Air inlet pressure self-balance adjusting device based on shortest feedback path

Abstract

The invention discloses an air inlet channel pressure self-balancing adjusting device based on a shortest feedback path. The air inlet channel pressure self-balancing adjusting device comprises an air inlet channel, a lip cover arranged at an inlet of the air inlet channel and a side plate installed between the air inlet channel and the lip cover, and an air inlet channel inner flow channel is defined by the upper surface of the air inlet channel, the lip cover and the side plate; a plurality of partition plates are arranged in the air inlet channel inner flow channel in parallel, the partition plates are arranged in the air inlet flow direction, and the partition plates divide the inner flow channel into a plurality of inner flow channel units. And when the pressure difference between the two sides of each valve blade exceeds a preset value, the valve blades are opened, and the adjacent inner flow channel units communicate with one another. By arranging the valve blades, shortest feedback path drainage of the two adjacent inner flow channel units is achieved, airflow of the adjacent channels is accelerated, and the overall performance of the air inlet channel is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of air inlets for wide-speed-range aircraft, and particularly to an air inlet pressure self-balancing adjustment device based on the shortest feedback path. Background Art

[0002] As the respiratory tract and compressor in a scramjet propulsion system, the air inlet is responsible for providing an appropriate amount of high-quality air for the engine and compressing the oncoming flow, playing a crucial role in maintaining the stability of the aircraft. For the development of scramjet-powered hypersonic aircraft, the integrated design of the airframe / propulsion system has become the key to improving the overall performance of the aircraft, and the internal and external flow characteristics of the air inlet directly affect the matching efficiency of the aircraft and the propulsion system. Therefore, to meet the strategic needs of future airspace integration operations, ultra-long-range rapid troop deployment, and global rapid strike, the technology of wide Mach number supersonic / hypersonic aircraft and their propulsion systems has become one of the strategic high points in the current aerospace field.

[0003] For hypersonic aircraft, the high degree of integration of the forebody / air inlet, with the leading edge of the airframe as the pre-compression surface of the air inlet, makes the engine thrust very sensitive to changes in parameters such as flight altitude and speed. After the geometric parameters of the air inlet are determined, factors such as flight speed, altitude, and attitude determine the capture flow rate and critical total pressure recovery of the air inlet, thereby affecting the thrust performance of the engine; when the air inlet is adjusted, the aerodynamic force and moment will change accordingly, thereby causing changes in flight speed and attitude. In addition, since the air inlet is a typical pressurizing component, the complex flow phenomenon dominated by shock waves in the pipe is particularly prominent, and the flow separation and swirl structure formed by it will directly affect the aerodynamic force, combustion stability, and the operating envelope of the engine. Especially once the air inlet enters the unstart phenomenon, the induced strong shock wave oscillating flow will directly threaten flight safety. To avoid the aircraft safety problems caused by the unstart of a single air inlet, the integrated design of multiple independent propulsion systems and the fuselage is widely used, and the multi-module air inlets used have characteristics such as variable geometry and multi-channel design for high and low speeds. However, the working process of the multi-module air inlet is relatively complex, and there are differences between modules, which are prone to induce complex cross-module coupling interference flows due to single-engine failure, and even lead to the failure of the entire aircraft.

[0004] Therefore, in order to improve the working performance of the multi-module air inlet under wide-speed-range conditions, it is necessary to design an adjustment device that can adaptively balance the pressure differences between multiple modules to eliminate the negative impacts brought by the flow instability in the single air inlet channel. At the same time, the device should be as simple as possible in structure and should not bring adverse effects under the normal working conditions of the multi-module air inlet. Summary of the Invention

[0005] Objective of the Invention: Aiming at the above disadvantages, the present invention provides an air inlet pressure self - balancing regulating device based on the shortest feedback path.

