A large-scale continuous wind tunnel multi-engine inlet test device and test method

Abstract

The present invention belongs to the technical field of wind tunnel tests, and discloses a large-scale continuous wind tunnel multi-engine air inlet test device and test method. The front section of the oblique belly support bracket of the test device is fixed on the lower abdomen of the air inlet model, the oblique belly support bracket and the mounting platform are connected by a variable sideslip angle device, and the rear end of the mounting platform is fixedly connected to the scimitar mechanism of the wind tunnel; the variable sideslip angle device changes the sideslip angle of the air inlet model; and measuring devices such as flow meters and ejectors are fixed on the mounting platform. The test method includes wind tunnel test preparation; conducting wind tunnel tests; and test data processing. The test device and the test method adopt a "oblique belly support + lifting" support method to achieve a perfect combination of the test system and the support system; a hollow telescopic sleeve with ball joints at both ends is adopted to achieve compensation for changes in the length and angle of the airflow pipeline caused by the sideslip angle deflection, which provides a solution for large-scale continuous multi-engine air inlet tests and has engineering practical value.

Description

Technical Field

[0001] The invention belongs to the technical field of wind tunnel tests, and in particular relates to a large-scale continuous wind tunnel multi-engine inlet duct test device and a test method. Background Art

[0002] The air inlet is an important part of the aircraft power system, and is responsible for providing high-quality air for the engine. The performance of the air inlet is directly related to the performance of the power system, and even the improvement of the aircraft's technical and tactical level. With the development of science and technology, the size of aircraft is getting larger and larger. Most large aircraft generally adopt a multi-engine or combined power overall design. In order to improve the comprehensive performance of the air inlet and achieve engine power matching, most aircraft air inlets have adopted additional measures including boundary layer suction holes / slits, venting grooves, auxiliary air inlet valves and auxiliary air discharge valves to varying degrees. The supersonic air inlet also designs a complex secondary flow system to adjust the inlet flow matching, control shock wave / boundary layer interference, and suppress inlet surge. There is a certain interference between the multi-engine air inlets or combined power air inlets of these large aircraft, and the measures such as boundary layer suction holes / slits adopted by them will also have a certain impact on the air inlet performance. Therefore, when obtaining the air inlet performance parameters, it is necessary to simulate the multi-engine air inlet and boundary layer suction holes / slits at the same time.

[0003] Wind tunnel testing is the most direct and reliable technical means to obtain the characteristics of aircraft inlet ducts, and can quickly, systematically and scientifically obtain the performance parameters of aircraft inlet ducts. At present, due to the limitations of model scale and space, these large aircraft inlet duct performance tests are difficult to carry out in 1-2 meter wind tunnels, which can easily cause serious distortion in the simulation of boundary layer suction holes / slots, drain slots, etc.

[0004] Large-scale continuous high-speed wind tunnels above 4 meters provide good basic conditions for multi-engine inlet tests. However, in large-scale continuous high-speed wind tunnels, the model scale and the rotation radius of the mechanism are large, the model load increases exponentially, and the length of the airflow pipeline increases exponentially. In particular, in order to reduce weight, the airflow pipeline, flow meter and ejector can only use thin-walled structures. The model cannot use the flow meter tail support method commonly used in 1-meter to 2-meter wind tunnels, and the uncommon boom support method will also cause the airflow pipeline that is too long downstream of the model to face the contradiction between installation and length adjustment. At the same time, the continuous wind tunnel also requires the test system to be able to achieve continuous adjustment of the angle of attack and the angle of sideslip. The continuous change of the angle of attack can be achieved through the wind tunnel's scimitar mechanism. The design of the multi-engine inlet test device also needs to consider the drive problem of the sideslip angle. Therefore, the design of the support system for the large-scale continuous high-speed wind tunnel multi-engine inlet test model, flow meter and ejector faces great difficulties and great technical difficulty.

