter has no moving part or electromagnetic mechanism, the problems of abrasion, aging and the like caused by moving mechanical parts of other unsteady exciting devices and the electromagnetic protection problem caused by plasma/electromagnetic elements are avoided, and the service life, safety, reliability and robustness of the device are improved.

Fig. 2-3 provide a dual feedback channel oscillatory chamber-free pulse oscillator as the exciter 7, which comprises an air inlet chamber 71, a constriction 72, a first feedback channel 73 and a second feedback channel 74, a first orifice pipe 75, and a second orifice pipe 76. The fluid is ejected from the first and

second spout pipes

75 and 76 in the form of pulses. By adopting an unsteady flow control strategy, the control efficiency can be effectively improved, and the consumption of secondary flow is reduced. The jet direction and the main flow form a certain yaw angle beta, i.e. the included angle between the first nozzle pipe 75 and the second nozzle pipe 76 is 2 beta deg.. The value range of beta is 10-50 degrees.

The air intake chamber 71 is connected to the first pipe 4 or the second pipe 5, and the gas passing through the contraction port 72 is adapted to be output from the first spout pipe 75 or the second spout pipe 76. One end of each of the first nozzle pipe 75, the second nozzle pipe 76, the first feedback channel 73 and the second feedback channel 74 is connected with the outlet of the contraction port 72; the other end of the first feedback passage 73 is connected to the middle of the first orifice pipe 75, and the other end of the second feedback passage 74 is connected to the middle of the second orifice pipe 76.

In particular, said actuators 7 are connected on both inner sides of the vectoring nozzle, part of the actuators 7 being connected to the first duct and part of the actuators 7 being connected to the second duct. The high-pressure gas enters the gas inlet chamber 71 through the first pipe or the second pipe, and is further delivered in the direction of the first spout pipe 75 and the second spout pipe 76 through the contraction port 72. In this embodiment, the first and

second spout ducts

75 and 76 merge at the outlet of the constriction 72, and when fluid flows to the spout duct on one side, the main fluid flows against the side wall surface, and the pressure is reduced. The feedback channel at the front end of the nozzle pipeline at the side enables the guide part to flow back, and pushes the main fluid to be ejected to the nozzle pipeline at the other side, so that pulse type output is formed.

The exciter provided by figure 4 is a double feedback channel oscillation cavity type pulse oscillator which comprises an air inlet cavity, a contraction opening 81, an oscillation cavity 82, a first feedback channel 83, a second feedback channel 84, a first nozzle pipeline 85 and a second nozzle pipeline 86. The jet direction and the main flow form a certain yaw angle beta, i.e. the included angle between the first nozzle pipeline 85 and the second nozzle pipeline 86 is 2 beta degrees. The value range of beta is 10-50 degrees.

Wherein the air inlet chamber is connected to the first pipe 4 or the second pipe 5, and the gas enters the oscillation chamber 82 through the constriction 81. The end of the oscillation cavity 82 connected with the outlet of the contraction port 81 is also connected with one end of the first feedback channel 83 and one end of the second feedback channel 84; the other end of the oscillation chamber 82 remote from the constricted port 81 is connected to the other end of the first feedback passage 83, the other end of the second feedback passage 84, the first orifice pipe 85, and the second orifice pipe 86.

Specifically, the main air flow entering the oscillation chamber 82 through the constricted port 81 is diffused in the oscillation chamber 82, and the main air flow partially flows along one side wall and forms the vortex 200. The main flow along one of the side walls necessarily causes a reduction in the port pressure of the feedback channel at the output of the constriction 81, causing the fluid to flow back along the feedback channel of that side, pushing the main flow towards the other side wall, while the tendency to move towards the other side wall is enhanced by the action of the vortex 200. The primary fluid then flows along the other sidewall and forms a vortex on the opposite side of the primary fluid. It is to be noted that, in order to achieve the adsorption enhancing effect of the vortex, concave guides are formed at the first and

second spout ducts

85 and 86 in this embodiment, so that the main fluid flowing attached to the side wall of the oscillation chamber 82 near the first feedback passage 83 flows out of the second spout duct 86, and the main fluid flowing attached to the side wall of the oscillation chamber 82 near the first feedback passage 83 flows out of the first spout duct 85.

