CN107764558B - It is a kind of for simulate gear fanjet blade loss experimental provision and experimental method - Google Patents

Abstract

The invention discloses a kind of for simulating the experimental provision and experimental method of gear fanjet blade loss.Experimental provision of the invention mainly includes direct current generator, shaft coupling I, shaft coupling II, shaft coupling III, shaft coupling IV, torque rotary speed sensor I, torque rotary speed sensor II, disk, gear-rotor system, magnetic powder brake, the quality m for simulating fan propeller₁Mass block I, quality m₂Mass block II and workbench.The present invention, for simulating the experimental provision and its experimental method of gear fanjet blade loss, solves the problems, such as that amount of unbalance is lost and quantitatively applied to simulation gear fanjet blade using a kind of.

Description

An experimental device and experiment for simulating blade loss of a geared turbofan engine method

technical field

The invention relates to the technical field of aero-engine rotor dynamics and airworthiness compliance verification, in particular to an experimental device and an experimental method for simulating the loss of gear turbofan engine blades.

Background technique

Reducing fuel consumption and reducing pollution emissions are the main development directions of the next generation of civil aeroengines. The geared turbofan (Geared Turbofan Engine, GTF) engine has the advantages of low emission, low noise, low fuel consumption and low maintenance cost. Compared with the traditional twin-rotor turbofan engine, the gear-driven fan (GTF) engine has no fundamental change in the core engine, only a reduction box is added. In view of the technical performance characteristics and performance advantages of gear driven fan (GTF) engines, gear driven fan (GTF) engines have attractive market application development prospects in regional aircraft and single-aisle mainline aircraft.

Blade loss is a typical severe load condition that an engine may encounter, and it refers to a part or the entire rotor blade being broken and flying out. Loss of blades may be caused by fatigue failure of blades or tongues and grooves, large-scale bird strikes or other foreign object impacts, etc., and will cause serious damage to the engine structure, and even cause damage to the aircraft. Based on airworthiness safety requirements, the aviation safety management agency has put forward clear requirements for blade loss. The Civil Aviation Administration of China requires that the high bypass ratio turbofan engine must pass the blade loss test to verify that the turbofan engine can guarantee the maximum flight time during the longest flight period (the maximum flight time for some models is 3 hours) when the fan blades are lost. The turbofan engines are in a safe state from causing dangerous failures so that the aircraft can return safely. Therefore, blade loss is an important problem that must be solved in the engine development process. The early research was mainly through rigorous test verification, but it cost a lot of money. In recent years, the research trend is to avoid or reduce the test of the whole machine in the early stage of design, and verify the dynamic response law and characteristics of the structure through analysis and simulation as much as possible.

In the prior art, someone has invented a sub-scale simulated aero-engine rotation test device and test method. It is equipped with simulated case, simulated support plate, simulated rotor shaft, simulated blisk, simulated drum, front, middle and rear three fulcrum bearings and simulated front and rear mounting joints; the test device is driven by a motor through a set of broken shaft protection device to simulate The casing parts are connected by mounting side bolts, the simulated support plate is connected with the simulated casing by welding, the simulated blade is connected with the shaft through bolts and the mounting plate, the simulated drum and the simulated support plate are connected by bolts, and the simulated front mounting section is connected by bolts. It is connected to the rigid mounting base by bolts and suspenders, and the rear mounting section is connected to the rigid mounting base by bolts and hinges after simulation.

However, compared with the traditional twin-rotor turbofan engine, the GTF engine adds a gearbox, and the transmission structure has changed. Due to the existence of the gear system, the excitation source of the GTF engine system is no longer a single unbalanced quantity. As an elastic mechanical system with parametric excitation and nonlinear coexistence, the dynamic response of the gear system is not only affected by its own structural parameters and geometric parameters, but also affected by various excitations. However, the existing experimental device cannot quantitatively apply the unbalance, nor can it simulate the vibration characteristics of the GTF engine after the blade is lost in the windmill state.

Contents of the invention

The purpose of the present invention is to solve the problem of simulating the loss of geared turbofan engine blades and quantitatively applying unbalanced quantities. The present invention proposes an experimental device and an experimental method for simulating the loss of geared turbofan engine blades. This device is simple in structure and easy to disassemble It is easy to replace, can meet the requirements of different unbalanced quantities and different working conditions, and can verify the correctness of theoretical methods, analytical models and numerical results. It can meet the actual needs of enterprises and fill the gaps in related technologies.

