A multifunctional turbine driven fan simulator and its test method

Abstract

The present invention belongs to the technical field of aerospace aerodynamic test and evaluation, and discloses a multifunctional turbine-driven fan simulator and a test method thereof. The simulator includes an upstream measuring section, an adjustable guide vane section, a fan section, a downstream measuring section and an adjustable nozzle section connected in sequence through flanges; the inner cavity of the adjustable nozzle section is installed with a high-pressure turbine drive system; the high-pressure turbine drive system includes a high-pressure air collecting chamber, a turbine inlet guide plate, a high-pressure turbine and a turbine tail cone connected in sequence from front to back, and the driving shaft of the high-pressure turbine is fixedly connected to the fan rotor of the fan section forward. The test method includes determining the test task of the multifunctional turbine-driven fan simulator; installing and adjusting the multifunctional turbine-driven fan simulator; inputting high-pressure gas; adjusting the external environment; adjusting the adjustable nozzle section for the first time; adjusting the adjustable nozzle section multiple times; and leaving the surge boundary. The simulator and its test method meet the evaluation requirements of the coupling between the propulsion system and the fuselage of a high-stealth aircraft through more realistic simulation.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace aerodynamic test and evaluation, and in particular relates to a multifunctional turbine-driven fan simulator and a test method thereof. Background Art

[0002] With the continuous improvement of the requirements for stealth performance of aircraft, fusion body layout, large curvature air intake system and high thrust-to-weight ratio turbofan engine have been more widely used. Correspondingly, the importance of evaluating the coupling effect between aircraft propulsion system and fuselage has gradually become prominent.

[0003] Currently, propulsion system and fuselage coupling impact tests conducted in high-speed wind tunnels primarily utilize a turbine-powered simulator (TPS). The TPS uses high-pressure gas to drive the first-stage fan, simulating the fan's flow. The essence of the TPS is to provide flow simulation capabilities for propulsion system and fuselage coupling impact tests. For example, in integrated testing of large civil aircraft wings, nacelles, and TPSs, the ventilation flow rate is varied by changing the TPS speed. The aerodynamic changes at different flow rates are then measured to determine the overflow resistance characteristics of the large civil aircraft.

[0004] However, the turbofan engine has inlet guide vanes in front of the inlet, and the high-stealth inlet has strong swirl, which leads to an enhanced coupling effect between the inlet and the fan. Since the TPS lacks inlet guide vanes and does not measure interstage performance, the flow rate and speed cannot be independently adjusted, and the fan cannot be forced or de-pressed, which fails to meet the simulation requirements. Therefore, it is necessary to develop a multifunctional turbine-powered fan simulator and test methods for wind tunnel propulsion system and airframe coupling impact testing. The multifunctional turbine-powered fan simulator (TPFS) is required to have inlet guide vanes, interstage performance measurement, independent speed and flow rate adjustment, and fan forced and de-pressed functions. Summary of the Invention

[0005] One technical problem to be solved by the present invention is to provide a multifunctional turbine-driven fan simulator, and another technical problem to be solved is to provide a test method for the multifunctional turbine-driven fan simulator.

[0006] The multifunctional turbine-driven fan simulator of the present invention comprises an upstream measurement section, an adjustable guide vane section, a fan section, a downstream measurement section and an adjustable nozzle section, which are sequentially connected by flanges from front to back along a central axis.

[0007] The inner cavity of the multifunctional turbine-driven fan simulator includes, arranged in sequence from front to back, a measuring rake of the upstream measuring section, fan guide vanes of the adjustable guide vane section, fan rotor and fan stator of the fan section, and a measuring rake of the downstream measuring section. The inner cavity of the adjustable nozzle section is equipped with a high-pressure turbine drive system.

[0008] The high-pressure turbine drive system includes a high-pressure plenum chamber, a turbine inlet guide plate, a high-pressure turbine, and a turbine tail cone, which are connected in sequence from front to back. The high-pressure turbine drive shaft is fixedly connected to the fan rotor of the fan section forward. The multifunctional turbine drive fan simulator is fixed to the base through the inlet flange of the high-pressure plenum chamber.

[0009] The high-pressure airflow enters the high-pressure plenum chamber from the high-pressure turbine drive system's high-pressure intake duct, and then drives the high-pressure turbine to rotate after being rectified by the turbine inlet guide plate. The torque generated by the high-pressure turbine is transmitted to the upstream fan section through the drive shaft, achieving synchronous rotation of the fan rotor of the fan section and the high-pressure turbine. The high-pressure airflow after work is discharged through the flow channel formed by the turbine tail cone and the fixed inner casing of the adjustable nozzle section.

[0010] The pressure range of high-pressure air flow is 0.2MPa~1.5MPa.

[0011] Furthermore, the upstream measuring section is of a rotating body configuration; two symmetrical outer casing auxiliary supports are provided below the upstream measuring section for assisting in fixing the multifunctional turbine-driven fan simulator; the front and rear ends of the upstream measuring section are flange ends, the flange ends are fixed ends, the middle section is the measuring section I, and the front and rear sides of the measuring section I are fixedly connected to the corresponding flange ends by a sliding seal; a measuring rake is provided in the central cavity of the measuring section I; an outer gear ring structure is also provided on the outer periphery of the measuring section, and the motor and gear of the outer gear ring structure are used to realize the circumferential rotation of the measuring section I within the range of ±22.5°, thereby realizing the position adjustment and sweep measurement of the measuring rake;

[0012] The downstream measuring section is also a rotating body configuration; the front and rear ends of the downstream measuring section are flange ends, and the middle section is measuring section II;

[0013] On the inner wall of measuring section I and measuring section II, 4 to 10 measuring rakes are evenly distributed along the circumference, and the measuring points of each measuring rake are in the form of single point or composite form of total temperature and total pressure.