[0005] Currently, there is an urgent need to develop a large-scale continuous wind tunnel multi-engine inlet test device and test method. Summary of the invention

[0006] One technical problem to be solved by the present invention is to provide a large-scale continuous wind tunnel multi-engine inlet test device. Another technical problem to be solved by the present invention is to provide a large-scale continuous wind tunnel multi-engine inlet test method, which solves the support problem of large-scale continuous high-speed wind tunnel multi-engine inlet test model and test system, and provides a solution for large-scale continuous multi-engine inlet test.

[0007] The large-scale continuous wind tunnel multi-engine inlet duct test device of the present invention comprises a supporting device, a variable sideslip angle device and a measuring device;

[0008] The support device includes an oblique belly support bracket and a mounting platform. The front section of the oblique belly support bracket is fixed to the lower belly of the air inlet model. The oblique belly support bracket and the mounting platform are connected through a variable sideslip angle device. The rear end of the mounting platform is fixedly connected to the scimitar mechanism of the wind tunnel.

[0009] The variable sideslip angle device adopts a gear transmission mechanism, a chain transmission mechanism, a worm gear transmission mechanism or a track transmission mechanism to realize the rotation of the oblique belly support bracket around the front section of the mounting platform to change the sideslip angle of the air inlet model;

[0010] The measuring device comprises a measuring section, a transfer section, a telescopic sleeve, a flowmeter transfer section, a flowmeter and an ejector which are sequentially connected from front to back, wherein the front and rear ends of the telescopic sleeve are respectively connected to the transfer section and the flowmeter transfer section through a ball joint retaining ring, and the remaining components are connected through flanges; the front end of the measuring section is connected to the air outlet of the inlet duct model, and the airflow at the outlet of the inlet duct model is discharged into the mainstream of the wind tunnel through the measuring section, the transfer section, the telescopic sleeve, the flowmeter transfer section, the flowmeter and the ejector; the flowmeter is fixedly supported by a flowmeter support fixed on the mounting platform, and the ejector is fixedly supported by an ejector support fixed on the mounting platform.

[0011] Furthermore, the track-type transmission mechanism comprises a side-sliding rotating workpiece, an actuating rod, a driving rod, a linear track workpiece, a linear stepping motor and a motor fixing support, and the side-sliding rotating workpiece and the mounting platform are matched with arc surfaces along the central axis direction of the rotating shaft according to the right-hand rule; the front section of the side-sliding rotating workpiece is connected to the rear section of the oblique abdominal support bracket by screws equidistantly distributed around the circumference;

[0012] The linear track workpiece is arranged on the left side of the installation platform. The linear track workpiece is provided with a waist-shaped hole I with an inner diameter of R and parallel to the central axis of the wind tunnel. The waist-shaped hole I is the linear track I.

[0013] A waist-shaped hole II with an inner diameter of R is arranged inside the side-sliding rotating workpiece, the angle between the center line of the waist-shaped hole II and the center line of the waist-shaped hole I is α, and the waist-shaped hole II is the linear track II;

[0014] The linear track I and the linear track II intersect, and the intersection is an inscribed cylindrical cavity with an inner diameter of R and parallel to the central axis of the rotating shaft. A cylindrical actuating rod with an outer diameter of R is inserted into the inscribed cylindrical cavity, and the actuating rod and the linear track I and the linear track II are all linearly matched;

[0015] The linear stepper motor is fixed on the left side of the mounting platform through a motor fixing support, and the driving rod of the linear stepper motor is fixedly connected with the actuating rod.

[0016] Furthermore, the oblique abdominal support bracket has an attack angle pre-bias.

[0017] Furthermore, the telescopic sleeve is provided with sealing rings on the outer surface of the inner sleeve and the inner surface of the outer sleeve respectively.

[0018] Furthermore, the angle α is an acute angle or an obtuse angle according to the right-hand rule.

[0019] Furthermore, the straight track II is replaced by a curved track.

[0020] Furthermore, the linear stepper motor is replaced by a power source for linear motion including an electric cylinder.

