A compressor integrated vortex swirl distortion simulation device facilitating independent control of swirl

Abstract

The present invention discloses a compressor integral vortex swirl distortion simulation device that is convenient for independently controlling swirl, specifically relating to the technical field of turbomachinery experimental simulation devices. A compressor integral vortex swirl distortion simulation device that is convenient for independently controlling swirl includes a distortion generator body, which is composed of a rotating disk and spoiler rods detachably connected to the rotating disk. A plurality of the spoiler rods are circumferentially and equidistantly distributed on the rotating disk. A driving shaft passes through the center of the rotating disk, and a motor is provided at the free end of the driving shaft. A coupling is provided between the motor and the driving shaft. A bearing is also provided on the driving shaft, and a bearing housing is provided outside the bearing. The technical solution of the present invention provides an integral vortex swirl distortion simulation device that can independently adjust the swirl distortion angle / intensity without being affected by the compressor operating conditions, has a large adjustment range, less energy waste, and is convenient and fast for distortion adjustment.

Description

Technical Field

[0001] The invention relates to the technical field of impeller experimental simulation devices, and in particular to a compressor whole vortex swirl flow distortion simulation device which is convenient for independently controlling swirl flow. Background Art

[0002] S-shaped inlets are widely used in modern aircraft. In addition to their use in auxiliary power units, modern stealth fighters also use them as main engine inlets to shield the engine rotors from direct radar radiation. Advanced missiles employ S-shaped inlets in the middle and rear of the missile body, freeing up space at the front for more payload. Airflow undergoes two significant deflections in an S-shaped inlet, making it prone to separation. This is particularly true during high-intensity maneuvers or sideslips, which can generate strong vortexes and create swirl-distorted intake conditions at the engine inlet. Furthermore, wing-body aircraft, due to their light weight and low drag, are considered promising for widespread application in both military and commercial aviation. However, wing-body aircraft also generate swirl during flight. If this swirl is drawn into the inlet, it can create severe swirl-distorted intake conditions at the engine inlet.

[0003] Swirl distortion inlet conditions have a significant impact on engine operation. In the 1970s, severe surge and blade flutter problems caused frequent mid-flight engine shutdowns in British Tornado fighter jets during flight tests. Investigations determined that the decisive cause of these accidents was swirl distortion at the inlet exit. Subsequent research has shown that, in addition to potentially causing serious accidents such as surge flameout, swirl distortion inlet conditions can also negatively impact engine thrust and significantly increase the probability of high-cycle fatigue failure. Therefore, swirl distortion, as a crucial factor in inlet-engine compatibility studies, must be given due attention during ground-based research.

[0004] When conducting ground-based research on swirl distortion compatibility, it's necessary to first accurately simulate the swirl distortion spectrum at the inlet outlet through certain means, and then study its impact on engine operation. While complex, swirl distortion at the inlet outlet occurs in two basic forms: integral vortex and counter-inverted vortex. Counter-inverted integral vortex swirl distortion has the most significant impact on the compressor characteristic line during intake, presenting the greatest threat. To address these two basic distortion types, swirl distortion generators have been developed over many years, with several types now available, including blade-type, cavity-type, and jet-type.

[0005] Vane-type swirl distortion generators are the most widely used. The most common situation is similar to the pre-whirl vanes of a compressor. However, the swirl vanes are usually distributed in the circular cross-section at the outlet of the inlet duct, rather than in the annular channel like the pre-whirl vanes of a compressor. In addition to the form of uniform distribution in a whole circle, the vanes can also be arranged in groups. By changing the vane angle or camber, the swirl angle and direction can be adjusted. When all the vanes deflect / bend in the same direction, a single vortex flow is generated; when the vanes on both sides deflect / bend symmetrically, a pair of vortex flows is generated. In addition, there are cases where the vane type is customized for a specific swirl distortion pattern, but generally such swirl distortion generators cannot be adjusted and cannot adapt to multiple swirl distortion patterns. The defect of vane-type swirl distortion generators is that when the downstream compressor operating conditions are certain, the adjustment range of the swirl angle / intensity is affected by the flow state on the vane surface where the distortion occurs. When the adjustment angle is too large and significant flow separation occurs on the vane surface, the expected swirl state cannot be formed and a large total pressure loss will be brought. In addition, it is difficult to adjust the vane angle / camber during the experiment, which requires a significant increase in the complexity of the distortion generator.