[0014] Furthermore, the adjustable guide vane segment includes a plurality of fan guide vanes evenly distributed along the circumferential direction, and the central axis of each fan guide vane extends along the radial direction of the adjustable guide vane segment and is connected to a floating ring. The floating ring is mounted on the adjustable guide vane segment, and the floating ring drives each fan guide vane to rotate synchronously through a connecting rod mechanism. The rotation angle range is ±15°, and the adjustment accuracy of the rotation angle is 0.1°; an angle indicator dial is also provided on the outer periphery of the adjustable guide vane segment for indicating the angle value of the rotation angle.

[0015] Furthermore, the fan segment includes a fan rotor and a fan stator connected in sequence; the fan rotor includes N blades with a swept design that are evenly distributed along the circumference of the inner wall of the fan segment; the fan rotor has a blade disk diameter of 260 mm and a maximum speed of 32,000 RPM; the fan stator includes 2N blades with a double arc blade shape that are evenly distributed along the circumference of the inner wall of the fan segment.

[0016] Furthermore, the adjustable nozzle section includes a fixed inner casing, a sliding outer casing mounted on the fixed inner casing, and servo actuators evenly distributed along the outer circumference of the sliding outer casing; the fixed end of the servo actuator is fixed to the downstream measuring section;

[0017] Through the synchronous extension and retraction of the servo actuator, the flow direction position of the sliding outer casing is adjusted, and then the flow path profile between the fixed inner casing and the sliding outer casing is adjusted, the nozzle outlet area of ​​the adjustable nozzle section is changed, and the downstream back pressure of the fan section and the fan forced and retreated breathing tests are realized.

[0018] Furthermore, the high-pressure air inlet pipe of the high-pressure air collecting chamber of the high-pressure turbine drive system adopts an elliptical cross-section.

[0019] Furthermore, the fan rotor of the fan section and the high-pressure turbine of the high-pressure turbine drive system are sealed with an elastic open ring, which reduces friction between rotating parts through high-pressure circuit lubricating oil and takes away heat at the same time.

[0020] Furthermore, the total pressure rake, static pressure measuring hole, total temperature measuring rake, total pressure and total temperature integrated measuring rake, single-point total temperature measuring rake and wall static pressure hole are replaced with pressure sensors, pulsating pressure sensors and temperature sensors for the purpose of measuring total pressure, static pressure and total temperature; the measuring points are rearranged or monitoring probes are added according to the measurement requirements of total pressure, static pressure and total temperature.

[0021] Furthermore, the fan rotor of the fan section is replaceable and the fan stator is removable;

[0022] The fan guide vanes of the adjustable guide vane section have two working states: installation and removal. When installed, the multifunctional turbine-driven fan simulator realizes 1.5-stage fan simulation. After removal, the multifunctional turbine-driven fan simulator realizes single-stage fan simulation.

[0023] The test method of the multifunctional turbine driven fan simulator of the present invention comprises the following steps:

[0024] S10. Determine the test tasks of the multifunctional turbine-driven fan simulator;

[0025] The multifunctional turbine-driven fan simulator is suitable for conducting ground tests or wind tunnel tests. After final assembly, the multifunctional turbine-driven fan simulator can be used individually or in combination. When used individually, an air intake bell mouth is added to the front end of the upstream measurement section to carry out fan performance measurements. When used in combination, a scaled-down model of the aircraft's air intake system is connected to the front end of the upstream measurement section to carry out fan performance measurements, or the total pressure, static pressure, and total temperature data obtained from the upstream measurement section are used to evaluate the air intake system performance.

[0026] S20. Install and adjust the multi-function turbine-driven fan simulator;

[0027] Connect the air hoses and signal lines for pressure and temperature measurement on the upstream and downstream measurement sections, turn on the measurement system, and check and confirm that the measurement signals are normal; adjust the rotation angle of the fan guide vanes of the adjustable guide vane section to the preset position and lock the connecting rod mechanism; check the sliding outer casing of the adjustable nozzle section to confirm that the sliding is normal, and adjust the nozzle outlet area to the maximum; connect the high-pressure air inlet pipe of the high-pressure gas collecting chamber of the high-pressure turbine drive system to an external high-pressure air source, and check and confirm that the pressure regulating system of the high-pressure air source is working properly;

[0028] S30. Input high-pressure gas;

[0029] Adjust the temperature and pressure of the high-pressure gas to the starting state through the high-pressure gas source pressure regulating valve, and inject high-pressure gas into the high-pressure gas collecting chamber through the high-pressure air intake pipeline. The high-pressure gas drives the fan rotor of the fan section to rotate and maintain the idle state. Check and confirm that the measurement signals of the upstream and downstream measurement sections are normal, and confirm that the fan rotor rotates normally;

[0030] S40. Adjust the external environment;

[0031] Adjust the external environment. For wind tunnel tests, start the high-speed wind tunnel and establish a high-speed flow field. For ground tests, use natural air intake and empty the test chamber. Adjust the temperature and pressure of the high-pressure gas to the pre-set target state. Continue to idle the fan rotor and maintain a stable speed. Obtain total pressure, static pressure, and total temperature data, calculate the flow field parameters of the intake section of the upstream measurement section and the exhaust section of the downstream measurement section, and then calculate the total pressure distortion of the flow field, the total pressure recovery coefficient, the fan pressure ratio, and the fan efficiency.