The technical scheme adopted for realizing the object of the present invention is such that a kind of experimental device for simulating the loss of gear turbofan engine blade mainly includes DC motor, coupling I, coupling II, coupling III, coupling Shaft device IV, torque speed sensor I, torque speed sensor II, disc for simulating fan rotor, gear rotor system, magnetic powder brake, mass block _I with mass m1, mass block _II with mass m2 and workbench .

The DC motor, the torque speed sensor I, the gear rotor system, the torque speed sensor II and the magnetic powder brake are sequentially installed on the workbench.

The DC motor provides speed and power.

The rotating shaft of the DC motor and the rotating shaft of the torque speed sensor 1 are connected together through the coupling 1.

When the experimental equipment for simulating the loss of geared turbofan engine blades simulates the normal working state, the rotating shaft of the torque speed sensor I and the input shaft of the gear rotor system are connected together through the coupling II.

When the windmill state is simulated by the experimental equipment for simulating the loss of gear turbofan engine blades, the rotating shaft of the torque speed sensor I and the output shaft of the gear rotor system are connected together through the coupling II.

The gear rotor system includes the input shaft, bearing housing I, bearing housing II, box, the output shaft, eddy current displacement sensor I, eddy current displacement sensor II, acceleration sensor I, acceleration sensor II, acceleration sensor III , acceleration sensor IV, acceleration sensor V, acceleration sensor VI, eddy current displacement sensor III and eddy current displacement sensor IV.

The bearing seat I, the bearing seat II and the box are installed on the workbench in sequence.

The acceleration sensor I and the acceleration sensor II are glued on the bearing seat I. The acceleration sensor I and the acceleration sensor II are distributed in 900°.

The acceleration sensor III and the acceleration sensor IV are glued on the bearing block II. The acceleration sensors III and the acceleration sensors IV are distributed at 900°.

The acceleration sensor V and the acceleration sensor VI are glued on the box body. The acceleration sensors V and the acceleration sensors VI are distributed at 900 degrees.

The output shaft is supported on the workbench through the bearing seat I and the bearing seat II.

Further, the gear rotor system also includes a planetary shaft, a planetary carrier, a sun gear, a herringbone planetary gear, a herringbone ring gear and a fan sleeve.

There are three planet shafts. The planetary shaft is fixed on the box body. One end of the planetary shaft is threaded. The threaded end of the planetary shaft is mounted on the planetary carrier through a planetary shaft fixing nut, and has a hollow cantilever structure. The planet shafts are evenly distributed around the sun gear.

The 3 said herringbone planetary gears are installed on the corresponding planetary shafts. The herringbone planetary gear meshes with the sun gear to form an external meshing gear transmission. The herringbone planetary gear meshes with the herringbone ring gear to form an internal meshing transmission.

The herringbone ring gear is connected with the fan sleeve (911) through splines.

When the windmill state is simulated by the experimental equipment for simulating the blade loss of the geared turbofan engine, the input shaft of the geared rotor system and the rotating shaft of the torque speed sensor II are connected together through the coupling III.

The eddy current displacement sensor I and the eddy current displacement sensor II are mounted on a magnetic base to align with the input shaft. The eddy current displacement sensor I and the eddy current displacement sensor II are distributed at 90°.

When the experimental equipment for simulating the loss of gear turbofan engine blades simulates the normal working state, the output shaft of the gear rotor system and the rotating shaft of the torque speed sensor II are connected together through the coupling III.

The eddy current displacement sensor III and the eddy current displacement sensor IV are mounted on a magnetic base to align with the output shaft. The eddy current displacement sensors III and the eddy current displacement sensors IV are distributed at 90°.

The rotating shaft of the torque speed sensor II and the rotating shaft of the magnetic powder brake are connected together through the shaft coupling IV.

The magnetic powder brake is used to simulate the load.

There is a hole I matching the input shaft in the middle of the disk of the simulated fan rotor. The disk of the simulated fan rotor is installed on the input shaft through the hole I.

The disc of the simulated fan rotor has a hole II where the mass I can be placed.

When the experimental equipment for simulating the loss of gear turbofan engine blades simulates the state of a windmill, the mass I is embedded in the hole II.

The product of the mass m ₁ of the mass I and the distance from the center of the hole II to the center of the disc of the simulated fan rotor matches the unbalance to be simulated.

Alternatively, when the windmill state is simulated by the experimental equipment for simulating the loss of the blades of the geared turbofan engine, the hole II is drilled on the disk of the simulated fan rotor. At this time, the disc of the simulated fan rotor cuts off the mass II by punching holes.

