Fan-shaped afterburner inlet flow field simulation device and control method thereof

Abstract

The invention relates to the field of aero-engine afterburner tests, and discloses a fan-shaped afterburner inlet flow field simulation device and a control method thereof.The fan-shaped afterburner inlet flow field simulation device comprises a linkage ring, a knuckle bearing, a transmission cylinder and a servo electric cylinder, and the telescopic end of the servo electric cylinder stretches out and draws back in the axial direction of an afterburner and is used for driving the transmission cylinder to rotate through stretching out and drawing back; and the corresponding guide blades are driven by the linkage ring and the rocker arms of the other guide blades to rotate along the rotating shafts of the corresponding guide blades. Through the structural design of the servo electric cylinder and the transmission mechanism, the actual inlet flow field state of the fan-shaped afterburner is simulated, and particularly, the angle of the air inlet guide blade can be synchronously adjusted through continuous change, so that the test environment simulation of the fan-shaped afterburner with different air inlet cosine angles is realized; the fan-shaped afterburner inlet airflow cosine angle distribution is obtained, so that the test environment is closer to the real working environment, and the efficient development of the aero-engine afterburner performance test can be supported.

Description

Technical Field

[0001] The present invention relates to the field of afterburner tests for aeroengines, and discloses a simulation device for the inlet flow field of a sector-shaped afterburner and a control method therefor. Background Art

[0002] The afterburner is located between the turbine and the tail nozzle. Since the airflow at the outlet of the low-pressure turbine is non-uniform in the radial, circumferential, and axial directions, this results in a high-speed area and a low-speed area in the velocity distribution of the inner-duct inlet section of the afterburner. For the test piece of the sector-shaped afterburner, the inlet airflow usually adopts a uniform intake method, and there are few test devices that can adjust the inlet airflow, which makes the difference between the inlet flow field of the sector-shaped afterburner test and the actual inlet flow field relatively large, thus affecting the test results. Summary of the Invention

[0003] The purpose of the present invention is to provide a simulation device for the inlet flow field of a sector-shaped afterburner and a control method therefor, which can synchronously adjust the angles of the inlet guide vanes, realize the simulation of the test environment of the sector-shaped afterburner with different inlet cosine angles, obtain the cosine angle distribution of the inlet airflow of the sector-shaped afterburner, and make the test environment closer to the actual working environment.

[0004] In order to achieve the above technical effects, the technical solution adopted by the present invention is:

[0005] A simulation device for the inlet flow field of a sector-shaped afterburner, comprising:

[0006] A linkage ring, which is movably installed on the outer wall of the casing of the sector-shaped afterburner, and the linkage ring is coaxially arranged with the afterburner casing;

[0007] A spherical plain bearing, which is movably installed in the linkage ring, and a spherical plain bearing is provided at the position of the linkage ring corresponding to each guide vane of the afterburner;

[0008] A transmission cylinder, which is drivingly connected to the rotating shaft of the guide vane, and a rocker arm fixedly connected to the spherical plain bearing is further provided on the transmission cylinder;

[0009] A servo electric cylinder, which is installed on the outer wall of the casing of the afterburner through a fixed bracket, and the telescopic end of the servo electric cylinder is drivingly connected to the transmission cylinder through a rocker. The telescopic end of the servo electric cylinder telescopically moves along the axial direction of the afterburner, and is used to drive the transmission cylinder to rotate through telescoping, so as to drive the corresponding guide vane to rotate along the rotating shaft, and drive the corresponding guide vane to rotate along its own rotating shaft through the linkage ring and the rocker arms of other guide vanes.

[0010] Further, a spline shaft is also provided on the transmission cylinder drivingly connected to the servo cylinder. The spline shaft is coaxially arranged with the rotating shaft of the guide vane. The rocker is drivingly connected to the spline shaft through a transmission link and is used to drive the transmission cylinder to rotate through the spline shaft.

[0011] Further, an inner and outer bypass partition is also provided in the casing of the afterburner. The guide vane is located inside the inner and outer bypass partition. The rotating shaft passes through the inner and outer ring partitions and the outer wall of the casing and is drivingly connected to the transmission cylinder.