[0021] The large-scale continuous wind tunnel multi-engine inlet test method of the present invention comprises the following steps:

[0022] S10. Wind tunnel test preparation;

[0023] A large-scale continuous wind tunnel multi-engine inlet test device is installed in the wind tunnel, and the attitude of the inlet model is adjusted to the initial angle of attack and initial sideslip angle; in conventional tests, the initial angle of attack and initial sideslip angle are both zero degrees; in large angle of attack tests, the angle of attack pre-bias is set by the diagonal belly support bracket, and the initial angle of attack is not zero;

[0024] S20. Conduct wind tunnel tests;

[0025] Start the wind tunnel and establish a stable flow field; adjust the inlet model to the specified angle of attack through the scimitar mechanism, drive the drive rod and the actuator rod to move linearly along the linear track I through the linear stepper motor, force the sideslip rotating workpiece to deflect around the rotation axis, convert the linear motion of the linear stepper motor into the rotational motion of the sideslip rotating workpiece, and adjust the inlet model to the specified sideslip angle position; adjust and measure the outlet airflow flow of the inlet model through the flowmeter, and increase the outlet airflow flow simulation range of the inlet model through the ejector; adjust the wind tunnel flow field speed and the angle of attack and sideslip angle of the inlet model according to the test plan, and complete the measurement of the inlet performance data under all test conditions;

[0026] After the test, the wind tunnel was closed;

[0027] S30. Experimental data processing;

[0028] According to the requirements, the test data is processed to obtain the intake duct characteristics of the intake duct model.

[0029] The large-scale continuous wind tunnel multi-engine inlet duct test device and test method of the present invention have the following characteristics:

[0030] 1. The inlet model is installed on the oblique belly support bracket by the "oblique belly support" method, and the flow meter and ejector are fixed on the installation platform by the flow meter support and ejector support respectively by the "lifting" method; the "oblique belly support + lifting" support method has little interference, and the airflow at the outlet of the inlet model achieves a nearly "straight" flow;

[0031] 2. The "lifting" method is adopted, and flow meters and ejectors of different calibers can be installed on the platform through the flow meter support and ejector support respectively, which is convenient for replacement during wind tunnel testing;

[0032] 3. The oblique belly support bracket and the side sliding rotating workpiece are connected by screws evenly distributed around the circumference, which achieves a certain angle of attack pre-bias and expands the test angle of attack range;

[0033] 4. The sideslip angle of the inlet model is driven by a track-type transmission with high transmission efficiency, which realizes the continuous adjustment of the sideslip angle;

[0034] 5. The hollow telescopic sleeve with ball joints at both ends is used to compensate for the changes in the length and angle of the airflow pipeline caused by the sideslip angle deflection. The ball joints at both ends expand the angle compensation range;

[0035] 6. The sealing rings arranged on the outer surface of the inner sleeve and the inner surface of the outer sleeve of the telescopic sleeve are of "double-layer opposite-side" sealing design, which achieves the requirements of high reliability and smooth telescopic movement.

[0036] In short, the large-scale continuous wind tunnel multi-engine inlet test device and test method of the present invention adopts the "oblique belly support + lifting" support method to achieve a perfect combination of the test system and the support system; and adopts a hollow telescopic sleeve with ball joints at both ends to achieve compensation for the changes in the length and angle of the airflow duct caused by the sideslip angle deflection.

[0037] The large-scale continuous wind tunnel multiple-engine air inlet test device and test method of the present invention solve the support problem of large-scale continuous high-speed wind tunnel multiple-engine air inlet test model and test system, provide a solution for large-scale continuous multiple-engine air inlet test, and have engineering practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 It is a schematic structural diagram of a large-scale continuous high-speed wind tunnel multi-engine inlet duct test device of the present invention;

[0039] Figure 2 It is a partial enlarged view of A of the large-scale continuous high-speed wind tunnel multi-engine inlet duct test device of the present invention.