[0032] S50. First adjustment of the adjustable nozzle section;

[0033] The servo actuator is used to adjust the sliding outer casing of the adjustable nozzle section to change the nozzle outlet area and adjust the temperature and pressure of the high-pressure gas accordingly to ensure that the fan rotor reaches a stable speed. The total pressure, static pressure and total temperature data are obtained to calculate the flow field parameters of the inlet section of the upstream measurement section and the exhaust section of the downstream measurement section, and then the total pressure distortion of the flow field, the total pressure recovery coefficient, the fan pressure ratio and the fan efficiency are calculated.

[0034] S60. Multiple adjustments to the adjustable nozzle section;

[0035] Repeat S50 to obtain a corresponding curve between the pressure of the high-pressure gas and the stable speed of the fan rotor according to a pre-set nozzle outlet area sequence until the fan rotor reaches the surge boundary;

[0036] S70. Leave the surge boundary;

[0037] When the fan rotor shows signs of surge, quickly slide the outer casing back to the starting position, restore the nozzle outlet area to its maximum, and gradually reduce the temperature and pressure of the high-pressure gas until the fan rotor reaches idle speed.

[0038] S80. Turn off the multi-function turbine drive fan simulator;

[0039] Slowly close the high-pressure air source and allow the fan rotor to stop naturally. Check and confirm that the measurement signals of the upstream and downstream measurement sections are normal. Turn off the measurement system. Check and confirm that the structure of the fan simulation device of the multifunctional turbine-driven fan simulator is normal and end the test.

[0040] The high-pressure turbine drive system is the core system of the multi-functional turbine-driven fan simulator. It is responsible for the operation and regulation of the multi-functional turbine-driven fan simulator. At the same time, it serves as the main load-bearing structure to provide support for the fan section, high-pressure turbine, drive shaft, bearings and sliding outer casing. The high-pressure air intake duct of the high-pressure collecting chamber adopts an elliptical cross-section, which reduces the disturbance of the high-pressure air intake duct on the fan section airflow and improves the aerodynamic stability of the multi-functional turbine-driven fan simulator.

[0041] The multifunctional turbine-driven fan simulator simulates the inlet guide vanes of a turbofan engine, a 1.5-stage fan, or a single-stage fan by installing removable fan guide vanes and fan stators. It measures and evaluates the inlet flow field characteristics and fan performance through upstream and downstream measurement sections. Adjusting the nozzle outlet area through an adjustable nozzle allows for regulation of flow rate and downstream pressure. By adjusting the turbine drive pressure, the multifunctional turbine-driven fan simulator can achieve forced and withdrawn gasping functions at a constant fan speed. By adopting an elliptical cross-section in the high-pressure inlet duct, the fan section diameter is reduced to less than or equal to 260mm, effectively reducing the disturbance of the high-pressure inlet duct on the fan flow field.

[0042] In short, the multifunctional turbine-driven fan simulator of the present invention adopts an integrated aerodynamic and structural design of a high-pressure turbine drive system, taking into account both aerodynamic performance and the main load-bearing structure requirements of the device. With the cooperation of the auxiliary support of the external casing, the structural vibration is small and the safety factor is high, which solves the technical problems of high-quality air intake and strong anti-seismic support of the turbine-driven fan simulator, and has the advantages of high turbine speed accuracy and good simulator vibration suppression. At the same time, the functions of inlet guide vanes, inter-stage performance measurement, independent adjustment of speed and flow, fan forced breathing and retreat breathing, etc. are synchronously realized in a confined space. The test method of the multifunctional turbine-driven fan simulator of the present invention can be used for direct-connected tests of ground intake distortion, and can also meet the requirements of high-speed wind tunnel fuselage, air inlet and fan integrated tests, providing a more realistic simulation capability for the evaluation of the coupling effect between the aircraft propulsion system and the fuselage, and meeting the requirements of the coupling evaluation between the propulsion system and the fuselage of high-stealth aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 A schematic structural diagram (overall structure) of a multifunctional turbine-driven fan simulator of the present invention;

[0044] Figure 2 A schematic structural diagram (internal structure) of a multifunctional turbine-driven fan simulator of the present invention;

[0045] Figure 3 Schematic diagram of the structure of the upstream measurement section of the multifunctional turbine-driven fan simulator of the present invention;

[0046] Figure 4 It is a schematic structural diagram of the adjustable guide vane section of the multifunctional turbine-driven fan simulator of the present invention;

[0047] Figure 5 It is a structural schematic diagram of the fan section of the multifunctional turbine-driven fan simulator of the present invention;

[0048] Figure 6 It is a schematic structural diagram of the downstream measurement section of the multifunctional turbine-driven fan simulator of the present invention;

[0049] Figure 7a Schematic diagram of the overall structure of the adjustable nozzle section of the multifunctional turbine-driven fan simulator of the present invention;

[0050] Figure 7b A schematic diagram of the maximum opening of the adjustable nozzle section of the multifunctional turbine-driven fan simulator of the present invention;

[0051] Figure 7c Schematic diagram of the minimum opening of the adjustable nozzle section of the multifunctional turbine-driven fan simulator of the present invention;

[0052] Figure 8This is a schematic structural diagram of the high-pressure turbine drive system of the multifunctional turbine-driven fan simulator of the present invention.