Fig. 5 provides a dual feedback channel cavity type pulse oscillator, which comprises an air inlet cavity 91, a feedback channel 92, a first control port 93, a second control port 94, a first nozzle pipeline 95 and a second nozzle pipeline 96. The air intake chamber 91 is connected to the first duct 4 or the second duct 5, and the gas passing through the contraction port is adapted to be output from the first spout duct 95 or the second spout duct 96. The first nozzle pipeline 95, the second nozzle pipeline 96, the first control port 93 and the second control port 94 are all connected with the outlet of the contraction port; the first control port 93 and the second control port 94 are connected by the feedback passage 92.

In this embodiment, when the main air flow flows along one side wall and is emitted from the collision pipe on the side, the low pressure wave is transmitted to the other control port through the control port on the side and the feedback passage 92, and the swing control of the main fluid is realized by the suction force of the low pressure wave.

The control structure and the control method of the pneumatic thrust vectoring nozzle adopt a flow control strategy, have simple structure, high reliability and strong adaptability, do not need to utilize a complex mechanical structure to change the appearance of the nozzle, and reduce the weight of an aircraft; the resistance of the aircraft cannot be increased due to the change of the shape of the spray pipe; meanwhile, the stealth performance of the aircraft can be obviously improved.

Meanwhile, an unsteady flow control strategy is adopted, so that the control efficiency can be effectively improved, and the consumption of secondary flow is reduced. The novel pulse type fluid oscillation exciter is adopted to generate oscillation jet flow of dozens of to ten thousand hertz, and simultaneously the range influenced by the same outlet area is larger, so that the consumption of an air source is reduced, the single-side exciter array can be independently opened or closed, the inlet flow is adjusted, and the flexible control of the deflection angle of the main jet flow is realized. And because the device does not have any moving part or electromagnetic mechanism, the problems of abrasion, aging and the like caused by moving mechanical parts of other unsteady-state excitation devices and the problem of electromagnetic protection caused by plasma/electromagnetic elements are avoided, and the service life, safety, reliability and robustness of the device are improved.

Referring to the specification and the attached figure 6, a vector nozzle based on self-excited pulse oscillation jet is disclosed. The structure of the embodiment shown in the attached figure 6 and the structure of the embodiment shown in the attached figure 1 can be equivalent or mutually replaced.

Referring to fig. 6-8, the vectoring nozzle includes an airflow outlet 401, a bleed air chamber 402, a primary flow passage 403, an air supply, a switching valve, a first airflow interface 404, an actuator 405, an engine 406, an annular air chamber 407, and a second airflow interface 408. Wherein the airflow outlet 401 is provided integrally with the bleed air chamber 402.

Wherein the front end of the primary channel 403 is tapered and the rear end is regular rectangular or cylindrical, so that the primary air flow can be accelerated after entering the rectangular or cylindrical channel through the front end channel.

The gas flow outlet 401, which is in the form of a trumpet, is connected to the rectangular or cylindrical flow channel end of the main flow channel 403 and forms a throat at the connection. The exciter 405 is located at the throat and deflects the primary air flow by projecting an oscillating airflow towards the throat section. In one embodiment, the exciter 405 is milled into the outer wall surface of the end of the primary channel 403. The upper end surface of the actuator 405 is closed by bringing the end of the main flow passage 403 into contact with the inner wall surfaces of the airflow outlet 401 and the bleed air chamber 402. In another embodiment, the actuator 405 is milled in an intermediate piece that is sandwiched between the main flow passage 403 or the airflow outlet 401 and the inner wall surface of the bleed air chamber 402, and the milled opening of the actuator 405 is closed by the main flow passage 403 or the airflow outlet 401 and the inner wall surface of the bleed air chamber 402.

