CN209870723U - Multi-stage blowing circulation volume high-lift device and aircraft - Google Patents
Multi-stage blowing circulation volume high-lift device and aircraft Download PDFInfo
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- CN209870723U CN209870723U CN201920500874.1U CN201920500874U CN209870723U CN 209870723 U CN209870723 U CN 209870723U CN 201920500874 U CN201920500874 U CN 201920500874U CN 209870723 U CN209870723 U CN 209870723U
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- 238000000034 method Methods 0.000 description 3
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Abstract
The utility model provides a multistage ring volume of blowing increases liter device and aircraft relates to aviation aircraft technical field. The multistage blowing circulation high-lift device comprises an airfoil and a coanda trailing edge which are connected, wherein at least two jet ports are arranged on the airfoil and the coanda trailing edge, a first jet port is arranged at the joint of the airfoil and the coanda trailing edge, and a second jet port is arranged on the cambered surface of the coanda trailing edge. Through setting up a plurality of jet ports, the stagnation point of aircraft moves down more, and it is less and the coanda effect is more obvious to rise the resistance, can maximize promotion aircraft lift under same air supply power, improves flight performance.
Description
Technical Field
The utility model relates to an aerocraft technical field particularly, relates to a multistage ring volume of blowing increases and rises device and aircraft.
Background
Conventional mechanical high lift devices include leading edge slats, trailing edge flaps, and the like. These high mechanical lift devices, while producing noise pollution, also add weight to the aircraft and reduce the payload of the aircraft.
And the air blowing and sucking technology is adopted to increase the wing circulation so as to improve the overall lift of the airplane. In the current common single-nozzle annular quantity control device, in order to improve the lift force, the blowing speed needs to be increased, which leads to the increase of the air-entraining quantity. In addition, in order to generate a larger jet flow speed, the total pressure in the air guide cavity needs to be increased, and at the moment, the sprayed jet flow can be blocked at the jet opening, so that the pneumatic performance of the circulation control is not fully exerted.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a multistage ring volume of blowing increases and rises device can control the efflux better and produce higher ring volume to realize increasing the demand of liter drag reduction. And the circulation volume is increased through multi-stage blowing, an additional mechanical high-lift device is not needed, the weight is small, the effective load is increased, and the noise pollution is small.
The utility model discloses an aim at still including providing an aircraft, can realize the purpose of high lift drag reduction, improve the performance of aircraft. Meanwhile, noise pollution is effectively reduced, and the takeoff weight of the aircraft is reduced.
The utility model discloses improve its technical problem and realize with following technical scheme.
The utility model provides a pair of multistage ring volume of blowing increases and rises device is applied to on the wing of aircraft. The multistage blowing circulation high-lift device comprises an airfoil and a coanda trailing edge which are connected, wherein at least two jet ports are arranged on the airfoil and the coanda trailing edge, and the at least two jet ports comprise a first jet port and a second jet port; the first jet orifice is arranged at the joint of the airfoil and the coanda trailing edge, and the second jet orifice is arranged on the cambered surface of the coanda trailing edge.
Further, a distance between the first jet opening and the second jet opening is one third of an arc length of the coanda trailing edge.
Further, the second jet orifice is arranged below the first jet orifice.
Further, the jet flow port further comprises a third jet flow port, and the third jet flow port is arranged on the arc surface of the coanda trailing edge.
Further, a distance between the third jet opening and the first jet opening is two-thirds of an arc length of the coanda trailing edge.
Furthermore, the third jet orifice is arranged below the first jet orifice, and the second jet orifice is positioned between the first jet orifice and the third jet orifice.
Further, a ratio of a height of the jet opening to the coanda trailing edge radius is between 0.4 and 0.8.
Further, the ratio of the height of the jet opening to the coanda trailing edge radius is 0.7.
The utility model provides a pair of aircraft, including aircraft body and foretell multistage ring volume of blowing increase lift device, multistage ring volume of blowing increase lift device is installed on the aircraft body.
Further, an air channel is arranged in the aircraft body, and the jet flow port is communicated with the air channel.