[0040] In the figure, 1. Inlet duct model; 2. Measuring section; 3. Adapter section; 4. Ball joint retaining ring; 5. Diagonal brace bracket; 6. Telescopic sleeve; 7. Side sliding rotating workpiece; 8. Flow meter adapter section; 9. Actuating rod; 10. Driving rod; 11. Linear track workpiece; 12. Linear stepper motor; 13. Motor fixed support; 14. Flow meter; 15. Flow meter support; 16. Ejector; 17. Ejector support; 18. Installation platform; 19. Scimitar mechanism. DETAILED DESCRIPTION

[0041] The present invention will be further described below in conjunction with the accompanying drawings.

[0042] Example: Figure 1 , Figure 2 As shown, the large-scale continuous wind tunnel multi-engine inlet test device of this embodiment includes a supporting device, a variable sideslip angle device and a measuring device;

[0043] The support device includes an oblique belly support bracket 5 and a mounting platform 18. The front section of the oblique belly support bracket 5 is fixed to the lower belly of the air inlet model 1. The oblique belly support bracket 5 and the mounting platform 18 are connected through a variable side slip angle device. The rear end of the mounting platform 18 is fixedly connected to a scimitar mechanism 19 of the wind tunnel.

[0044] The side slip angle changing device adopts a gear transmission mechanism, a chain transmission mechanism, a worm gear transmission mechanism or a track transmission mechanism to realize the rotation of the oblique belly support bracket 5 around the front section of the mounting platform 18 to change the side slip angle of the air inlet model 1;

[0045] The measuring device includes a measuring section 2, a transition section 3, a telescopic sleeve 6, a flowmeter transition section 8, a flowmeter 14 and an ejector 16 which are connected in sequence from front to back, wherein the front and rear ends of the telescopic sleeve 6 are respectively connected to the transition section 3 and the flowmeter transition section 8 through a ball joint retaining ring 4, and the remaining components are connected through flanges; the front end of the measuring section 2 is connected to the air outlet of the inlet duct model 1, and the outlet airflow of the inlet duct model 1 is discharged into the mainstream of the wind tunnel through the measuring section 2, the transition section 3, the telescopic sleeve 6, the flowmeter transition section 8, the flowmeter 14 and the ejector 16; the flowmeter 14 is fixedly supported by a flowmeter support 15 fixed on a mounting platform 18, and the ejector 16 is fixedly supported by an ejector support 17 fixed on the mounting platform 18.

[0046] Furthermore, the track-type transmission mechanism includes a side-sliding rotating workpiece 7, an actuating rod 9, a driving rod 10, a linear track workpiece 11, a linear stepping motor 12 and a motor fixing support 13. The side-sliding rotating workpiece 7 and the mounting platform 18 are matched with arc surfaces along the central axis direction of the rotating shaft according to the right-hand rule; the front section of the side-sliding rotating workpiece 7 is connected to the rear section of the oblique abdominal support bracket 5 by screws equidistantly distributed around the circumference;

[0047] The linear track workpiece 11 is arranged on the left side of the mounting platform 18. The linear track workpiece 11 is provided with a waist-shaped hole I with an inner diameter of R and parallel to the central axis of the wind tunnel, and the waist-shaped hole I is the linear track I;

[0048] The side sliding rotating workpiece 7 is provided with a waist-shaped hole II with an inner diameter of R, the angle between the center line of the waist-shaped hole II and the center line of the waist-shaped hole I is α, and the waist-shaped hole II is a straight track II;

[0049] The linear track I and the linear track II intersect, and the intersection is an inscribed cylindrical cavity with an inner diameter of R and parallel to the central axis of the rotating shaft. A cylindrical actuating rod 9 with an outer diameter of R is inserted into the inscribed cylindrical cavity. The actuating rod 9 is linearly matched with the linear track I and the linear track II.

[0050] The linear stepper motor 12 is fixed to the left side of the mounting platform 18 through a motor fixing support 13 , and the driving rod 10 of the linear stepper motor 12 is fixedly connected to the actuating rod 9 .

[0051] Furthermore, the oblique abdominal support bracket 5 has a pre-biased angle of attack.

[0052] Furthermore, the telescopic sleeve 6 is provided with sealing rings on the outer surface of the inner sleeve and the inner surface of the outer sleeve respectively.