[0012] Further, a floating sleeve is sleeved on the outer wall of the guide vane corresponding to the inner and outer bypass partition. The outer wall of the floating sleeve is in clearance fit with the hole at the position of the inner and outer bypass partition. The hole is a through hole provided on the inner and outer bypass partition for the rotating shaft to pass through.

[0013] Further, a base is provided at the installation position of the transmission cylinder on the outer wall of the casing. The outer wall of the base is of a cylindrical surface structure. An installation hole in clearance fit with the outer wall of the base is provided at the bottom of the transmission cylinder. A guide hole for the rotating shaft to penetrate is provided in the base. The rotating shaft passes through the guide hole and is drivingly connected to the transmission cylinder.

[0014] Further, the spherical plain bearing is movably installed in the linkage ring through a pin shaft arranged radially.

[0015] To achieve the above technical effects, the present invention also provides a control method for a fan-shaped afterburner inlet flow field simulation device. The control method is based on the fan-shaped afterburner inlet flow field simulation device and includes:

[0016] Construct a three-dimensional model of the inlet flow field simulation device based on the fan-shaped afterburner according to the structural parameters of the fan-shaped afterburner and the structural parameters of the fan-shaped afterburner inlet flow field simulation device;

[0017] Taking different adjustment angles and different blade heights of the guide vane as inputs, use flow field simulation analysis to obtain the inlet cosine angle of the three-dimensional model under the test conditions;

[0018] Taking the blade height and adjustment angle of the guide vane as independent variables and the inlet cosine angle data corresponding to the blade height and adjustment angle under the test conditions as dependent variables, construct an inlet cosine angle analysis model based on the blade height and adjustment angle of the guide vane;

[0019] According to the actual height and inlet cosine angle design of the guide vane in the fan-shaped afterburner, use the analysis model to calculate and obtain the adjustment angle data value of the guide vane in the fan-shaped afterburner;

[0020] The servo electric cylinder is controlled to extend and retract, and the guide blade is driven directly or through a linkage ring to rotate along the corresponding rotation axis to the adjustment angle data value of the guide blade.

[0021] Furthermore, the intake cosine angle analysis model based on the blade height and adjustment angle of the guide vane is constructed as α=16.52+0.4614x+1.749δ-0.01119x 2 -0.01159xδ+4.876×10 -5 x 3 , where ɑ is the inlet cosine angle, x is the blade height, and δ is the adjustment angle of the guide vane.

[0022] Compared with the existing technology, the beneficial effects of the present invention are: the present invention simulates the actual inlet flow field state of the fan-shaped afterburner through the structural design of the servo electric cylinder and the transmission mechanism, especially can realize the simulation of the fan-shaped afterburner test environment with different inlet cosine angles by continuously changing and synchronously adjusting the angle of the intake guide vane, and obtain the cosine angle distribution of the inlet airflow of the fan-shaped afterburner, so that the test environment is closer to the real working environment, which can support the efficient implementation of the performance test of the afterburner of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 A three-dimensional diagram of a fan-shaped afterburner inlet flow field simulation device in an embodiment;

[0024] Figure 2 Schematic diagram of the structure of the sector afterburner inlet flow field simulation device in the embodiment;

[0025] Figure 3 Schematic diagram of the installation structure of the inner and outer culvert partitions and the floating sleeve in the embodiment;

[0026] Among them, 1. Linkage ring; 2. Casing; 3. Spherical bearing; 4. Guide vane; 5. Transmission cylinder; 6. Rocker arm; 7. Servo electric cylinder; 8. Fixed bracket; 9. Rocker; 10. Rotating shaft; 11. Spline shaft; 12. Inner and outer duct partitions; 13. Floating sleeve; 14. Base; 15. Pin shaft. DETAILED DESCRIPTION

[0027] The present invention will be described in further detail below with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the present invention to the following embodiments, as all technologies implemented based on the present invention fall within the scope of the present invention.