[0006] Technical Solution: To solve the above problems, the present invention adopts an air inlet pressure self - balancing regulating device based on the shortest feedback path, which includes an air inlet duct, a cowl arranged at the entrance of the air inlet duct, and side plates installed between the air inlet duct and the cowl. The upper surface of the air inlet duct, the cowl, and the side plates surround to form an inner flow path of the air inlet duct; several partitions are arranged in parallel in the inner flow path of the air inlet duct, and the partitions are all arranged along the air inlet flow direction, and the partitions divide the inner flow path into several inner flow path units; a valve blade is hingedly installed on the partition, and when the pressure difference on both sides of the valve blade exceeds a preset value, the valve blade opens to connect adjacent inner flow path units.

[0007] Further, the upper surface of the air inlet duct includes an air inlet duct forebody compression surface and an inner channel compression surface arranged from front to back along the flow direction, and the cowl and the side plates are arranged on the inner channel compression surface.

[0008] Further, a first opening - closing block is provided on the valve blade, and a second opening - closing block corresponding to the first opening - closing block in position is provided on the partition. The first opening - closing block and the second opening - closing block are attracted by a preset gravitational force; when the external force on the valve blade is less than the gravitational force between the first opening - closing block and the second opening - closing block, the valve blade closes, and when the external force on the valve blade is greater than the gravitational force between the first opening - closing block and the second opening - closing block, the valve blade opens.

[0009] Further, both the first opening - closing block and the second opening - closing block are electromagnets with opposite polarities.

[0010] Further, one of the first opening - closing block and the second opening - closing block is a metal block, and the other is an electromagnet.

[0011] Further, the thickness of the partition is equal to the thickness of the valve blade.

[0012] Further, the valve blade is hingedly connected to the partition through a rotating shaft, and at least two springs are also provided between the rotating shaft and the valve blade, and the two springs are respectively used to tension two opposite surfaces of the valve blade.

[0013] Further, an air release slit is opened on the inner channel compression surface, and an air release outlet is opened on the side plate, and the air release slit is communicated with the air release outlet.

[0014] Further, an air release cavity is provided below the inner channel compression surface, and the air release slit and the air release outlet are communicated through the air release cavity.

[0015] Further, multiple mutually parallel air release slits are provided in each inner flow path unit, and the axial direction of the air release slits is perpendicular to the air inlet flow direction.

[0016] Beneficial effects: Compared with the prior art, the significant advantages of the present invention are as follows: (1) By setting the valve blades, the shortest feedback path drainage between adjacent internal flow channel units is achieved, accelerating the airflow in adjacent channels and improving the overall performance of the intake duct; (2) The bleed channel formed by the bleed slot and the bleed outlet also assists in drainage, helping to relieve the high-pressure disturbance in the intake duct and improving the stability of the intake duct; (3) The gravitational force between the two magnets is adjustable to adapt to the pressure characteristics of the intake duct under different downstream backpressures, realizing the stable control of the multi-module intake duct under different flight states, and improving the applicability and flexibility of the device. Brief Description of the Drawings

[0017] Figure 1 It is a schematic diagram of the overall structure of the intake duct pressure self-balancing adjustment device of the present invention;

[0018] Figure 2 It is an enlarged schematic diagram of the structure at the entrance of the internal flow channel of the present invention;

[0019] Figure 3 It is a schematic diagram of the installation structure of the valve blades of the present invention;

[0020] Figure 4 It is a schematic diagram of the bleed channel structure of the present invention;

[0021] Figure 5 It is a schematic diagram of the rotation process of the valve blades of the present invention. Detailed Embodiment

[0022] As Figure 1 and Figure 2 shown, an intake duct pressure self-balancing adjustment device based on the shortest feedback path in this embodiment includes an intake duct, a lip cover 3 arranged at the entrance of the intake duct, and a side plate 4 installed between the intake duct and the lip cover 3. The upper surface of the intake duct includes an intake duct front body compression surface 1 and an internal channel compression surface 2 arranged from front to back along the flow direction. The lip cover 3 and the side plate 4 are arranged on the internal channel compression surface 2, and the internal channel compression surface 2, the lip cover 3, and the side plate 4 surround to form an intake duct internal flow channel. Three partition plates 5 are arranged in parallel in the intake duct internal flow channel, and the partition plates 5 are all arranged along the intake air flow direction. The partition plates 5 divide the internal flow channel into four internal flow channel units.