The product of the mass m ₂ of the mass II and the distance from the center of the hole II to the center of the disc of the simulated fan rotor matches the unbalance to be simulated.

Further, the hole I and the hole II are holes for simulating centrifugal force under high-speed rotation.

Preferably, the hole I and the hole II use thread patterns.

Further, the experimental device also includes a control system, a data collector, an eddy current signal conditioner, an SP-DSA analysis system or a computer.

The control system controls the rotational speed of the DC motor.

The control system controls the load of the magnetic powder brake.

The eddy current signal conditioner amplifies the charges of the signals in the eddy current displacement sensor I, the eddy current displacement sensor II, the eddy current displacement sensor III and the eddy current displacement sensor IV.

Further, the eddy current signal conditioner is a charge amplifier.

The data collector collects the acceleration sensor I, the acceleration sensor II, the acceleration sensor III, the acceleration sensor IV, the acceleration sensor V, the acceleration sensor VI and the eddy current signal conditioner The data.

All the data collected by the data collector are transmitted to the SP-DSA analysis system or the computer.

The SP-DSA analysis system or the computer analyzes all the received data.

The experimental method for simulating the normal working state of a geared turbofan engine by using an experimental device mainly includes the following steps:

1) Prepare the experimental equipment, mainly including the experimental device for simulating the loss of the gear turbofan engine blade.

2) Debugging the entire experimental equipment mainly includes observing whether the gear-rotor system can rotate normally, and ensuring that the torque speed sensor I and the torque speed sensor II have speed signal output.

3) Check the test system, the lubricating oil system and the control system according to the regulations, and confirm that the test system, the lubricating oil system and the control system can work normally.

4) Slowly increase the speed of the gear-rotor system to a certain safe speed or rated operating speed to provide reference data for formal experiments.

5) On the premise that the vibration limit value is not exceeded, the speed of the gear-rotor system is increased to the speed required by the experiment.

6) Observe different measuring points under load conditions.

7) Record the unbalanced vibration response of the gear-rotor system at different measuring points.

8) Shut down according to the operating procedures of the experimental equipment.

Adopt described experimental device to simulate the experimental method of gear turbofan engine windmill state, mainly comprise the following steps:

1) Prepare the experimental equipment, mainly including the experimental device for simulating the loss of the gear turbofan engine blade.

2) In the experimental device for simulating the loss of a geared turbofan engine blade, the mass I is placed at the hole I of the disk of the simulated fan rotor.

3) Debugging the entire experimental equipment mainly includes observing whether the gear-rotor system can rotate normally, and ensuring that the torque speed sensor I and the torque speed sensor II have speed signal output.

4) Check the test system, the lubricating oil system and the control system according to the regulations, and confirm that the test system, the lubricating oil system and the control system can work normally.

5) Slowly increase the speed of the gear-rotor system to a certain safe speed or rated operating speed to provide reference data for formal experiments.

6) On the premise that the vibration limit value is not exceeded, the speed of the gear-rotor system is increased to the speed required by the experiment.

7) Observe different measuring points under load conditions.

8) Record the unbalanced vibration response of the gear-rotor system at different measuring points.

9) Shut down according to the operating procedures of the experimental equipment.

Adopt described experimental device to simulate the experimental method of gear turbofan engine windmill state, mainly comprise the following steps:

1) Prepare the experimental equipment, mainly including the experimental device for simulating the loss of the gear turbofan engine blade.

2) In the experimental device for simulating the blade loss of the geared turbofan engine, the hole II is drilled on the disk of the simulated fan rotor. At this time, the disk of the simulated fan rotor is shaved off the mass II.

3) Debugging the entire experimental equipment mainly includes observing whether the gear-rotor system can rotate normally, and ensuring that the torque speed sensor I and the torque speed sensor II have speed signal output.

4) Check the test system, the lubricating oil system and the control system according to the regulations, and confirm that the test system, the lubricating oil system and the control system can work normally.

5) Slowly increase the speed of the gear-rotor system to a certain safe speed or rated operating speed to provide reference data for formal experiments.

6) On the premise that the vibration limit value is not exceeded, the speed of the gear-rotor system is increased to the speed required by the experiment.

7) Observe different measuring points under load conditions.

8) Record the unbalanced vibration response of the gear-rotor system at different measuring points.

9) Shut down according to the operating procedures of the experimental equipment.