The utility model provides a multistage ring volume of blowing increases and rises device and aircraft have the beneficial effect of following several aspects:
the utility model provides a multistage ring volume of blowing increases and rises device, reach the junction at the trailing edge at wing section and coanda and set up first spout mouth, it spouts the mouth to set up the second on the cambered surface at the trailing edge at coanda, through the two-stage spout mouth, the air current flows when first spout mouth along the upper surface of wing section, because first spout efflux produces the coanda effect, can make the mainstream deflect and flow along the cambered surface that coanda reached the trailing edge, this will postpone the time of air current and cambered surface separation, stay the point promptly and will follow the cambered surface and move backward, increase the lift of wing section or aircraft. Under the boosting of the jet flow of the second jet flow port, the main flow continuously flows along the cambered surface of the coanda trailing edge, the annular volume of the wing profile is further increased, and therefore the lift force of the aircraft is greatly improved.
The utility model provides an aircraft, including foretell multistage circulation volume of blowing increase device, the air current is through multistage spout mouthful after for the wing stays the point and removes on a relatively large scale under a plurality of spout mouthful interact, thereby has increased the circulation of wing, and then increases lift, and for ordinary circulation controlling means, increases to rise the effect and is showing.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic diagram of an application scenario structure of a single-nozzle high lift device;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
fig. 3 is a schematic view of a first structure of the multi-stage blowing ring volume high lift device provided in this embodiment;
FIG. 4 is an enlarged partial view taken at B in FIG. 3;
fig. 5 is a schematic view of a second structure of the multi-stage blowing ring volume increasing device provided in this embodiment;
FIG. 6 is an enlarged partial view at C of FIG. 5;
FIG. 7 is an original airfoil flow-around diagram with zero jet ports on the airfoil;
FIG. 8 is a schematic view of an airfoil profile flow path with a single nozzle disposed on the airfoil;
FIG. 9 is a schematic view of an airfoil profile with dual jet ports on the airfoil;
FIG. 10 is a schematic view of an airfoil with three jet ports on the airfoil.
Icon: 101-an airfoil; 103-air channel; 111-an airfoil profile; 113-coanda trailing edge; 121-a first jet port; 123-a second jet port; 125-third spout.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
In the description of the present invention, it should be understood that the terms "upper" and "lower" are used as the terms of the orientation or the positional relationship based on the drawings, or the orientation or the positional relationship that the product of the present invention is usually placed when using, or the orientation or the positional relationship that the person skilled in the art usually understands, only for the convenience of describing the present invention and simplifying the description, but not for the indication or the suggestion that the device or the element that is referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore, should not be interpreted as the limitation of the present invention.
The terms "first", "second", and the like in the present invention are used only for descriptive distinction and have no special meanings.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed" and "mounted" are to be interpreted broadly, e.g., as being either fixedly connected, detachably connected, or integrally connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In recent centuries, with the rapid development of aviation industry, aircrafts have been widely used in various fields. For example, in military affairs, the device can be used for reconnaissance monitoring, communication relay, electronic countermeasure and the like; for civil use, the method can be used for geodetic surveying, environmental monitoring and the like; in scientific research, the method can be used for atmospheric research, sampling and monitoring nuclear biochemical pollution areas and the like. Along with the expansion of the application field of the aircraft, people have more and more great demands on the aircraft with simple structure, easy control, high space utilization rate and stable flight.
In the high lift technology of an aircraft, mechanical high lift is generally adopted, such as leading edge slats, trailing edge flaps and the like, a mechanical high lift device and a landing gear are main noise generation sources in the taking-off and landing processes of the aircraft, and a high lift mechanism accounts for the main part of noise. However, in the current blowing circulation volume increasing technology, in order to increase the lift, the blowing speed needs to be increased, which leads to the increase of the air-bleed quantity. In addition, in order to generate a larger jet flow speed, the total pressure in the air guide cavity needs to be increased, and at the moment, the sprayed jet flow can be blocked at the jet opening, so that the pneumatic performance of the circulation control is not fully exerted.
In order to overcome the defects of the blowing circulation volume lift increasing technology in the prior art, the application provides the multi-stage blowing circulation volume lift increasing device, so that the aircraft has better pneumatic performance, can better control jet flow to generate higher circulation volume, and further meets the requirements of lift increasing and drag reduction.
Fig. 1 is a schematic view of an application scenario structure of a single-nozzle high lift device, and fig. 2 is a partially enlarged view of a point a in fig. 1, please refer to fig. 1 and fig. 2. The first jet flow port 121 is formed at the connection position of the airfoil 111 and the coanda trailing edge 113, when airflow flows along the upper surface of the airfoil 111 and passes through the first jet flow port 121, the jet flow of the first jet flow port 121 generates a coanda effect, so that the main flow can be deflected and flows along the cambered surface of the coanda trailing edge 113, the time for separating the airflow from the cambered surface is delayed, namely, the stagnation point moves backwards along the cambered surface, and the lift force of the airfoil 111 or an aircraft is increased.