[0006] The cavity-type swirl distortion generator is installed at the compressor inlet. The inlet air direction is set tangentially to the compressor inlet cross-section. When the air flow is inhaled, a swirl is generated in the cavity and then enters the compressor. Different forms of swirl distortion are generated by changing the cavity shape, and the swirl direction and intensity / angle are adjusted. This method has a simple structure and low cost, but the disadvantages are that the swirl distortion adjustment is coupled with the compressor operating condition adjustment, the swirl intensity is also affected by the compressor flow rate, and the total pressure loss coefficient caused by the distortion generator itself increases significantly when the compressor flow rate increases. In addition, it is also difficult to adjust the cavity shape during the experiment, which requires a significant increase in the complexity of the distortion generator.

[0007] The jet-type swirl distortion generator injects circumferential momentum actively by blowing air through nozzles arranged tangentially to the compressor inlet cross-section. Under the mixing action of the jet and the mainstream, a velocity component of the main air flow in the circumferential direction is generated to form a swirl. The swirl intensity and direction can be controlled by adjusting the jet flow rate and direction. Its active control method is flexible and convenient. It can adjust the swirl distortion intensity / angle independently of the compressor operating conditions and can also be adjusted during the experiment with a large adjustment range. However, the disadvantages are that an additional air source system needs to be equipped, high requirements for the air source and equipment are needed to achieve a large range of adjustment, there are also large aerodynamic losses during the mixing process of the jet and the mainstream, and in order to make the flow field of the mixed air flow as uniform as possible, a long mixing distance or other rapid mixing technical means are needed, which will further increase the aerodynamic losses and also have high design requirements for the distortion generator.

[0008] Most of the distortion generation parts of the above swirl distortion generator are located in the circular cross-section area upstream of the engine inlet, far from the compressor inlet. Since the distortion will naturally decay during the downstream flow, the swirl distortion intensity / angle will decrease when reaching the aerodynamic interface of the compressor inlet annular cross-section. Therefore, the actual distortion amplitude generated at the distortion generator needs to be higher than the distortion amplitude required for engine tests, which will inevitably cause energy waste in this process. Summary of the Invention

[0009] The present invention aims to provide a compressor integral vortex swirl distortion simulation device that is convenient for independently controlling the swirl. The above device can independently adjust the swirl distortion angle / intensity without being affected by the compressor operating conditions, has a large adjustment range, less energy waste, and is convenient and fast for distortion adjustment.

[0010] To achieve the above object, the technical solution of the present invention is as follows: A compressor integral vortex swirl distortion simulation device that is convenient for independently controlling the swirl, including a distortion generator body. The distortion generator body is composed of a rotating disk and spoiler rods detachably connected to the rotating disk. A plurality of the spoiler rods are circumferentially and equidistantly distributed on the rotating disk. A driving shaft passes through the center of the rotating disk. A motor is provided at the free end of the driving shaft. A coupling is provided between the motor and the driving shaft. A bearing is also provided on the driving shaft, and a bearing housing is provided outside the bearing.

[0011] Principle and effect of the technical solution: In this solution, the simulation device can be installed on the test bench with the help of the bearing and the bearing housing. During the simulation process, the motor and the coupling can drive the driving shaft to rotate. After the driving shaft rotates, it drives the rotating disk and the spoiler rods to rotate, thereby adjusting the circumferential velocity component required in the swirl distortion intake condition by means of the movement speed of the spoiler rods. At the same time, different rotation speeds can be achieved with the help of the motor, thus achieving the purpose of free adjustment and being independent of the adjustment of the operating conditions of the test compressor.

[0012] Further, weight-reducing holes are provided on the rotating disk. With the help of the weight-reducing holes, the weight of the simulation device can be reduced, thereby reducing the energy consumption during the simulation process.

[0013] Further, a speed reducer is provided between the coupling and the motor. With the help of the speed reducer, the working characteristics of the simulation device and the motor can be better matched, thereby reducing the waste caused by excessive performance of the motor part.

[0014] Further, a spline sleeve is connected between the rotating disk and the driving shaft.

[0015] Through the above settings, the requirement for the strength of the rotating disk of the simulation device can be reduced, thereby reducing the weight of the simulation device.

[0016] Furthermore, the free ends of all the spoiler rods are jointly covered with a connecting ring. By means of the connecting ring, all the spoiler rods can be connected into a whole, thus enhancing the overall strength of this simulation device.

[0017] Furthermore, a seal is also provided on the rotating wheel disc. Through the seal, the problem of air flow leaking away from the gap between the rotating wheel disc and the inner casing of the annular passage can be alleviated, improving the accuracy of the results of this simulation device.