The technical effect of the present invention is unquestionable. The experimental device can satisfy the experimental verification under different unbalanced quantities and different working conditions by quantitatively applying unbalanced quantities, thereby simulating the loss of gear turbofan engine blades. In this experimental device, a hole is drilled at the proper position of the disc for simulating rotor unbalance, and a mass block that can simulate unbalance is added by connecting, which is convenient for replacement and disassembly.

Therefore, the device can be used to obtain the dynamic response characteristics of the system under different unbalanced quantities and different working conditions, and to study the influence of unbalanced quantities, different input speeds and loads on the vibration characteristics of the system, and to verify the correctness of the theoretical method.

Description of drawings

Figure 1 is a schematic diagram of the experimental bench layout.

Figure 2 is a schematic diagram of the experimental measurement arrangement.

Figure 3 is a partial enlarged view of the connection of the gear-rotor system box.

Figure 4 is a schematic diagram of the connection of the experimental system.

Fig. 5 is a disk of a simulated fan rotor with mass blocks added.

Fig. 6 is the disk of the simulated fan rotor with the masses removed.

In the figure: direct current 1, coupling I2, coupling II3, coupling III4, coupling IV5, torque speed sensor I6, torque speed sensor II7, disc 8 for simulating fan rotor, gear rotor system 9 , Magnetic powder brake ₁₀ , mass block I11 with mass m1, mass block _II12 with mass m2, workbench 13, input shaft 905, bearing seat I902, bearing seat II903, box body 904, planetary shaft 906, planet carrier 907 , sun gear 908, herringbone planetary gear 909, herringbone ring gear 910, fan sleeve 911, output shaft 901, eddy current displacement sensor I9011, eddy current displacement sensor II9012, acceleration sensor I9021, acceleration sensor II9022, acceleration sensor III9031 , Acceleration sensor IV9032, acceleration sensor V9041, acceleration sensor VI9042, eddy current displacement sensor III9051 and eddy current displacement sensor IV9052, control system, data collector, eddy current signal conditioner, SP-DSA analysis system or computer.

Detailed ways

The present invention will be further described below in conjunction with the examples, but it should not be understood that the scope of the subject of the present invention is limited to the following examples. Without departing from the above-mentioned technical ideas of the present invention, various replacements and changes made according to common technical knowledge and conventional means in this field shall be included in the protection scope of the present invention.

Example 1:

An experimental device for simulating the loss of a geared turbofan engine blade, see Figure 1, the experimental device for simulating the loss of a geared turbofan engine blade mainly includes a DC motor 1, a coupling I2, a coupling II3, a coupling III4, Coupling IV5, torque speed sensor I6, torque speed sensor II7, disc 8 for simulating fan rotor, gear rotor system 9, magnetic powder brake 10, mass block I11 with mass m ₁ , mass block with mass m ₂ II12 and bench 13.

The DC motor 1 , the torque speed sensor I6 , the gear rotor system 9 , the torque speed sensor II7 and the magnetic powder brake 10 are installed on the workbench 13 in sequence.

The DC motor 1 provides rotational speed and power.

The rotating shaft of the DC motor 1 and the rotating shaft of the torque speed sensor I6 are connected together through the coupling I2.

When the experimental equipment for simulating loss of geared turbofan engine blades simulates a normal working state, the rotating shaft of the torque speed sensor I6 and the input shaft 905 of the geared rotor system 9 are connected together through the coupling II3.

When the windmill state is simulated by the experimental equipment for simulating the blade loss of the geared turbofan engine, the rotating shaft of the torque speed sensor I6 and the output shaft 901 of the geared rotor system 9 are connected together through the coupling II3.

When the experimental equipment for simulating the loss of geared turbofan engine blades simulates normal working conditions, the output shaft 901 of the geared rotor system 9 and the rotating shaft of the torque speed sensor II7 are connected together through the coupling III4.

When the windmill state is simulated by the experimental equipment for simulating the blade loss of the geared turbofan engine, the input shaft 905 of the geared rotor system 9 and the rotating shaft of the torque speed sensor II7 are connected together through the coupling III4.

The rotation shaft of the torque speed sensor II7 and the rotation shaft of the magnetic powder brake 10 are connected together through the shaft coupling IV5.

The magnetic powder brake 10 is used to simulate a load.

Example 2:

An experimental device for simulating the loss of gear turbofan engine blades, see Figure 2 and Figure 3, the gear rotor system 9 includes the output shaft 901, bearing housing I902, bearing housing II903, box body 904, the input Shaft 905, eddy current displacement sensor I9011, eddy current displacement sensor II9012, acceleration sensor I9021, acceleration sensor II9022, acceleration sensor III9031, acceleration sensor IV9032, acceleration sensor V9041, acceleration sensor VI9042, eddy current displacement sensor III9051 and eddy current displacement sensor IV9052 .