Wherein, the coanda trailing edge 113 is a circular arc surface, and the principle of the increase of the annular volume is as follows: the wing 101 is composed of a fixed wing section 111 and a semicircular trailing edge, a hole or a slit is formed between the fixed wing section 111 and the semicircular trailing edge, due to the viscosity of airflow, high-pressure airflow in a cavity inside the wing section 111 generates jet flow along the object plane in a tangential direction through the hole or the slit, the jet flow and outflow flow are mixed to flow along the surface of the curved circular trailing edge to form a coanda effect, and the semicircular trailing edge is the coanda trailing edge 113.
Fig. 3 is a schematic structural diagram of a first structure of the multi-stage blowing ring volume increasing device according to the present embodiment, and fig. 4 is an enlarged view of a portion at B in fig. 3, please refer to fig. 3 and fig. 4.
The multi-stage blowing circulation volume lift-increasing device provided by the embodiment is applied to the wings 101 of an aircraft, and is used for increasing the lift force of the aircraft and achieving the purpose of lift-increasing and drag-reducing. The multi-stage blowing circulation high lift device comprises an airfoil 111 and a coanda trailing edge 113 which are connected, wherein at least two jet ports are arranged on the airfoil 111 and the coanda trailing edge 113, and the at least two jet ports comprise a first jet port 121 and a second jet port 123. The first jet ports 121 are disposed at the junction of the airfoil 111 and the coanda trailing edge 113, and the second jet ports 123 are disposed on the camber of the coanda trailing edge 113.
It is easy to understand that the multi-stage blowing ring volume high lift device, i.e. the double-nozzle high lift device, is based on a single-nozzle high lift device, and a second jet port 123 is added, optionally, the second jet port 123 is arranged on the arc surface of the coanda trailing edge 113, and the distance between the first jet port 121 and the second jet port 123 is about one third of the entire arc length of the coanda trailing edge 113. Of course, the second jet opening 123 may be disposed below the first jet opening 121, that is, the first jet opening 121 and the second jet opening 123 are located on the same vertical plane, and of course, may not be disposed on the same vertical plane, and is not limited herein. In this embodiment, the second spout 123 and the first spout 121 are located on the same vertical plane.
When the airflow flows along the upper surface of the airfoil 111 through the first jet opening 121, the jet flow of the first jet opening 121 generates the coanda effect, so that the main flow is deflected and flows along the cambered surface of the coanda trailing edge 113, the time for separating the airflow from the cambered surface is delayed, namely the trailing edge stagnation point moves backwards along the cambered surface, and the lift force of the airfoil 111 or the aircraft is increased. Then under the boosting of the jet flow of the second jet flow port 123, the main flow is enabled to continuously flow along the cambered surface of the coanda trailing edge 113, the annular volume of the airfoil 111 is further increased, and therefore the lift force of the aircraft is greatly improved.
Fig. 5 is a schematic diagram of a second structure of the multi-stage blowing ring volume increasing device according to the present embodiment, and fig. 6 is an enlarged view of a portion at C in fig. 5, please refer to fig. 5 and fig. 6.
The multi-stage blowing circulation high lift device is a three-nozzle high lift device, and a third jet port 125 is added on the basis of a double-nozzle high lift device. The third jet 125 is disposed over the arc of the coanda trailing edge 113 and the distance between the third jet 125 and the first jet 121 is about two-thirds of the entire arc length of the coanda trailing edge 113 disposed over the arc of the coanda trailing edge 113. It will be readily appreciated that the junction of the airfoil 111 and the coanda trailing edge 113 is provided with a first jet 121, and the entire arc length of the coanda trailing edge 113 is approximately trisected, with a second jet 123 at the first bisecting point and a third jet 125 at the second bisecting point, wherein the second jet 123 is located between the first jet 121 and the third jet 125. Alternatively, the third injection ports 125 may be disposed on the same vertical plane of the first injection port 121 or the second injection port 123, or may be disposed in a staggered manner, which is not limited herein. In this embodiment, the third spout 125 and the first spout 121 are located on the same vertical plane, and the third spout 125 and the second spout 123 are also located on the same vertical plane.
The sizes of the first jet opening 121, the second jet opening 123 and the third jet opening 125 may be equal or unequal, and optionally, in this embodiment, the three jet openings have the same shape and size, and the ratio of the height h of the jet opening to the radius R of the coanda trailing edge 113 is between 0.4 and 0.8. Preferably, the ratio of the height of the jet to the radius of the coanda trailing edge 113 is 0.7. Through repeated experiments, the ratio is in the range of 0.4 to 0.8, and the better ring volume increasing effect is achieved.