[0018] Compared with the prior art, the beneficial effects of this application are as follows:

[0019] 1. The magnitude of the circumferential velocity component in the circumferential velocity distortion intake condition depends on the movement speed of the spoiler rod, and its adjustable range is large;

[0020] 2. The circumferential velocity distortion angle / intensity can be adjusted independently of the compressor operating conditions; when the circumferential velocity distortion angle / intensity requirement changes or the compressor operating conditions change, only need to calculate the required circumferential velocity component according to the compressor experimental flow rate, and then adjust the motor to make the rotating wheel disc reach the corresponding speed, and the circumferential velocity distortion angle / intensity can be adjusted, without being restricted by the compressor operating conditions.

[0021] 3. The circumferential velocity distortion occurs in the annular passage, and the position where the circumferential velocity distortion occurs is relatively close to the compressor inlet, with less attenuation of the distorted flow and less energy wasted when reaching the same circumferential velocity distortion angle / intensity;

[0022] 4. The circumferential velocity distortion angle / intensity can be quickly adjusted during the experiment, thus saving experimental time. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is a schematic structural view of Embodiment 1 of the present invention;

[0024] Figure 2 is Figure 1 a partial enlarged view of A in

[0025] Figure 3 is a front view of the distortion generator body in Embodiment 1 of the present invention;

[0026] Figure 4 is a sectional view of the distortion generator body in Embodiment 1 of the present invention;

[0027] Figure 5 is a front view of the distortion generator body in Embodiment 2 of the present invention;

[0028] Figure 6 is a sectional view of the distortion generator body in Embodiment 2 of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0029] The present invention will be further described in detail below through specific embodiments:

[0030] The reference numerals in the attached drawings of the specification include: rotary wheel 1, spoiler rod 2, weight reduction hole 3, spline sleeve 4, drive shaft 5, coupling 6, speed reducer 7, motor 8, angular contact ball bearing 9, cylindrical roller bearing 10, seal 11, outer casing 12, inner casing 13, connecting ring 14, protrusion 15.

[0031] Embodiment 1

[0032] Basically as shown in the attached Figure 1 to the attached Figure 4 As shown: A compressor integral vortex distortion simulation device facilitating independent control of swirl includes a distortion generator body, which is composed of a rotary wheel 1 and spoiler rods 2 threadedly connected to the rotary wheel 1. Four weight reduction holes 3 are circumferentially and equidistantly distributed on the rotary wheel 1. By means of the weight reduction holes 3, the weight of the simulation device can be reduced, thereby reducing the energy loss during the simulation process; the cross-sectional shape of the spoiler rod 2 is circular. Multiple spoiler rods 2 are circumferentially and equidistantly distributed on the rotary wheel 1, and the extension line of the axis of each spoiler rod 2 passes through the center of the rotary wheel 1. Threads are tapped at one end of each spoiler rod 2, and the spoiler rods 2 are threadedly connected to the outer edge of the rotary wheel 1. The outer surface of the part of the spoiler rod 2 extending beyond the rotary wheel 1 is smooth.

[0033] A spline sleeve 4 is also bolted to the center of the rotary wheel 1. The right end of the spline sleeve 4 passes through the rotary wheel 1, and a drive shaft 5 is inserted into the spline sleeve 4. By means of the spline sleeve 4, the strength requirement of the rotary wheel 1 for this simulation device can be reduced, thereby reducing the weight of this simulation device; a cover plate is bolted to the left end of the drive shaft 5, a coupling 6 is bolted to the right end of the drive shaft 5, a speed reducer 7 is connected to the right end of the coupling 6. By means of the speed reducer 7, the torque can be increased. A motor 8 is connected to the right side of the speed reducer 7, and a power supply and a control system (not shown in the figure) are also connected to the motor 8. Among them, the control system adopts a PLC control system in the prior art. By means of the above control system, it is convenient to adjust the rotation speed of the motor 8. Bearings are inserted on both the left and right sides of the drive shaft 5. A pair of angular contact ball bearings 9 are used for the bearing on the left side of the drive shaft 5, and cylindrical roller bearings 10 are used for the bearing on the right side of the drive shaft 5. A bearing seat is covered outside each bearing. By means of the bearing seat, this simulation device can be fixedly installed on the support structure of the test bench.

[0034] As shown in the attached Figure 2 As shown, annular seals 11 are symmetrically bolted to both the left and right sides of the upper part of the rotary wheel 1. The seals 11 can be adopted as shown in the attached Figure 2The "L" shape shown can also be other shapes. Two "V"-shaped protrusions 15 are integrally formed on the seal 11 and are distributed at intervals. The protrusions 15 are close to the inner side wall of the inner casing 13. By means of the seal 11 and the protrusions 15 thereon, the resistance when the air flow passes through the gap between the inner casing 13 and the rotating wheel disc 1 is increased, thus alleviating the problem of gas leakage.