The bearing seat I902, the bearing seat II903 and the box body 904 are installed on the workbench 13 in sequence.

The bearing seat I902 and the bearing seat II903 are fixed on the box body 904 through the installation holes.

The acceleration sensor I9021 and the acceleration sensor II9022 are glued on the bearing seat I902. The acceleration sensor I9021 and the acceleration sensor II9022 are distributed at 90°.

The acceleration sensor III9031 and the acceleration sensor IV9032 are glued on the bearing block II903. The acceleration sensor III9031 and the acceleration sensor IV9032 are distributed at 90°.

The acceleration sensor V9041 and the acceleration sensor VI9042 are glued on the box body 904 . The acceleration sensor V9041 and the acceleration sensor VI9042 are distributed at 90°.

The output shaft 901 is supported on the workbench 13 through the bearing seat I902 and the bearing seat II903;

The eddy current displacement sensor I9011 and the eddy current displacement sensor II9012 are mounted on a magnetic base to align with the input shaft 905 . The eddy current displacement sensors I9011 and the eddy current displacement sensors II9012 are distributed at 90°.

The eddy current displacement sensor III9051 and the eddy current displacement sensor IV9052 are mounted on a magnetic base to align with the output shaft 901 . The eddy current displacement sensor III9051 and the eddy current displacement sensor IV9052 are distributed at 90°.

Further, the gear rotor system 9 also includes a planetary shaft 906 , a planetary carrier 907 , a sun gear 908 , a herringbone planetary gear 909 , a herringbone ring gear 910 and a fan sleeve 911 .

There are three planet shafts 906 in total. The planet shaft 906 is fixed on the box body 904 . One end of the planet shaft 906 is threaded. The threaded end of the planetary shaft 906 is mounted on the planetary carrier 907 through a planetary shaft fixing nut, and has a hollow cantilever structure. The planet shafts 906 are evenly distributed around the sun gear 908 .

The three said herringbone planetary gears 909 are installed on the corresponding planetary shafts 906 . The herringbone planetary gear 909 meshes with the sun gear 908 to form an external meshing gear transmission. The herringbone planetary gear 909 meshes with the herringbone ring gear 910 to form an internal meshing transmission.

The herringbone ring gear 910 is connected with the fan sleeve (911) through splines.

There is a hole I matching the output shaft 901 in the middle of the disc 8 of the simulated fan rotor. The disc 8 of the simulated fan rotor is installed on the output shaft 901 through the hole I.

Example 3:

An experimental device for simulating the loss of gear turbofan engine blades, see Figure 4, also includes a control system, data collector, eddy current signal conditioner, SP-DSA analysis system or computer.

The control system controls the rotation speed of the DC motor 1 .

The control system controls the load of the magnetic powder brake 10 .

The eddy current signal conditioner amplifies the charges of the signals in the eddy current displacement sensor I9011, the eddy current displacement sensor II9012, the eddy current displacement sensor III9051 and the eddy current displacement sensor IV9052.

Further, the eddy current signal conditioner is a charge amplifier.

The data collector collects the acceleration sensor I9021, the acceleration sensor II9022, the acceleration sensor III9031, the acceleration sensor IV9032, the acceleration sensor V9041, the acceleration sensor VI9042 and the eddy current signal conditioner The data.

All the data collected by the data collector are transmitted to the SP-DSA analysis system or the computer.

The SP-DSA analysis system or the computer analyzes all the received data.

Example 4:

An experimental device for simulating the loss of a geared turbofan engine blade, see FIG. 5 , the disc 8 of the simulated fan rotor has a hole II where the mass I11 can be placed. Easy to replace and remove

Further, the hole II is used to simulate centrifugal force under high-speed rotation.

Preferably, the hole II uses a thread pattern, and the mass I11 has a thread pattern matching the hole.

When the experimental equipment for simulating the loss of gear turbofan engine blades simulates the state of a windmill, the mass I11 is embedded in the hole II.

The product of the mass m ₁ of the mass I11 and the distance from the center of the hole II to the center of the disc 8 of the simulated fan rotor matches the unbalance to be simulated.

Further, the unbalance amount of the mass I11 is e=mr, m is the mass of the mass, and r is the distance from the mass to the center of the disc 8 of the simulated fan rotor. For different unbalanced quantities, when the position of the hole II has been determined, a threaded mass block corresponding to the simulated unbalanced quantity can be manufactured to simulate the state under different unbalanced quantities.