[0053] In the figure, 1. Upstream measurement section; 2. Adjustable guide vane section; 3. Fan section; 4. Downstream measurement section; 5. Adjustable nozzle section; 6. High-pressure turbine drive system;

[0054] 1-1. Outer gear ring structure; 1-2. Total pressure rake; 1-3. Static pressure measuring hole; 1-4. Total temperature rake; 1-5. External casing auxiliary support;

[0055] 2-1. Fan guide vane; 2-2. Floating ring; 2-3. Connecting rod mechanism; 2-4. Angle indicator plate;

[0056] 3-1. Fan rotor; 3-2. Fan stator;

[0057] 4-1. Total pressure and total temperature integrated rake; 4-2. Single point total temperature rake; 4-3. Wall static pressure hole;

[0058] 5-1. Sliding outer casing; 5-2. Fixed inner casing; 5-3. Servo actuator;

[0059] 6-1. High-pressure plenum chamber; 6-2. Turbine inlet guide plate; 6-3. High-pressure turbine; 6-4. Drive shaft; 6-5. Turbine tail cone. DETAILED DESCRIPTION

[0060] The present invention will be described in detail below with reference to the accompanying drawings and embodiments.

[0061] Example: Figure 1 、 Figure 2 As shown, the multifunctional turbine-driven fan simulator of this embodiment includes an upstream measurement section 1, an adjustable guide vane section 2, a fan section 3, a downstream measurement section 4, and an adjustable nozzle section 5, which are sequentially connected along the central axis from front to back via flanges.

[0062] The inner cavity of the multifunctional turbine-driven fan simulator includes, arranged in order from front to back, a measuring rake of the upstream measuring section 1, a fan guide vane 2-1 of the adjustable guide vane section 2, a fan rotor 3-1 and a fan stator 3-2 of the fan section 3, and a measuring rake of the downstream measuring section 4. The inner cavity of the adjustable nozzle section 5 is installed with a high-pressure turbine drive system 6.

[0063] like Figure 8 As shown, the high-pressure turbine drive system 6 includes a high-pressure plenum chamber 6-1, a turbine inlet guide plate 6-2, a high-pressure turbine 6-3, and a turbine tail cone 6-5, which are connected in sequence from front to back. The drive shaft 6-4 of the high-pressure turbine 6-3 is fixedly connected to the fan rotor 3-1 of the fan section 3 in front. The multifunctional turbine drive fan simulator is fixed to the base through the inlet flange of the high-pressure plenum chamber 6-1.

[0064] The high-pressure airflow enters the high-pressure air collecting chamber 6-1 from the high-pressure turbine drive system 6 through the high-pressure air intake pipe. After being rectified by the turbine inlet guide plate 6-2, it drives the high-pressure turbine 6-3 to rotate. The torque generated by the high-pressure turbine 6-3 is transmitted to the upstream fan section 3 through the drive shaft 6-4, achieving synchronous rotation of the fan rotor 3-1 of the fan section 3 and the high-pressure turbine 6-3. The high-pressure airflow after work is discharged through the flow channel formed by the turbine tail cone 6-5 and the fixed inner casing 5-2 of the adjustable nozzle section 5.

[0065] The pressure range of high-pressure air flow is 0.2MPa~1.5MPa.

[0066] Furthermore, if Figure 3 As shown, the upstream measuring section 1 is a rotating body configuration; two left-right symmetrical outer casing auxiliary supports 1-5 are provided below the upstream measuring section 1 for assisting in fixing the multifunctional turbine-driven fan simulator; the front and rear ends of the upstream measuring section 1 are flange ends, the flange ends are fixed ends, the middle section is the measuring section I, and the front and rear sides of the measuring section I are fixedly connected to the corresponding flange ends by a sliding seal; a measuring rake is provided in the central cavity of the measuring section I; an outer gear ring structure 1-1 is further provided on the periphery of the measuring section, and the circumferential rotation of the measuring section I within the range of ±22.5° is achieved by the motor and gear of the outer gear ring structure 1-1, thereby realizing the position adjustment and sweep measurement of the measuring rake;

[0067] like Figure 6 As shown, the downstream measuring section 4 is also a rotating body configuration; the front and rear ends of the downstream measuring section 4 are flange ends, and the middle section is the measuring section II;

[0068] On the inner wall of measuring section I and measuring section II, 4 to 10 measuring rakes are evenly distributed along the circumference, and the measuring points of each measuring rake are in the form of single point or composite form of total temperature and total pressure.

[0069] On the inner wall of the measuring section I of this embodiment, eight total pressure measuring rakes 1-2 and two total temperature measuring rakes 1-4 are evenly distributed along the circumference, and a corresponding static pressure measuring hole 1-3 is provided at the root of each total pressure measuring rake 1-2; five total pressure probes are arranged at the center point of equal annular area of ​​the total pressure measuring rake 1-2, and the total temperature measuring rake 1-4 is a single-point total temperature probe located at the 90% radius position.