[0028] Example

[0029] See also Figures 1-3 , a fan-shaped afterburner inlet flow field simulation device, comprising:

[0030] Linkage ring 1, the linkage ring 1 is movably installed on the outer wall of the casing 2 of the sector afterburner, and the linkage ring 1 is coaxially arranged with the afterburner casing 2;

[0031] Spherical plain bearing 3, the spherical plain bearing 3 is movably installed in the linkage ring 1, and one spherical plain bearing 3 is arranged at the position of the linkage ring 1 corresponding to each guide vane 4 of the afterburner;

[0032] Drive cylinder 5, the drive cylinder 5 is drivingly connected to the rotating shaft 10 of the guide vane 4, and a rocker arm 6 fixedly connected to the spherical plain bearing 3 is further arranged on the drive cylinder 5;

[0033] Servo cylinder 7, the servo cylinder 7 is installed on the outer wall of the casing 2 of the afterburner through a fixed bracket 8, the telescopic end of the servo cylinder 7 is drivingly connected to the drive cylinder 5 through a rocker 9, and the telescopic end of the servo cylinder 7 extends and retracts along the axial direction of the afterburner, and is used to drive the drive cylinder 5 to rotate through telescoping, so as to drive the corresponding guide vane 4 to rotate along the rotating shaft 10, and drive the corresponding guide vane 4 to rotate along its own rotating shaft 10 through the linkage ring 1 and the rocker arms 6 of other guide vanes 4.

[0034] In this embodiment, there are two paths to drive the guide vane 4 to rotate. One is the direct drive method: servo cylinder 7 - rocker 9 - drive cylinder 5 - rotating shaft 10 - guide vane 4; the other is the indirect drive method: servo cylinder 7 - rocker 9 - drive cylinder 5 - linkage ring 1 - rocker arm 6 - rotating shaft 10 - guide vane 4, so as to realize the synchronous transmission of all guide vanes 4. In this embodiment, through the structural design of the servo cylinder 7 and the transmission mechanism, the actual inlet flow field state of the sector afterburner is simulated. Especially, the angle of the inlet guide vane 4 can be continuously changed and synchronously adjusted to realize the simulation of the test environment of the sector afterburner with different inlet cosine angles, obtain the cosine angle distribution of the inlet air flow of the sector afterburner, make the test environment closer to the real working environment, and support the efficient development of the performance test of the aeroengine afterburner.

[0035] In this embodiment, a spline shaft 11 is further arranged on the drive cylinder 5 drivingly connected to the servo cylinder 7. The spline shaft 11 is coaxially arranged with the rotating shaft 10 of the guide vane 4. The rocker 9 is drivingly connected to the spline shaft 11 through a transmission link, and is used to drive the drive cylinder 5 to rotate through the spline shaft 11. The design of the spline shaft 11 enhances the stable drive and transmission efficiency between the drive cylinder 5 and the rotating shaft 10 of the guide vane 4, and ensures that under the drive of the servo cylinder 7, the drive cylinder 5 can accurately and stably drive the guide vane 4 to rotate along a predetermined trajectory. As a key component connecting the rocker 9 and the spline shaft 11, the transmission link has a reasonable structural design and can effectively transmit the driving force.

[0036] In this embodiment, an inner and outer bypass partition 12 is further disposed in the casing 2 of the afterburner. The guide vane 4 is located inside the inner and outer bypass partition 12. The rotating shaft 10 passes through the inner and outer ring partitions and the outer wall of the casing 2 and is drivingly connected to the transmission cylinder 5. The design of the inner and outer bypass partition 12 not only effectively isolates the airflows of the inner and outer bypasses in the afterburner, ensures that the guide vane 4 will not be interfered by the outer bypass airflow when adjusting the angle, and guarantees a smooth flow passage without sudden changes, thus ensuring the accuracy of the test data of the afterburner.

[0037] In this embodiment, a floating sleeve 13 is sleeved on the outer wall of the guide vane 4 corresponding to the inner and outer bypass partition 12. The outer wall of the floating sleeve 13 is in clearance fit with the hole position at the position of the inner and outer bypass partition 12. The hole position is a through hole provided on the inner and outer bypass partition 12 for the rotating shaft 10 to pass through. It can ensure the expansion gap between the outer bypass airflow and the inner bypass airflow at different temperatures, and prevent the expansion deformation under large temperature differences from damaging the entire device.