Example 5:

An experimental device for simulating the loss of a geared turbofan engine blade, see Figure 6, when the experimental equipment for simulating the loss of a geared turbofan engine blade is simulating a windmill state, a hole II is drilled on the disc 8 of the simulated fan rotor . At this time, the disc 8 of the simulated fan rotor cuts off the mass II12 by punching holes.

Further, the hole II is used to simulate centrifugal force under high-speed rotation.

Preferably, the hole II can use a thread pattern, and the mass block II12 has a thread pattern matching the hole.

The product of the mass m ₂ of the mass II12 and the distance from the center of the hole II to the center of the disc 8 of the simulated fan rotor matches the unbalance to be simulated.

According to the density of the material of the disk 8 of the simulated fan rotor, the corresponding volume of the mass II that should be removed under different balance quantities can be calculated, so as to drill holes II of different diameters to simulate different windmill states the amount of imbalance.

Embodiment 6:

The experimental method for simulating the normal working state of a geared turbofan engine by using the experimental device mainly includes the following steps:

1) Prepare experimental equipment, mainly including experimental devices and test instruments for simulating the loss of gear turbofan engine blades.

2) Assemble the experimental device according to the structure of the experimental device for simulating the loss of gear turbofan engine blades in the normal working state.

3) Verify and calibrate the test instruments to ensure that the test instruments are placed reasonably, connected correctly, and free from interference.

4) Check the experimental equipment to ensure that the instruments and meters are within the verification period, the control system parameters are correct, the knobs are in the correct position, and test whether the circuit is correct and the communication is normal. Check the vibration test system again to ensure that the gap voltage of the eddy current displacement sensor is within a reasonable range and the displacement sensor is working in the linear region, and gently tap the support on which the vibration acceleration sensor has been installed to ensure that the test instrument responds normally.

5) Debugging the entire experimental equipment mainly includes: observing whether the gear rotor system 9 can rotate normally, and ensuring that the torque speed sensor I6 and the torque speed sensor II7 have speed signal output.

6) Check the test system, the lubricating oil system and the control system according to the regulations, and confirm that the test system, the lubricating oil system and the control system can work normally.

7) Adjust the control parameters according to the experimental requirements.

8) Slowly increase the speed of the gear-rotor system 9 to a certain safe speed or rated operating speed, so as to provide reference data for formal experiments.

9) On the premise that the vibration limit value is not exceeded, the speed of the gear-rotor system 9 is increased to the speed required by the experiment.

10) Adjust the speed and load values through the control system to simulate different working conditions.

11) Observe different measuring points under the same load state.

12) Record the unbalanced vibration response of the gear-rotor system 9 at different measuring points.

13) Repeat step 12 and step 13 until multiple measuring points are observed under each load state.

14) Shut down according to the operating procedures of the experimental equipment.

Embodiment 7:

Adopt described experimental device to simulate the experimental method of gear turbofan engine windmill state, mainly comprise the following steps:

1) Prepare experimental equipment, mainly including experimental devices and test instruments for simulating the loss of gear turbofan engine blades.

2) Assemble the experimental device according to the structure of the windmill state of the experimental device for simulating the loss of gear turbofan engine blades.

3) Verify and calibrate the test instruments to ensure that the test instruments are placed reasonably, connected correctly, and free from interference.

4) Check the experimental equipment to ensure that the instruments and meters are within the verification period, the control system parameters are correct, the knobs are in the correct position, and test whether the circuit is correct and the communication is normal. Check the vibration test system again to ensure that the gap voltage of the eddy current displacement sensor is within a reasonable range and the displacement sensor is working in the linear region, and gently tap the support on which the vibration acceleration sensor has been installed to ensure that the test instrument responds normally.

5) In the experimental device for simulating the loss of a geared turbofan engine blade, the mass I11 is placed at the hole II of the disc 8 of the simulated fan rotor.

6) Debugging the entire experimental equipment mainly includes: observing whether the gear-rotor system 9 can rotate normally, and ensuring that the torque speed sensor I6 and the torque speed sensor II7 have speed signal output.

7) Check the test system, lubricating oil system and the control system according to the regulations, and confirm that the test system, the lubricating oil system and the control system can work normally.

8) Adjust the control parameters according to the experimental requirements.

9) Slowly increase the speed of the gear-rotor system 9 to a certain safe speed or rated operating speed to provide reference data for formal experiments.