[0053] Furthermore, the angle α is an acute angle or an obtuse angle according to the right-hand rule.

[0054] Furthermore, the straight track II is replaced by a curved track.

[0055] Furthermore, the linear stepper motor 12 is replaced by a power source for linear motion including an electric cylinder.

[0056] The large-scale continuous wind tunnel multiple-engine inlet test method of this embodiment includes the following steps:

[0057] S10. Wind tunnel test preparation;

[0058] A large-scale continuous wind tunnel multi-engine inlet test device is installed in the wind tunnel, and the posture of the inlet model 1 is adjusted to an initial angle of attack and an initial sideslip angle; in a conventional test, the initial angle of attack and the initial sideslip angle are both zero degrees; in a large angle of attack test, an angle of attack pre-bias is set by the oblique belly support bracket 5, and the initial angle of attack is not zero;

[0059] S20. Conduct wind tunnel tests;

[0060] Start the wind tunnel and establish a stable flow field; adjust the inlet model 1 to the specified angle of attack position through the scimitar mechanism 19, drive the drive rod 10 and the actuator rod 9 to move linearly along the linear track I through the linear stepper motor 12, force the sideslip rotating workpiece 7 to deflect around the rotation axis, convert the linear motion of the linear stepper motor 12 into the rotational motion of the sideslip rotating workpiece 7, and adjust the inlet model 1 to the specified sideslip angle position; adjust and measure the outlet airflow flow rate of the inlet model 1 through the flowmeter 14, and increase the outlet airflow flow rate simulation range of the inlet model 1 through the ejector 16; adjust the wind tunnel flow field speed and the angle of attack and sideslip angle of the inlet model 1 according to the test plan, and complete the measurement of the inlet performance data under all test conditions;

[0061] After the test, the wind tunnel was closed;

[0062] S30. Experimental data processing;

[0063] According to the requirements, the test data is processed to obtain the intake duct characteristics of the intake duct model 1.

[0064] Although the embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the description and the embodiments, and can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional improvements and modifications can be easily realized without departing from the principles of the present invention. Therefore, without departing from the general concept defined by the claims and equivalent scope, the present invention is not limited to the specific details and the illustrations shown and described here.

Claims

1. A large-scale continuous wind tunnel multi-engine inlet test device, characterized in that: The large-scale continuous wind tunnel multi-engine inlet test device comprises a supporting device, a variable sideslip angle device and a measuring device; The support device comprises an oblique belly support bracket (5) and a mounting platform (18), the front section of the oblique belly support bracket (5) is fixed to the lower belly of the air inlet duct model (1), the oblique belly support bracket (5) and the mounting platform (18) are connected via a variable sideslip angle device, and the rear end of the mounting platform (18) is fixedly connected to a scimitar mechanism (19) of the wind tunnel; The side slip angle changing device adopts a track-type transmission mechanism to realize the rotation of the oblique belly support bracket (5) around the front section of the mounting platform (18) to change the side slip angle of the air inlet model (1); The measuring device comprises a measuring section (2), a transfer section (3), a telescopic sleeve (6), a flowmeter transfer section (8), a flowmeter (14) and an ejector (16) which are connected in sequence from front to back, wherein the front and rear ends of the telescopic sleeve (6) are connected to the transfer section (3) and the flowmeter transfer section (8) respectively via a ball joint retaining ring (4), and the remaining components are connected via flanges; the front end of the measuring section (2) is connected to the air outlet of the air inlet model (1), and the outlet airflow of the air inlet model (1) is discharged into the mainstream of the wind tunnel through the measuring section (2), the transfer section (3), the telescopic sleeve (6), the flowmeter transfer section (8), the flowmeter (14) and the ejector (16); the flowmeter (14) is fixedly supported by a flowmeter support (15) fixed on a mounting platform (18), and the ejector (16) is fixedly supported by an ejector support (17) fixed on the mounting platform (18); The track-type transmission mechanism comprises a side-sliding rotating workpiece (7), an actuating rod (9), a driving rod (10), a linear track workpiece (11), a linear stepping motor (12) and a motor fixing support (13); the side-sliding rotating workpiece (7) and the mounting platform (18) are matched with arc surfaces along the central axis direction of the rotating shaft according to the right-hand rule; the front section of the side-sliding rotating workpiece (7) is connected to the rear section of the oblique belly support bracket (5) by screws equidistantly distributed around the circumference; The linear track workpiece (11) is arranged on the left side of the mounting platform (18), and a waist-shaped hole I with an inner diameter R and parallel to the central axis of the wind tunnel is arranged on the linear track workpiece (11), and the waist-shaped hole I serves as the linear track I; The side-sliding rotating workpiece (7) is provided with a waist-shaped hole II with an inner diameter of R, the angle between the center line of the waist-shaped hole II and the center line of the waist-shaped hole I is α, and the waist-shaped hole II is a linear track II; The linear track I and the linear track II intersect, and the intersection is an inscribed cylindrical cavity with an inner diameter R and parallel to the central axis of the rotating shaft. A cylindrical actuating rod (9) with an outer diameter R is inserted into the inscribed cylindrical cavity, and the actuating rod (9) and the linear track I and the linear track II are all linearly matched; The linear stepper motor (12) is fixed to the left side of the mounting platform (18) via a motor fixing support (13), and the driving rod (10) of the linear stepper motor (12) is fixedly connected to the actuating rod (9).