Typically the exciter has only an overall length of 20mm to 100mm and a height of 2mm to 15 mm. The bleed air chambers are distributed on both sides of the main flow channel 403 and have a larger front end, the ends of the bleed air chambers gradually decrease in height towards the actuator, and the first air flow interface 404 is connected to the bleed air chambers 403 for introducing a high-pressure air source. The gas flow is further accelerated after passing through the constrictions.

More than 98% of the air flow provided by the engine 406 is output through the main flow passage 403, 0.5% -2% of the air flow enters the annular cavity 407 from the air hole 410 arranged on the engine, the annular cavity 407 is provided with a second air flow interface 408, and the second air flow interface 408 is connected with the first air flow interface 404 through a switch valve. By controlling the on/off of the on/off valve, the upper or lower actuator 405 can be selectively caused to output an air flow, thereby controlling the deflection of the main flow.

Be provided with sealing washer 411 on two outer walls of annular cavity 407 and engine 406 outer wall contact, annular cavity 407 is provided with the fracture, fracture department is provided with two lugs 409, leaves 0.5mm-5 mm's clearance between two

lugs

409, and 2 mm's clearance can satisfy the engine and get into smoothly in preferred scheme annular cavity 407, and can comparatively lock fast and stably, make things convenient for engine 406 quilt annular cavity 407 joint is locked two lugs 409 through the retaining member, has reduced the space that annular cavity encircleed, compresses tightly sealing washer 411 to engine 406 wall to sealed has been realized. Referring to fig. 7, the surface of the engine is provided with a plurality of air holes 410. The air holes are positioned in each compressor stator flow guide channel, in order to ensure that the influence of air entraining on the engine can be ignored, if n guide vane channels are provided, the distance between every two flow guide channels is m, the diameter of the air entraining hole is D, and the sum of the sectional areas of all the exciter throats in the single-side spray pipe is A, the air holes need to be arranged in the stator flow guide channels of the compressor, and the air holes need to be arranged in the stator flow guide channels of the compressor, so that the influence of the air entraining on the engine can be ignoredThe following two relationships are satisfied: 1: d<m；2:πnD²/4>10A。

Referring to fig. 9, comparing the deflection state of the main jet of the engine when the engine adopts the conventional straight jet (the upper half of fig. 9) and the self-excited pulse-type oscillation jet (the lower half of fig. 9), it can be seen that the airflow of the exciter reaches 4m³At/h (about 1.03% of the total engine airflow), the self-exciting, pulsed, oscillating jet has been able to maximize the deflection of the engine's main jet along the nozzle's flared opening. When using direct jets, even up to 5m³H (about 1.29 percent of the total air flow of the engine), and the deflection angle of the main air flow of the engine is still smaller than that of the exciter air flow at 3m³The self-excited pulse type oscillating jet flow can enable the deflection angle generated by the main air flow of the engine at the time of/h.

In conclusion, the self-excitation pulse type oscillating jet flow is adopted, so that the excitation slits can become discrete excitation holes, and meanwhile, the high-frequency oscillating jet flow generated by each hole has the effect similar to that of a sector surface, so that the secondary excitation flow can be reduced under the condition that the effect of the excitation slits is similar, and the vector efficiency is improved.

By adopting an unsteady flow control strategy, the control efficiency can be effectively improved, and the consumption of secondary flow is reduced. The novel pulse type fluid oscillation exciter is adopted to generate oscillation jet flow of dozens of to ten thousand hertz, and simultaneously the range influenced by the same outlet area is larger, so that the consumption of an air source is reduced, the single-side exciter array can be independently opened or closed, the inlet flow is adjusted, and the flexible control of the deflection angle of the main jet flow 100 is realized. And because the device does not have any moving part or electromagnetic mechanism, the problems of abrasion, aging and the like caused by moving mechanical parts of other unsteady-state excitation devices and the problem of electromagnetic protection caused by plasma/electromagnetic elements are avoided, and the service life, safety, reliability and robustness of the device are improved.