[0070] The inner wall of measurement section II of this embodiment is equipped with eight integrated total pressure and temperature measuring rakes 4-1 and eight wall static pressure holes 4-3, as well as two single-point total temperature measuring rakes 4-2, which are evenly spaced along the circumference. The total pressure measuring points of the integrated total pressure and temperature measuring rakes 4-1 are arranged according to the center positions of five equal annular areas. The total temperature measuring points of the single-point total temperature measuring rakes 4-2 are located at the center of the flow channel, near the second and fourth total pressure measuring points of the adjacent integrated total pressure and temperature measuring rakes 4-1, and are positioned according to the results of numerical simulation.

[0071] Furthermore, if Figure 4As shown, the adjustable guide vane segment 2 includes a plurality of fan guide vanes 2-1 uniformly distributed along the circumferential direction, and the central axis of each fan guide vane 2-1 extends along the radial direction of the adjustable guide vane segment 2 and is connected to the floating ring 2-2. The floating ring 2-2 is mounted on the adjustable guide vane segment 2, and the floating ring 2-2 drives each fan guide vane 2-1 to rotate synchronously through the connecting rod mechanism 2-3. The rotation angle range is ±15°, and the adjustment accuracy of the rotation angle is 0.1°. The outer periphery of the adjustable guide vane segment 2 is also provided with an angle indicator disk 2-4 for indicating the angle value of the rotation angle.

[0072] Further, if Figure 5 As shown, the fan segment 3 includes a fan rotor 3-1 and a fan stator 3-2 connected in sequence; the fan rotor 3-1 includes N blades with a swept design that are evenly distributed along the circumference of the inner wall of the fan segment 3; the fan rotor 3-1 has a blade disk diameter of 260 mm and a maximum speed of 32000 RPM; the fan stator 3-2 includes 2N blades with a double arc blade shape that are evenly distributed along the circumference of the inner wall of the fan segment 3.

[0073] In this embodiment, N=16.

[0074] Further, if Figure 7a 、 Figure 7b 、 Figure 7c As shown, the adjustable nozzle section 5 includes a fixed inner casing 5-2, a sliding outer casing 5-1 mounted on the fixed inner casing 5-2, and servo actuators 5-3 evenly distributed along the outer circumference of the sliding outer casing 5-1; the fixed end of the servo actuator 5-3 is fixed to the downstream measuring section 4;

[0075] By synchronously extending and retracting the servo actuator 5-3, the flow direction position of the sliding outer casing 5-1 is adjusted, and then the flow path profile between the fixed inner casing 5-2 and the sliding outer casing 5-1 is adjusted, the nozzle outlet area of ​​the adjustable nozzle section 5 is changed, and the downstream back pressure of the fan section 3 and the fan forced and retreated breathing tests are realized.

[0076] In this embodiment, there are four servo actuators 5-3.

[0077] Furthermore, the high-pressure air intake pipe of the high-pressure air collecting chamber 6 - 1 of the high-pressure turbine drive system 6 adopts an elliptical cross-section.

[0078] Furthermore, the fan rotor 3-1 of the fan section 3 and the high-pressure turbine 6-3 of the high-pressure turbine drive system 6 are sealed with an elastic open ring, which reduces the friction between the rotating parts through high-pressure circuit lubricating oil and takes away the heat at the same time, thereby realizing high-speed, stable and safe operation of the multi-functional turbine-driven fan simulator.

[0079] Furthermore, the total pressure measuring rake 1-2, static pressure measuring hole 1-3, total temperature measuring rake 1-4, total pressure and total temperature integrated measuring rake 4-1, single point total temperature measuring rake 4-2 and wall static pressure hole 4-3 are replaced with pressure sensors, pulsating pressure sensors and temperature sensors for the purpose of measuring total pressure, static pressure and total temperature; the measuring points are rearranged or monitoring probes are added according to the measurement requirements of total pressure, static pressure and total temperature.

[0080] Furthermore, the fan rotor 3-1 of the fan section 3 is replaceable and the fan stator 3-2 is removable;

[0081] The fan guide vane 2-1 of the adjustable guide vane section 2 has two working states: installation and removal. When installed, the multifunctional turbine-driven fan simulator realizes 1.5-stage fan simulation. After removal, the multifunctional turbine-driven fan simulator realizes single-stage fan simulation.

[0082] The test method of the multifunctional turbine driven fan simulator of this embodiment includes the following steps:

[0083] S10. Determine the test tasks of the multifunctional turbine-driven fan simulator;

[0084] The multifunctional turbine-driven fan simulator is suitable for conducting ground tests or wind tunnel tests. After final assembly, the multifunctional turbine-driven fan simulator can be used individually or in combination. When used individually, an air intake bell mouth is added to the front end of the upstream measurement section 1 to carry out fan performance measurements. When used in combination, a scaled-down model of the aircraft's air intake system is connected to the front end of the upstream measurement section 1 to carry out fan performance measurements, or the total pressure, static pressure, and total temperature data obtained from the upstream measurement section 1 are used to evaluate the air intake system performance.