[0035] Working principle and process: Before the simulation of this device, this simulation device is fixed on the support structure of the test bench by means of the bearing seat, so as to facilitate the transfer of various loads to the support structure through the bearings and the bearing seat. This device is arranged in the annular channel at the inlet of the compressor during the simulation. At this time, an appropriate gap is left between the free end of the spoiler rod 2 and the outer casing 12 of the annular channel to avoid the risk of rubbing during operation; at the same time, the outer edge of the rotating wheel disc 1 is flush with the outer edge of the inner casing 13 of the annular channel, and appropriate gaps are left between the left and right sides of the rotating wheel disc 1 and the inner casing 13 of the annular channel to avoid the risk of rubbing on the left and right sides of the rotating wheel disc 1 during operation.

[0036] During the simulation, the motor 8 is started through the control system and the rotation speed of the motor 8 is set. After the motor 8 is started, its rotation speed can be reduced by means of the speed reducer 7 and reach the required rotation speed. The speed reducer 7 drives the drive shaft 5 to rotate through the coupling 6. After the drive shaft 5 rotates, the rotating wheel disc 1 and the spoiler rod 2 can be driven to rotate through the spline sleeve 4. When the spoiler rod 2 rotates with the rotating wheel disc 1, the spoiler rod 2 drives the air flow to rotate in the circumferential direction, so that the air flow passing through the distortion generator body obtains a circumferential velocity component, thus forming the condition for the formation of a whole vortex flow distortion. By adjusting the rotation speed of the rotating wheel disc 1, the disturbance intensity of the spoiler rod 2 on the air flow can be changed, and then the magnitude of the circumferential velocity component obtained by the air flow can be changed, so as to realize the adjustment of the intensity or angle of the whole vortex flow. The adjustment of the magnitude of the circumferential velocity component obtained by the air flow is independent of the adjustment of the operating conditions of the test compressor, thus realizing the decoupling of the swirl distortion adjustment and the adjustment of the operating conditions of the test compressor; and the rotation speed of the rotating wheel disc 1 is adjusted by adjusting the rotation speed of the motor 8, and the operation is simple, greatly improving the efficiency of the experiment.

[0037] Embodiment 2

[0038] As shown in the attached Figure 5 and attached Figure 6 As shown, the difference between this embodiment and Embodiment 1 is only that: a connecting ring 14 is commonly coated outside all the spoiler rods 2. The connecting ring 14 is made of a relatively thin metal. By means of the connecting ring 14, the free ends of all the spoiler rods 2 can be coated and connected together in a hemming manner, thus enhancing the overall stiffness of this device and making this device applicable to the case where the aspect ratio of the part of the spoiler rod 2 exceeding the rotating wheel disc 1 is relatively large or the working rotation speed is relatively high.

[0039] The above are only embodiments of the present invention, and common knowledge such as specific structures and / or characteristics known in the solutions is not described in detail herein. It should be noted that for those skilled in the art, without departing from the structure of the present invention, several modifications and improvements can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the implementation effect of the present invention and the practicality of the patent. The protection scope required by this application shall be subject to the content of its claims, and the specific implementation manners described in the specification can be used to interpret the content of the claims.

Claims

1. A compressor integral vortex flow distortion simulation device facilitating independent control of vortex flow, characterized in that: It includes a distortion generator body, which is composed of a rotating wheel disc and spoiler rods detachably connected to the rotating wheel disc. A plurality of the spoiler rods are circumferentially and equidistantly distributed on the rotating wheel disc. A driving shaft penetrates through the center of the rotating wheel disc. A motor is provided at the free end of the driving shaft. A coupling is provided between the motor and the driving shaft. A bearing is also provided on the driving shaft, and a bearing housing is provided outside the bearing; A seal is also provided on the rotating wheel disc. Two spaced "V"-shaped protrusions are integrally formed on the seal, and the protrusions are close to the inner side wall of the inner casing.

2. The compressor integral vortex swirl distortion simulation device for facilitating independent control of swirl according to claim 1, characterized in that: Weight-reducing holes are formed in the rotating wheel disc.

3. The compressor integrated vortex flow distortion simulation device for facilitating independent control of vortex flow according to claim 2, characterized in that: A speed reducer is provided between the coupling and the motor.

4. A compressor integral vortex swirl distortion simulation device facilitating independent control of swirl according to claim 3, characterized in that: A spline sleeve is connected between the rotating wheel disc and the driving shaft.

5. A compressor integral vortex flow distortion simulation device for facilitating independent control of swirl, characterized in that: A connecting ring commonly covers the free ends of all the spoiler rods.

Images