In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.

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 application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

It will be understood by those skilled in the art that the foregoing embodiments are merely for clarity of description and are not intended to limit the scope of the utility model. Other variations or modifications will occur to those skilled in the art based on the foregoing disclosure and are within the scope of the utility model.

Claims

1. A vectoring nozzle based on self-excited pulsed oscillating jets, comprising an air flow duct, characterized in that: the device also comprises an air source, a switch valve, an exciter, a first pipeline and a second pipeline;

the actuator ejecting gas in a pulse manner along the first sidewall or the second sidewall, the actuator including a first jet channel and a second jet channel from which fluid is ejected in a pulse manner; the included angle between the first nozzle pipeline and the second nozzle pipeline is 2 beta degrees, and the beta angle range is 10-50 degrees.

2. The vectoring nozzle based on a self-exciting pulsed oscillating jet as claimed in claim 1, characterized in that: the exciter also comprises an air inlet cavity, a contraction port, a first feedback channel and a second feedback channel;

the gas inlet cavity is connected with the first pipeline or the second pipeline, and the gas passing through the contraction opening is suitable for being output from the first spout pipeline or the second spout pipeline;

one ends of the first nozzle pipeline, the second nozzle pipeline, the first feedback channel and the second feedback channel are connected with the outlet of the contraction port; the other end of the first feedback channel is connected with the middle of the first nozzle pipeline, and the other end of the second feedback channel is connected with the middle of the second nozzle pipeline.

3. The vectoring nozzle based on a self-exciting pulsed oscillating jet as claimed in claim 2, characterized in that: the exciter also comprises an air inlet cavity, a contraction opening, an oscillation cavity, a first feedback channel and a second feedback channel;

the gas inlet cavity is connected with the first pipeline or the second pipeline, and gas enters the oscillation cavity through the contraction port;

the end part of the oscillation cavity connected with the outlet of the contraction port is also connected with one end of the first feedback channel and one end of the second feedback channel; and the other end part of the oscillation cavity, which is far away from the contraction port, is connected with the other end of the first feedback channel, the other end of the second feedback channel, the first nozzle pipeline and the second nozzle pipeline.

4. The vectoring nozzle based on a self-exciting pulsed oscillating jet as claimed in claim 2, characterized in that: the exciter further comprises an air inlet cavity, a contraction port, a feedback channel, a first control port and a second control port;

the first nozzle pipeline, the second nozzle pipeline, the first control port and the second control port are all connected with the outlet of the contraction port; the first control port is connected with the second control port through the feedback channel.

5. The vectoring nozzle based on self-exciting pulsed waterjets as claimed in any of claims 1-4, characterized in that: the first pipeline and the second pipeline both comprise air-introducing cavities, the air source is an engine, main air flow of the engine enters the air flow pipeline, and lateral air flow of the engine enters the air-introducing cavities.

6. The vectoring nozzle based on a self-exciting pulsed oscillating jet as claimed in claim 5, characterized in that: the air guide cavity is characterized by comprising an annular cavity body, wherein a plurality of air holes are formed in the outer wall surface of the engine, the annular cavity body is covered with the air holes, the engine is collected from the side air flow output by the air holes, and the air flow is output to the air guide cavity through a second interface on the annular cavity body.

7. The vectoring nozzle based on a self-exciting pulsed oscillating jet as claimed in claim 6, characterized in that: and sealing rings are arranged on the two outer walls of the annular cavity, which are in contact with the outer wall of the engine.

8. The vector nozzle based on self-excited pulsed oscillatory jets as claimed in claim 7, characterized in that: the annular cavity is provided with a fracture, the fracture is provided with two lugs, the locking mechanism is locked through locking holes in the lugs, and a gap between the two lugs during locking is smaller than a gap during unlocking.