[0085] S20. Install and adjust the multi-function turbine-driven fan simulator;

[0086] Connect the pressure and temperature measuring hoses and signal lines on the upstream measuring section 1 and the downstream measuring section 4, turn on the measuring system, and check and confirm that the measuring signals are normal; adjust the rotation angle of the fan guide vane 2-1 of the adjustable guide vane section 2 to the preset position, and lock the connecting rod mechanism 2-3; check the sliding outer casing 5-1 of the adjustable nozzle section 5 to confirm that the sliding is normal, and adjust the nozzle outlet area to the maximum; connect the high-pressure air intake line of the high-pressure gas collecting chamber 6-1 of the high-pressure turbine drive system 6 to an external high-pressure air source, and check and confirm that the pressure regulating system of the high-pressure air source is operating normally;

[0087] S30. Input high-pressure gas;

[0088] Adjust the temperature and pressure of the high-pressure gas to the starting state through the high-pressure gas source pressure regulating valve, and inject high-pressure gas into the high-pressure gas collecting chamber 6-1 through the high-pressure air intake pipeline. The high-pressure gas drives the fan rotor 3-1 of the fan section 3 to rotate and maintain the idle state. Check and confirm that the measurement signals of the upstream measurement section 1 and the downstream measurement section 4 are normal, and confirm that the fan rotor 3-1 is rotating normally;

[0089] S40. Adjust the external environment;

[0090] Adjust the external environment. For wind tunnel tests, start the high-speed wind tunnel and establish a high-speed flow field. For ground tests, use natural air intake and empty the test chamber. Adjust the temperature and pressure of the high-pressure gas to the pre-set target state. Continue to idle the fan rotor 3-1 and maintain a stable speed. Obtain total pressure, static pressure, and total temperature data, calculate the flow field parameters of the intake section of the upstream measurement section 1 and the exhaust section of the downstream measurement section 4, and then calculate the total pressure distortion of the flow field, the total pressure recovery coefficient, the fan pressure ratio, and the fan efficiency.

[0091] S50. First adjustment of the adjustable nozzle section 5;

[0092] The sliding outer casing 5-1 of the adjustable nozzle section 5 is adjusted via the servo actuator 5-3 to change the nozzle outlet area and adjust the temperature and pressure of the high-pressure gas accordingly to ensure that the fan rotor 3-1 reaches a stable speed. The total pressure, static pressure, and total temperature data are obtained to calculate the flow field parameters of the inlet cross-section of the upstream measurement section 1 and the exhaust cross-section of the downstream measurement section 4. Furthermore, the total pressure distortion of the flow field, the total pressure recovery coefficient, the fan pressure ratio, and the fan efficiency are calculated.

[0093] S60. Multiple adjustments to the adjustable nozzle section 5;

[0094] Repeat S50 to obtain a corresponding curve between the pressure of the high-pressure gas and the stable speed of the fan rotor 3 - 1 according to a pre-set nozzle outlet area sequence until the fan rotor 3 - 1 reaches the surge boundary;

[0095] S70. Leave the surge boundary;

[0096] When the fan rotor 3-1 shows signs of surge, the outer casing 5-1 is quickly moved back to the starting position, the nozzle outlet area is restored to its maximum, and the temperature and pressure of the high-pressure gas are gradually reduced until the fan rotor 3-1 reaches the idle state;

[0097] S80. Turn off the multi-function turbine drive fan simulator;

[0098] Slowly close the high-pressure air source, and the fan rotor 3-1 will stop naturally. Check and confirm that the measurement signals of the upstream measurement section 1 and the downstream measurement section 4 are normal. Turn off the measurement system, check and confirm that the structure of the fan simulation device of the multifunctional turbine-driven fan simulator is normal, and end the test.

[0099] Although the embodiments of the present invention have been disclosed as above, they are not limited to the applications listed in the description and implementation methods. For those familiar with the art, all features disclosed in the present invention, or all steps in the disclosed methods or processes, except for mutually exclusive features and / or steps, can be combined in any way without departing from the principles of the present invention. The present invention is not limited to the specific details and illustrations shown and described herein.

Claims

1. A multifunctional turbine driven fan simulator, characterized in that: The multifunctional turbine-driven fan simulator comprises an upstream measuring section (1), an adjustable guide vane section (2), a fan section (3), a downstream measuring section (4), and an adjustable nozzle section (5) which are sequentially connected along a central axis from front to back via flanges. The inner cavity of the multifunctional turbine driven fan simulator includes a measuring rake of an upstream measuring section (1), a fan guide vane (2-1) of an adjustable guide vane section (2), a fan rotor (3-1) and a fan stator (3-2) of a fan section (3), and a measuring rake of a downstream measuring section (4), which are arranged in sequence from front to back. A high pressure turbine drive system (6) is installed in the inner cavity of the adjustable nozzle section (5); The high-pressure turbine drive system (6) includes a high-pressure air collecting chamber (6-1), a turbine inlet guide plate (6-2), a high-pressure turbine (6-3) and a turbine tail cone (6-5) connected in sequence from front to back, a drive shaft (6-4) of the high-pressure turbine (6-3) is fixedly connected to the fan rotor (3-1) of the fan section (3) forward; a multifunctional turbine drive fan simulator is fixed to the base through the inlet flange of the high-pressure air collecting chamber (6-1); The high-pressure airflow enters the high-pressure air collecting chamber (6-1) from the high-pressure air inlet pipe of the high-pressure turbine drive system (6), and then drives the high-pressure turbine (6-3) to rotate after being rectified by the turbine inlet guide plate (6-2). The torque generated by the high-pressure turbine (6-3) is transmitted to the upstream fan section (3) through the drive shaft (6-4), thereby realizing the synchronous rotation of the fan rotor (3-1) of the fan section (3) and the high-pressure turbine (6-3). The high-pressure airflow after work is discharged through the flow channel formed by the turbine tail cone (6-5) and the fixed inner casing (5-2) of the adjustable nozzle section (5); The pressure range of high-pressure air flow is 0.2MPa~1.5MPa.