[0038] In this embodiment, a base 14 is provided on the outer wall of the casing 2 at the installation position of the transmission cylinder 5. The outer wall of the base 14 is a cylindrical surface structure. An installation hole in clearance fit with the outer wall of the base 14 is provided at the bottom of the transmission cylinder 5. A guide hole for the rotating shaft 10 to penetrate is provided in the base 14. The rotating shaft 10 passes through the guide hole and is drivingly connected to the transmission cylinder 5. The setting of the base 14 not only ensures the precise positioning of the rotating shaft 10 during the transmission process, but also provides good guidance and positioning for the installation and rotation of the transmission cylinder 5, ensures that the transmission cylinder 5 is not easily offset during rotation, and realizes the precise adjustment of the angle of the guide vane 4.

[0039] In this embodiment, the spherical plain bearing 3 is movably installed in the linkage ring 1 through a radially arranged pin shaft 15. Ensure that the spherical plain bearing 3 can rotate flexibly in the linkage ring 1. While realizing the flexible adjustment of the angle of the guide vane 4, the disassembly and replacement of the spherical plain bearing 3 can be realized after the spherical plain bearing 3 is worn after long-term use.

[0040] In order to realize the matching adjustment of the intake cosine angle, the present invention also provides a control method for a fan-shaped afterburner inlet flow field simulation device. The control method is based on the fan-shaped afterburner inlet flow field simulation device, and includes:

[0041] Step 1: According to the structural parameters of the fan-shaped afterburner and the structural parameters of the fan-shaped afterburner inlet flow field simulation device, construct a three-dimensional model of the inlet flow field simulation device based on the fan-shaped afterburner.

[0042] Step 2: Taking different adjustment angles and different blade heights of the guide vane 4 as inputs, use flow field simulation analysis to obtain the intake cosine angle of the three-dimensional model under the assessment conditions.

[0043] Step 3: Taking the blade height and adjustment angle of the guide vane 4 as independent variables, and the intake air cosine angle data corresponding to the blade height and adjustment angle under the rated working conditions as the dependent variable, construct an intake air cosine angle analysis model based on the blade height and adjustment angle of the guide vane 4;

[0044] In this embodiment, the intake air cosine angle analysis model based on the blade height and adjustment angle of the guide vane 4 is α = 16.52 + 0.4614x + 1.749δ - 0.01119x 2 - 0.01159xδ + 4.876×10 -5 x 3 , where ɑ is the intake air cosine angle, x is the blade height, and δ is the adjustment angle of the guide vane 4.

[0045] Step 4: According to the actual height and intake air cosine angle design of the guide vane 4 in the fan-shaped afterburner, use the analysis model to calculate and obtain the adjustment angle data value of the guide vane 4 in the fan-shaped afterburner;

[0046] Step 5: Control the telescopic movement of the servo electric cylinder 7 to directly drive or drive the guide vane 4 to rotate along the corresponding rotating shaft 10 to the adjustment angle data value of the guide vane 4 through the linkage ring 1.

[0047] The intake air cosine angle analysis model in this embodiment takes into account the influence of the blade height, and can more accurately obtain the adjustment angle of the guide vane 4 that matches it according to the radial height and intake air cosine angle design value of the guide vane 4 in the fan-shaped afterburner, so as to support the efficient development of the performance test of the aero-engine afterburner.