[0023] As Figure 3 shown, a valve blade 6 is hingedly installed on the partition plate 5. The valve blade 6 is hinged to the partition plate 5 through a rotating shaft 8. Two springs 13 are also arranged between the rotating shaft 8 and the valve blade 6, and the two springs 13 are respectively used to tension the two opposite surfaces of the valve blade 6. The springs 13 are loaded with a pre-tightening force, and the valve blade 6 rotates under the action of the rotating shaft 8 and the springs 13. When the valve blade 6 is closed, the springs 13 apply an equivalent pre-tightening force on both sides of the valve blade 6 in advance, making the forces on both sides of the valve blade 6 uniform and the moment zero. The springs 13 on both sides of the valve blade 6 can stretch back and forth to achieve the stepless rotation of the valve blade 6 to the left and right.

[0024] A first magnet 9 is provided on the valve blade 6, and the first magnet 9 is arranged on the side of the valve blade 6 parallel to its own rotation axis, and a second magnet 10 is provided on the partition 5 at a position corresponding to the first magnet 9. The first magnet 9 and the second magnet 10 have opposite polarities. In this embodiment, the first magnet 9 is the S pole and the second magnet 10 is the N pole. The attraction between the two magnets keeps the valve blade 6 in a balanced state without external interference. The two magnets are electromagnets, and the attraction can be adjusted arbitrarily to control the threshold of opening and closing of the valve blade 6, adapt to the pressure characteristics of different air inlets, and realize stable control of multi-module air inlets under different flight conditions. In addition to being set as electromagnets, a magnetic metal and an electromagnet can also be set on the valve blade and the partition, which can also achieve the effect of mutual attraction and adjustable attraction between the two.

[0025] The valve blade 6 is equal to the thickness of the partition 5, so that when the valve blade 6 is closed, no bulges are formed on both sides of the partition 5, and the valve blade 6 will not have any influence on the flow field of the inner channel.

[0026] like Figure 4 As shown, four discharge slits 11 are also provided on the compression surface 2 of the inner channel, and one row is provided in each inner channel unit, and each row includes a plurality of mutually parallel venting slits 11, and the venting slits 11 are axially perpendicular to the inlet flow direction. The valve blade 6 is arranged upstream of the venting slit 11 along the flow direction, and the venting slit 11 is arranged upstream of the inlet throat 14 along the flow direction. A venting cavity 15 is provided below the compression surface 2 of the inner channel, and a venting outlet 12 is provided on the side plate 4. The venting slit 11 and the venting outlet 12 are connected through the venting cavity 15 to form a venting channel, so that the inner channel of the inlet channel is connected to the external flow field.

[0027] The working principle of the present invention is as follows: First, the gravitational values of the first magnet 9 and the second magnet 10 are set according to the flight state and characteristics of the aircraft. When the pressure difference on both sides of the valve blade 6 is small and the external force on the valve blade 6 does not exceed the gravitational force of the magnets, the valve blade 6 remains in a closed state and each inner flow channel unit works normally. The gravitational force between the two magnets can shield the slight difference between the inner flow channel units on both sides of the partition 5, so that the air inlet can work normally under the upstream non-uniform flow, ensuring the stability of the flow field between each flow channel. When the back pressure of a certain inner flow channel unit increases, the vent slit 11 and the vent outlet 12 are used to complete the flow discharge, and the high-pressure disturbance of the air inlet is alleviated. At this time, the air inlet flow field is not destroyed. If the back pressure increases further, the shock wave train passes over the vent slit 11. At this time, the pressure on one side of the valve blade 6 increases significantly, and the pressure difference force drives the spring 13 to stretch and compress respectively, and the valve blade 6 deflects to one side, such as Figure 5As shown, a bypass flow path 7 is formed to directly connect adjacent internal flow path units. The high-pressure air flow no longer needs to bypass the leading edge of the partition plate 5 and directly discharges through the bypass flow path 7 to achieve the shortest feedback path, and accelerates the air flow in adjacent channels, improving the overall performance of the inlet. When the back pressure of a single flow path decreases, the pressure difference force on both sides of the valve blade 6 gradually decreases. Under the gravitational force of the two magnets, the valve blade 6 gradually turns back and the valve blade 6 gradually closes, and the inlet returns to the normal working state.