2. The multifunctional turbine driven fan simulator according to claim 1, characterized in that: The upstream measuring section (1) is a rotating body configuration; two left-right symmetrical outer casing auxiliary supports (1-5) are provided below the upstream measuring section (1) for assisting in fixing the multifunctional turbine-driven fan simulator; the front and rear ends of the upstream measuring section (1) are flange ends, the flange ends are fixed ends, the middle section is the measuring section I, and the front and rear sides of the measuring section I are fixedly connected to the corresponding flange ends by a sliding seal; a measuring rake is provided in the central cavity of the measuring section I; an outer gear ring structure (1-1) is further provided on the outer periphery of the measuring section, and the circumferential rotation of the measuring section I within the range of ±22.5° is realized by the motor and gear of the outer gear ring structure (1-1), thereby realizing the position adjustment and sweep measurement of the measuring rake; The downstream measuring section (4) is also a rotating body configuration; the front and rear ends of the downstream measuring section (4) are flange ends, and the middle section is the measuring section II; On the inner wall of measurement section I and measurement section II, 4 to 10 measuring rakes are evenly distributed along the circumference. Each measuring rake measures total temperature and total pressure in a single point or composite form to obtain total pressure, static pressure and total temperature data. On the inner wall of the measuring section I, eight total pressure measuring rakes (1-2) and two total temperature measuring rakes (1-4) are evenly distributed along the circumference, and a corresponding static pressure measuring hole (1-3) is provided at the root of each total pressure measuring rake (1-2); five total pressure probes are arranged on the total pressure measuring rake (1-2) according to the center point of the equal annular area, and the total temperature measuring rake (1-4) is a single-point total temperature probe located at the 90% radius position; On the inner wall of the measuring section II, there are 8 total pressure and total temperature integrated measuring rakes (4-1) and 8 wall static pressure holes (4-3) evenly spaced along the circumference, as well as 2 single-point total temperature measuring rakes (4-2); the total pressure measuring points of the total pressure and total temperature integrated measuring rake (4-1) are arranged according to the center positions of 5 equal annular areas; the total temperature measuring point of the single-point total temperature measuring rake (4-2) is located in the center of the flow channel, near the second and fourth total pressure measuring points of the adjacent total pressure and total temperature integrated measuring rake (4-1), and is positioned according to the numerical simulation results.

3. The multifunctional turbine driven fan simulator according to claim 2, characterized in that: The adjustable guide vane segment (2) comprises a plurality of fan guide vanes (2-1) uniformly distributed along the circumferential direction, the central axis of each fan guide vane (2-1) extending radially along the adjustable guide vane segment (2) and connected to a floating ring (2-2), the floating ring (2-2) being mounted on the adjustable guide vane segment (2), the floating ring (2-2) driving each fan guide vane (2-1) to rotate synchronously via a connecting rod mechanism (2-3), the rotation angle range being ±15°, and the adjustment accuracy of the rotation angle being 0.1°; an angle indicator disk (2-4) is also provided on the outer periphery of the adjustable guide vane segment (2) for indicating the angle value of the rotation angle.

4. The multifunctional turbine driven fan simulator according to claim 3, characterized in that: The fan section (3) includes a fan rotor (3-1) and a fan stator (3-2) connected in sequence; the fan rotor (3-1) includes N blades with a swept design and uniformly distributed along the circumference of the inner wall of the fan section (3); the fan rotor (3-1) has a blade disk diameter of 260 mm and a maximum speed of 32,000 RPM; the fan stator (3-2) includes 2N blades with a double arc blade shape and uniformly distributed along the circumference of the inner wall of the fan section (3).

5. The multifunctional turbine driven fan simulator according to claim 4, characterized in that: The adjustable nozzle section (5) comprises a fixed inner casing (5-2), a sliding outer casing (5-1) mounted on the fixed inner casing (5-2), and servo actuators (5-3) uniformly distributed along the outer periphery of the sliding outer casing (5-1); the fixed end of the servo actuator (5-3) is fixed to the downstream measuring section (4); By synchronously extending and retracting the servo actuator (5-3), the flow direction position of the sliding outer casing (5-1) is adjusted, and then the flow path profile between the fixed inner casing (5-2) and the sliding outer casing (5-1) is adjusted, the nozzle outlet area of ​​the adjustable nozzle section (5) is changed, and the downstream back pressure of the fan section (3) and the fan forced and retreated breathing tests are realized.

6. The multifunctional turbine driven fan simulator according to claim 5, characterized in that: The high-pressure air intake pipe of the high-pressure air collecting chamber (6-1) of the high-pressure turbine drive system (6) adopts an elliptical cross-section.

7. The multifunctional turbine driven fan simulator according to claim 6, characterized in that: The fan rotor (3-1) of the fan section (3) and the high-pressure turbine (6-3) of the high-pressure turbine drive system (6) are sealed with an elastic open ring, which reduces friction between rotating parts through high-pressure circuit lubricating oil and takes away heat at the same time.