10) On the premise that the vibration limit value is not exceeded, the speed of the gear-rotor system 9 is increased to the speed required by the experiment.

11) Adjust the speed and load values through the control system to simulate different working conditions.

12) Observe different measuring points under the same load state.

13) Record the unbalanced vibration response of the gear-rotor system 9 at different measuring points.

14) Repeat step 12 and step 13 until multiple measuring points are observed under each load state.

15) Shut down according to the operating procedures of the experimental equipment.

Embodiment 8:

Adopt described experimental device to simulate the experimental method of gear turbofan engine windmill state, mainly comprise the following steps:

Adopt described experimental device to simulate the experiment of geared turbofan engine windmill state, mainly comprise the following steps:

1) Prepare experimental equipment, mainly including experimental devices and test instruments for simulating the loss of gear turbofan engine blades.

2) Assemble the experimental device according to the structure of the windmill state of the experimental device for simulating the loss of gear turbofan engine blades.

3) Verify and calibrate the test instruments to ensure that the test instruments are placed reasonably, connected correctly, and free from interference.

4) Check the experimental equipment to ensure that the instruments and meters are within the verification period, the control system parameters are correct, the knobs are in the correct position, and test whether the circuit is correct and the communication is normal. Check the vibration test system again to ensure that the gap voltage of the eddy current displacement sensor is within a reasonable range and the displacement sensor is working in the linear region, and gently tap the support on which the vibration acceleration sensor has been installed to ensure that the test instrument responds normally.

5) In the experimental device for simulating the loss of a geared turbofan engine blade, the hole II is drilled on the disk 8 of the simulated fan rotor. At this time, the disc 8 of the simulated fan rotor is shaved off the mass II12.

6) Debugging the entire experimental equipment mainly includes: observing whether the gear-rotor system 9 can rotate normally, and ensuring that the torque speed sensor I6 and the torque speed sensor II7 have speed signal output.

7) Check the test system, lubricating oil system and the control system according to the regulations, and confirm that the test system, the lubricating oil system and the control system can work normally.

8) Adjust the control parameters according to the experimental requirements.

9) Slowly increase the speed of the gear-rotor system 9 to a certain safe speed or rated operating speed to provide reference data for formal experiments.

10) On the premise that the vibration limit value is not exceeded, the speed of the gear-rotor system 9 is increased to the speed required by the experiment.

11) Adjust the speed and load values through the control system to simulate different working conditions.

12) Observe different measuring points under the same load state.

13) Record the unbalanced vibration response of the gear-rotor system 9 at different measuring points.

14) Repeat step 12 and step 13 until multiple measuring points are observed under each load state.

15) Shut down according to the operating procedures of the experimental equipment.

Claims (8)

1. a kind of for simulating the experimental provision of gear fanjet blade loss, it is characterised in that: mainly include direct current Machine (1), shaft coupling I (2), shaft coupling II (3), shaft coupling III (4), shaft coupling IV (5), torque rotary speed sensor I (6), torque Speed probe II (7), disk (8), gear-rotor system (9), the magnetic powder brake (10), quality m for simulating fan propeller₁ Mass block I (11), quality m₂Mass block II (12) and workbench (13)；

The direct current generator (1), torque rotary speed sensor I (6), the gear-rotor system (9), the torque rotary speed sensor II (7) and the magnetic powder brake (10) are sequentially arranged on the workbench (13)；

The direct current generator (1) provides revolving speed and power；

The shaft of the direct current generator (1) and the shaft of the torque rotary speed sensor I (6) are connected by the shaft coupling I (2) Together；

When the experimental provision that the simulation gear fanjet blade is lost simulates normal operating conditions, the torque rotary speed The shaft of sensor I (6) and the input shaft (905) of the gear-rotor system (9) are connected to one by the shaft coupling II (3) It rises；

When simulating the experimental provision simulation windmill condition that gear fanjet blade is lost, the torque rotary speed sensor I (6) output shaft (901) of shaft and the gear-rotor system (9) is linked together by the shaft coupling II (3)；

The gear-rotor system (9) includes the output shaft (901), bearing block I (902), bearing block II (903), cabinet (904), the input shaft (905), eddy current displacement sensor I (9011), eddy current displacement sensor II (9012), acceleration Sensor I (9021), acceleration transducer II (9022), acceleration transducer III (9031), acceleration transducer IV (9032), acceleration transducer V (9041), acceleration transducer VI (9042), eddy current displacement sensor III (9051) and electricity Eddy displacement sensor IV (9052)；