The airflow is ejected through the first jet flow port 121 to generate a coanda effect once, so that the lift force of the aircraft is improved, then the main flow continuously flows downwards along the arc surface and passes through the second jet flow port 123, and the blowing circulation is further increased under the boosting of the jet flow of the second jet flow port 123, so that the lift force of the aircraft is greatly improved. The main flow continues to flow downwards along the arc surface, and when the main flow flows through the third jet port 125, the blowing circulation is further increased under the boosting of the jet flow of the third jet port 125, so that the main flow continues to flow along the arc surface until the air flow is separated from the arc surface. The interaction of the first-stage nozzle, the second-stage nozzle and the third-stage nozzle enables the stagnation point of the wing 101 to move in a large range, so that the circulation of the wing 101 is increased, the lift force is increased, and compared with a common single-nozzle circulation control wing profile, the lift-increasing effect is obvious.
In the embodiment, the kinetic energy of the fluid generated by the jet flow of the first-level nozzle is supplemented by the jet flow of the second-level nozzle and the third-level nozzle after being consumed for a certain distance, so that the circulation is increased, and the occurrence of flow separation can be effectively avoided or inhibited. The mechanism of the multi-stage blowing circulation volume high lift device for generating high lift force is as follows: the air is blown through the jet flow ports arranged on the wings 101 to supplement energy to the boundary layer, so that the separation points of the boundary layer are pushed to move backwards, and meanwhile, the blown air flow generates a 'wrapping and carrying' effect on the outflow, so that the air flow generates a large circulation amount around the flowing of the wing profiles 111, and high lift force is obtained. And the air injection of the multi-stage jet flow port can effectively avoid the phenomenon of airflow blockage at the jet flow port while increasing the lift force. In the wing section 111 of the embodiment, the blowing speed of each jet opening is smaller than that of the common single-nozzle high lift device, and the energy consumed by blowing is proportional to the third power of the blowing speed, so that the pneumatic efficiency of the multi-stage blowing circulation high lift device is relatively higher than that of the common single-nozzle circulation control device.
In order to verify the lift-increasing characteristic of the multi-stage blowing circulation volume lift-increasing device, the utility model carries out a series of flow field analysis, and a zero jet orifice, a single jet orifice, two jet orifices and three jet orifices are respectively arranged on the coanda trailing edge 113 for numerical simulation comparison. And the ratio of the height of the jet flow port to the radius of the circular arc tail circle is uniformly set to be 0.7. The analysis results are shown in the following table:
as can be seen from the table, when there is no nozzle, i.e., zero nozzle, the lift coefficient of the airfoil 111 is 0.2713, the drag coefficient is 0.0201, and the lift-drag ratio is 13.4993; when the single jet orifice is arranged on the coanda trailing edge 113, the trailing edge stagnation point is located at the central point of the coanda trailing edge 113, the lift coefficient is 0.5720, the drag coefficient is 0.0217, and the lift-drag ratio is 26.3716; the double-jet-flow-port arrangement is adopted, the trailing edge stagnation point is positioned in the lower part of the coanda trailing edge 113, the lift coefficient of the airfoil 111 is 0.994, the drag coefficient is 0.0182, and the lift-drag ratio is 54.9121; and by adopting three jet ports, the trailing edge stagnation point position is obviously moved to the bottom of the coanda trailing edge 113, the coanda effect is obvious, the annular quantity around the airfoil profile 111 is increased, the lift coefficient is 1.2368, the drag coefficient is 0.0201, the lift-drag ratio is 61.53, and the overall performance is obviously improved.
Fig. 7 is an original airfoil type flow-around diagram when a zero jet orifice is provided on the airfoil 101, fig. 8 is an airfoil type flow-around diagram when a single jet orifice is provided on the airfoil 101, fig. 9 is an airfoil type flow-around diagram when a double jet orifice is provided on the airfoil 101, and fig. 10 is an airfoil type flow-around diagram when a three jet orifice is provided on the airfoil 101. The X coordinate and the Y coordinate represent the specific positions of the components on the wing 101, and the units are millimeters. The graph at 130 shows streamlines and 140 shows trailing edge stagnation points, where the streamlines reflect the flow of the gas stream in the vicinity of the components, i.e., the flow field characteristics.