8. The multifunctional turbine driven fan simulator according to claim 7, characterized in that: The total pressure measuring rake (1-2), static pressure measuring hole (1-3), total temperature measuring rake (1-4), total pressure and total temperature integrated measuring rake (4-1), single point total temperature measuring rake (4-2) and wall surface static pressure hole (4-3) are replaced with pressure sensors, pulsating pressure sensors and temperature sensors for achieving the purpose of total pressure, static pressure and total temperature measurement; and the measuring points are rearranged or monitoring probes are added according to the measurement requirements of the total pressure, static pressure and total temperature.

9. The multifunctional turbine driven fan simulator according to claim 8, characterized in that: The fan rotor (3-1) of the fan section (3) is replaceable, and the fan stator (3-2) is removable; The fan guide vane (2-1) of the adjustable guide vane section (2) has two working states: installation and removal. When installed, the multifunctional turbine-driven fan simulator realizes 1.5-stage fan simulation; when removed, the multifunctional turbine-driven fan simulator realizes single-stage fan simulation.

10. A test method for a multifunctional turbine-driven fan simulator, used for the multifunctional turbine-driven fan simulator according to claim 9, characterized in that: The test method comprises the following steps: S10. Determine the test tasks of the multifunctional turbine-driven fan simulator; The multifunctional turbine-driven fan simulator is suitable for conducting ground tests or wind tunnel tests; after the multifunctional turbine-driven fan simulator is assembled, it can be used alone or in combination; when used alone, an air intake rectifier bell mouth is added to the front end of the upstream measuring section (1) to carry out fan performance measurement; when used in combination, a scaled model of an aircraft air intake system is connected to the front end of the upstream measuring section (1) to carry out fan performance measurement, or the total pressure, static pressure and total temperature data obtained by the upstream measuring section (1) are used to evaluate the air intake system performance; S20. Install and adjust the multi-function turbine-driven fan simulator; Connect the pressure and temperature measuring hoses and signal lines on the upstream measuring section (1) and the downstream measuring section (4), turn on the measuring system, check and confirm that the measuring signals are normal; adjust the rotation angle of the fan guide vane (2-1) of the adjustable guide vane section (2) to the preset position, and lock the connecting rod mechanism (2-3); check the sliding outer casing (5-1) of the adjustable nozzle section (5), confirm that the sliding is normal, and adjust the nozzle outlet area to the maximum; connect the high-pressure air intake pipe of the high-pressure air collecting chamber (6-1) of the high-pressure turbine drive system (6) to the high-pressure air source, and check and confirm that the pressure regulating system of the high-pressure air source is working properly; S30. Input high-pressure gas; The temperature and pressure of the high-pressure gas are adjusted to a starting state through a pressure regulating valve of the high-pressure gas source, and the high-pressure gas is injected into the high-pressure gas collecting chamber (6-1) through a high-pressure air inlet pipeline. The high-pressure gas drives the fan rotor (3-1) of the fan section (3) to rotate and maintain an idle state. The measurement signals of the upstream measurement section (1) and the downstream measurement section (4) are checked and confirmed to be normal, and the fan rotor (3-1) is confirmed to rotate normally; S40. Adjust the external environment; Adjust the external environment. For wind tunnel tests, start the high-speed wind tunnel and establish a high-speed flow field. For ground tests, use natural air intake and empty the test chamber. Adjust the temperature and pressure of the high-pressure gas to the pre-set target state. The fan rotor (3-1) continues to reach the idle state and maintains a stable speed. Obtain total pressure, static pressure and total temperature data, calculate the flow field parameters of the intake section of the upstream measurement section (1) and the exhaust section of the downstream measurement section (4), and then calculate the total pressure distortion of the flow field, the total pressure recovery coefficient, the fan pressure ratio, and the fan efficiency. S50. First adjustment of the adjustable nozzle section (5); By adjusting the sliding outer casing (5-1) of the adjustable nozzle section (5) through the servo actuator (5-3), the nozzle outlet area is changed, and the temperature and pressure of the high-pressure gas are adjusted accordingly to ensure that the fan rotor (3-1) reaches a stable speed; the total pressure, static pressure and total temperature data are obtained, and the flow field parameters of the inlet cross section of the upstream measuring section (1) and the exhaust cross section of the downstream measuring section (4) are calculated, and then the total pressure distortion of the flow field, the total pressure recovery coefficient, the fan pressure ratio and the fan efficiency are calculated; S60. Multiple adjustments to the adjustable nozzle section (5); Repeat S50 to obtain a corresponding curve between the pressure of the high-pressure gas and the stable rotational speed of the fan rotor (3-1) according to a pre-set nozzle outlet area sequence until the fan rotor (3-1) reaches a surge boundary; S70. Leave the surge boundary; When the fan rotor (3-1) shows signs of surge, the outer casing (5-1) is quickly moved back to the starting position, the nozzle outlet area is restored to the maximum, and the temperature and pressure of the high-pressure gas are gradually reduced until the fan rotor (3-1) reaches the idle state; S80. Turn off the multi-function turbine drive fan simulator; Slowly close the high-pressure air source, and the fan rotor (3-1) stops naturally. Check and confirm that the measurement signals of the upstream measurement section (1) and the downstream measurement section (4) are normal. Turn off the measurement system, check and confirm that the structure of the fan simulation device of the multifunctional turbine-driven fan simulator is normal, and end the test.

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