[0048] The above are only the preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements, and improvements made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims

1. A simulation device for the inlet flow field of a fan-shaped afterburner, characterized in that, include: A linkage ring, the linkage ring being movably mounted on the outer wall of the casing of the sector-shaped afterburner, and the linkage ring is coaxially arranged with the afterburner casing; A spherical joint bearing is movably mounted in the linkage ring, and one spherical joint bearing is provided at the linkage ring position corresponding to each guide vane of the afterburner; A transmission cylinder, the transmission cylinder is drivingly connected to the rotating shaft of the guide blade, and the transmission cylinder is also provided with a rocker arm fixedly connected to the spherical bearing; A servo electric cylinder is mounted on the outer wall of the casing of the afterburner through a fixed bracket. The telescopic end of the servo electric cylinder is connected to the transmission cylinder through a rocker. The telescopic end of the servo electric cylinder is retracted and extended along the axis of the afterburner, and is used to drive the transmission cylinder to rotate through telescoping, so as to drive the corresponding guide blades to rotate along the rotating axis, and to drive the corresponding guide blades to rotate along their own rotating axis through the linkage ring and the rocker arms of other guide blades.

2. The fan-shaped afterburner inlet flow field simulation device according to claim 1, characterized in that A spline shaft is also provided on the transmission cylinder connected to the servo electric cylinder. The spline shaft is coaxially arranged with the rotation axis of the guide blade. The rocker is connected to the spline shaft through a transmission connecting rod and is used to drive the transmission cylinder to rotate through the spline shaft.

3. The fan-shaped afterburner inlet flow field simulation device according to claim 1, wherein The casing of the afterburner is further provided with inner and outer shroud partitions, and the guide vanes are located on the inner sides of the inner and outer shroud partitions; the rotating shaft passes through the inner and outer ring partitions and the outer wall of the casing and is drivingly connected to the transmission cylinder.

4. The fan-shaped afterburner inlet flow field simulation device according to claim 3, characterized in that, A floating sleeve is provided on the outer wall of the guide blade corresponding to the inner and outer culvert partitions. The outer wall of the floating sleeve is clearance-matched with the hole position of the inner and outer culvert partitions. The hole position is a through hole provided on the inner and outer culvert partitions for the rotating shaft to pass through.

5. The fan-shaped afterburner inlet flow field simulation device according to claim 1, characterized in that The outer wall of the casing is provided with a base at the installation position of the transmission cylinder. The outer wall of the base is a cylindrical structure. The bottom of the transmission cylinder is provided with a mounting hole that is clearance-matched with the outer wall of the base; a guide hole for the rotating shaft to pass through is provided in the base, and the rotating shaft is driven and connected to the transmission cylinder after passing through the guide hole.

6. The fan-shaped afterburner inlet flow field simulation device according to claim 1, characterized in that The spherical bearing is movably installed in the linkage ring through a pin shaft arranged in the radial direction.

7. A control method for a simulation device of the inlet flow field of a sector afterburner, the control method being based on the simulation device of the inlet flow field of a sector afterburner according to any one of claims 1-6, characterized in that, include: According to the structural parameters of the sector-shaped afterburner and the structural parameters of the sector-shaped afterburner inlet flow field simulation device, a three-dimensional model of the sector-shaped afterburner inlet flow field simulation device is constructed; Using different adjustment angles and different blade heights of the guide vanes as input, flow field simulation analysis is used to obtain the intake cosine angle of the three-dimensional model under the test conditions; The blade height and adjustment angle of the guide vane are used as independent variables, and the intake cosine angle data corresponding to the blade height and adjustment angle under the test conditions are used as the dependent variable. An intake cosine angle analysis model based on the blade height and adjustment angle of the guide vane is constructed. According to the actual height of the guide vanes in the sector afterburner and the intake cosine angle design, the analytical model is used to calculate the adjustment angle data value of the guide vanes in the sector afterburner; The servo electric cylinder is controlled to extend and retract, and the guide blade is driven directly or through a linkage ring to rotate along the corresponding rotation axis to the adjustment angle data value of the guide blade.

8. The control method of the fan-shaped afterburner inlet flow field simulation device according to claim 7, characterized in that The constructed intake air cosine angle analysis model based on the blade height and adjustment angle of the guide vane is α = 16.52 + 0.4614x + 1.749δ - 0.01119x 2 - 0.01159xδ + 4.876×10 -5 x 3 , where ɑ is the intake air cosine angle, x is the blade height, and δ is the adjustment angle of the guide vane.

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