[0028] By setting the valve blade, the present invention realizes the discharge of the shortest feedback path between two adjacent internal flow path units, accelerates the air flow in adjacent channels, and improves the overall performance of the inlet. The bleed channel formed by the bleed slot and the bleed outlet also assists in bleeding, helps relieve the high-pressure disturbance of the inlet, and improves the stability of the inlet. The gravitational force of the two magnets is adjustable to adapt to the pressure characteristics of different inlets, realizing the stable control of multi-module inlets under different flight states, and improving the applicability and flexibility of the device.

Claims

1. An intake duct pressure self - balancing adjustment device based on the shortest feedback path, characterized in that It includes an air inlet passage, a lip cover (3) arranged at the entrance of the air inlet passage, and a side plate (4) installed between the air inlet passage and the lip cover (3). The upper surface of the air inlet passage, the lip cover (3), and the side plate (4) surround to form an internal flow passage of the air inlet passage; several partitions (5) are arranged in parallel in the internal flow passage of the air inlet passage, and the partitions (5) are all arranged along the air inlet flow direction. The partitions (5) divide the internal flow passage into several internal flow passage units; a valve vane (6) is hingedly installed on the partition (5). When the pressure difference on both sides of the valve vane (6) exceeds a preset value, the valve vane (6) opens to connect adjacent internal flow passage units.

2. The intake duct pressure self-balancing adjustment device according to claim 1, wherein The upper surface of the air inlet passage includes an air inlet passage front body compression surface (1) and an internal passage compression surface (2) arranged from front to back along the flow direction. The lip cover (3) and the side plate (4) are arranged on the internal passage compression surface (2).

3. The intake air duct pressure self-balancing adjustment device according to claim 1, wherein A first opening and closing block (9) is arranged on the valve vane (6), and a second opening and closing block (10) corresponding to the first opening and closing block (9) in position is arranged on the partition (5). The first opening and closing block (9) and the second opening and closing block (10) are attracted by a preset gravitational force; when the external force received by the valve vane (6) is less than the gravitational force between the first opening and closing block (9) and the second opening and closing block (10), the valve vane (6) closes. When the external force received by the valve vane (6) is greater than the gravitational force between the first opening and closing block (9) and the second opening and closing block (10), the valve vane (6) opens.

4. The intake duct pressure self-balancing adjustment device according to claim 3, wherein, Both the first opening and closing block (9) and the second opening and closing block (10) are electromagnets with opposite polarities.

5. The intake air duct pressure self-balancing adjustment device according to claim 3, wherein One of the first opening and closing block (9) and the second opening and closing block (10) is a metal block, and the other is an electromagnet.

6. The intake duct pressure self-balancing adjustment device according to claim 3, wherein, The thickness of the partition (5) is equal to the thickness of the valve vane (6).

7. The intake air duct pressure self-balancing adjustment device according to claim 1, characterized in that, The valve vane (6) is hinged to the partition (5) through a rotating shaft (8), and at least two springs (13) are further arranged between the rotating shaft (8) and the valve vane (6). The two springs (13) are respectively used to tension two opposite surfaces of the valve vane (6).

8. The intake duct pressure self-balancing adjustment device according to claim 2, wherein An air release slit (11) is opened on the internal passage compression surface (2), and an air release outlet (12) is opened on the side plate (4). The air release slit (11) is communicated with the air release outlet (12).

9. The intake duct pressure self-balancing adjustment device according to claim 8, characterized in that, An air release cavity (15) is arranged below the internal passage compression surface (2), and the air release slit (11) and the air release outlet (12) are communicated through the air release cavity (15).

10. The intake air duct pressure self-balancing adjustment device according to claim 8, characterized in that, A plurality of mutually parallel air release slits (11) are arranged in each internal flow passage unit, and the axial direction of the air release slits (11) is perpendicular to the air inlet flow direction.

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