The data analysis in the figures and the tables shows that under the same pressure input condition, the three-jet-opening circulation volume increase device can enable the stagnation point to move downwards more, the lift resistance to be smaller and the wall attachment effect to be more obvious compared with a single jet opening and a double jet opening, and the lift-drag ratio is increased as a whole. In this way, the lift of the aircraft can be maximized at the same source power.
The aircraft provided by the embodiment comprises an aircraft body and the multistage blowing circulation high lift device, wherein the multistage blowing circulation high lift device is arranged on the aircraft body. Specifically, an air channel 103 is arranged in the aircraft body, and the jet flow port is communicated with the air channel 103. The jet channel 103 is connected with an air source, the air source can be obtained by the rotation of a turbofan, high-pressure air flow is sprayed out from each jet port along the jet channel 103, and sprayed jet flow and outflow flow are mixed and flow along the surface of the curved circular trailing edge to form a coanda effect, so that the cyclic lift is increased, the lift force of an aircraft is improved, and the purposes of increasing lift and reducing drag are achieved.
To sum up, the utility model provides a multistage ring volume of blowing increases and rises device and aircraft has the beneficial effect in several following aspects:
the utility model provides a multistage annular volume of blowing increases liter device and aircraft through setting up multistage jet orifice, can effectively avoid the air current to spout the blocking phenomenon of mouthful department when locating to can produce many times coanda effect, multistage jet orifice interact makes the trailing edge stagnation point of wing 101 realize removal on a large scale, thereby has increased wing 101's annular volume, and then increases lift, effectively improves the aerodynamic performance of aircraft. The aircraft with the multi-stage blowing circulation volume high lift device has the advantages of simple structure, easy control, higher pneumatic efficiency and realization of the purpose of high lift and drag reduction.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not intended to limit the present invention, which may be modified, combined, and varied by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A multi-stage blowing circulation volume high lift device is characterized in that the device is applied to wings of an aircraft; the multistage blowing circulation high-lift device comprises an airfoil and a coanda trailing edge which are connected, wherein at least two jet ports are arranged on the airfoil and the coanda trailing edge, and the at least two jet ports comprise a first jet port and a second jet port; the first jet opening is arranged at the joint of the airfoil and the coanda trailing edge, and the second jet opening is arranged on the cambered surface of the coanda trailing edge.
2. The multi-stage high lift apparatus of claim 1, wherein the distance between said first jet and said second jet is one third of the arc length of said coanda trailing edge.
3. The multi-stage air-blowing circulation volume-increasing device as claimed in claim 1, wherein the second jet orifice is arranged below the first jet orifice.
4. The multi-stage high lift device with blown air circulation of claim 1, wherein said jet ports further comprise a third jet port, said third jet port being disposed on an arc surface of said coanda trailing edge.
5. The multi-stage high lift apparatus of claim 4, wherein the distance between said third jet and said first jet is two thirds of the arc length of said coanda trailing edge.
6. The multi-stage air blowing circulation volume increasing device as claimed in claim 4, wherein the third jet orifice is arranged below the first jet orifice, and the second jet orifice is arranged between the first jet orifice and the third jet orifice.
7. The multi-stage high lift apparatus of one of claims 1 to 6, wherein the ratio of the height of the jet orifice to the coanda trailing edge radius is between 0.4 and 0.8.
8. The multi-stage high lift apparatus with air blowing rings of claim 7, wherein the ratio of the height of said jet orifice to the radius of said coanda trailing edge is 0.7.
9. An aircraft comprising an aircraft body and a multi-stage high blow-through-ring volume lift device according to any one of claims 1 to 8, mounted on the aircraft body.
10. The aircraft of claim 9 wherein an air jet channel is provided in the aircraft body, the jet port communicating with the air jet channel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920500874.1U CN209870723U (en) | 2019-04-12 | 2019-04-12 | Multi-stage blowing circulation volume high-lift device and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920500874.1U CN209870723U (en) | 2019-04-12 | 2019-04-12 | Multi-stage blowing circulation volume high-lift device and aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN209870723U true CN209870723U (en) | 2019-12-31 |
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|---|---|---|---|
| CN201920500874.1U Withdrawn - After Issue CN209870723U (en) | 2019-04-12 | 2019-04-12 | Multi-stage blowing circulation volume high-lift device and aircraft |
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|---|---|
| CN (1) | CN209870723U (en) |
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- 2019-04-12 CN CN201920500874.1U patent/CN209870723U/en not_active Withdrawn - After Issue
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