2. The large-scale continuous wind tunnel multiple-engine inlet duct test device according to claim 1 is characterized in that: The oblique abdominal support bracket (5) has an attack angle pre-bias.

3. The large-scale continuous wind tunnel multiple-engine inlet duct test device according to claim 1 is characterized in that: The telescopic sleeve (6) is provided with sealing rings on the outer surface of the inner sleeve and the inner surface of the outer sleeve respectively.

4. The large-scale continuous wind tunnel multiple-engine inlet duct test device according to claim 1 is characterized in that: The angle α is an acute angle or an obtuse angle according to the right-hand rule.

5. The large-scale continuous wind tunnel multiple-engine inlet duct test device according to claim 1 is characterized in that: The linear track II is replaced by a curved track.

6. The large-scale continuous wind tunnel multiple-engine inlet test device according to claim 1 is characterized in that: The linear stepper motor (12) is replaced by a power source for linear motion including an electric cylinder.

7. A large-scale continuous wind tunnel multiple-engine inlet duct test method, which is used in the large-scale continuous wind tunnel multiple-engine inlet duct test device according to claim 1, characterized in that: The following steps are involved: S10. Wind tunnel test preparation; A large-scale continuous wind tunnel multi-engine inlet test device is installed in the wind tunnel, and the attitude of the inlet model (1) is adjusted to an initial angle of attack and an initial sideslip angle; in a conventional test, the initial angle of attack and the initial sideslip angle are both zero degrees; in a high angle of attack test, an angle of attack pre-bias is set by a diagonal belly support bracket (5), and the initial angle of attack is not zero; S20. Conduct wind tunnel tests; Start the wind tunnel and establish a stable flow field; adjust the inlet duct model (1) to a specified angle of attack position through the scimitar mechanism (19); drive the driving rod (10) and the actuator rod (9) to move linearly along the linear track I through the linear stepper motor (12), force the side-slip rotating workpiece (7) to deflect around the rotation axis, convert the linear motion of the linear stepper motor (12) into the rotational motion of the side-slip rotating workpiece (7), and adjust the inlet duct model (1) to a specified side-slip angle position; adjust and measure the outlet airflow flow rate of the inlet duct model (1) through the flow meter (14), and increase the outlet airflow flow rate simulation range of the inlet duct model (1) through the ejector (16); adjust the wind tunnel flow field speed and the angle of attack and sideslip angle of the inlet duct model (1) according to the test plan, and complete the measurement of the inlet duct performance data under all test conditions; After the test, the wind tunnel was closed; S30. Experimental data processing; According to the requirements, the test data is processed to obtain the intake duct characteristics of the intake duct model (1).

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