The bearing block I (902), the bearing block II (903) and the cabinet (904) are sequentially arranged at the workbench (13) On；

The acceleration transducer I (9021) and the acceleration transducer II (9022) are with being adhesive in the bearing block I (902) On；The acceleration transducer I (9021) and the acceleration transducer II (9022) are in 90 ° of distributions；

The acceleration transducer III (9031) and the acceleration transducer IV (9032) are with being adhesive in the bearing block II (903) on；The acceleration transducer III (9031) and the acceleration transducer IV (9032) are in 90 ° of distributions；

The acceleration transducer V (9041) and the acceleration transducer VI (9042) are with being adhesive on the cabinet (904)； The acceleration transducer V (9041) and the acceleration transducer VI (9042) are in 90 ° of distributions；

The output shaft (901) is supported on the workbench by the bearing block I (902) and the bearing block II (903) (13) on；

When simulating the experimental provision simulation windmill condition that gear fanjet blade is lost, the gear-rotor system (9) The input shaft (905) and the shaft of the torque rotary speed sensor II (7) be connected to one by the shaft coupling III (4) It rises；

The eddy current displacement sensor I (9011) and the eddy current displacement sensor II (9012) are set up pair with magnet base The quasi- output shaft (901)；The eddy current displacement sensor I (9011) and the eddy current displacement sensor II (9012) are in 90 ° of distributions；

When simulating the experimental provision simulation normal operating conditions that gear fanjet blade is lost, the gear-rotor system (9) shaft of output shaft (901) and the torque rotary speed sensor II (7) is connected to one by the shaft coupling III (4) It rises；

The eddy current displacement sensor III (9051) and the eddy current displacement sensor IV (9052) are set up with magnet base It is directed at the output shaft (901)；The eddy current displacement sensor III (9051) and the eddy current displacement sensor IV (9052) in 90 ° of distributions；

The shaft of the torque rotary speed sensor II (7) and the shaft of the magnetic powder brake (10) pass through the shaft coupling IV (5) it links together；

The magnetic powder brake (10) is used for fictitious load；

There is the hole I to match with the input shaft (905) among the disk (8) of the simulation fan propeller；The mould The disk (8) of quasi- fan propeller is mounted on the input shaft (905) by the hole I；

The disk (8) of the simulation fan propeller has the hole II that can place the mass block I (11)；

When simulating the experimental provision simulation windmill condition that gear fanjet blade is lost, mass block I (11) insertion The hole II；

The quality m of the mass block I (11)₁With the center of circle to the center of circle of the disk (8) for simulating fan propeller of the hole II The product of distance matches with institute's amount of unbalance to be simulated；

Alternatively, when simulating the experimental provision simulation windmill condition that gear fanjet blade is lost, in the simulation fan Drilling bore hole II on the disk (8) of rotor；At this point, the disk (8) of the simulation fan propeller prunes quality by way of punching Block II (12)；

The quality m of the mass block II (12)₂With the center of circle to the center of circle of the disk (8) for simulating fan propeller of the hole II The product of distance match with an institute amount of unbalance to be simulated.

2. according to claim 1 a kind of for simulating the experimental provision of gear fanjet blade loss, feature It is: further includes control system, data collector, current vortex signal conditioner, SP-DSA analysis system or computer；

The control system controls the revolving speed of the direct current generator (1)；

The control system controls the load of the magnetic powder brake (10)；

The current vortex signal conditioner is to the eddy current displacement sensor I (9011), the eddy current displacement sensor II (9012), in the eddy current displacement sensor III (9051) and the eddy current displacement sensor IV (9052) signal electricity Lotus amplifies；

The data collector acquire the acceleration transducer I (9021), the acceleration transducer II (9022), it is described plus Velocity sensor III (9031), the acceleration transducer IV (9032), the acceleration transducer V (9041), the acceleration Spend the data in sensor VI (9042) and the current vortex signal conditioner；

Collected all data are transmitted in the SP-DSA analysis system or the computer in the data collector；

The SP-DSA analysis system or the computer analyze all data received.

3. according to claim 2 a kind of for simulating the experimental provision of gear fanjet blade loss, feature Be: the current vortex signal conditioner is a kind of charge amplifier.

4. according to claim 1 a kind of for simulating the experimental provision of gear fanjet blade loss, feature Be: the hole I and hole II is thread pattern.

5. according to claim 1 a kind of for simulating the experimental provision of gear fanjet blade loss, feature Be: the gear-rotor system (9) further includes planet axis (906), planet carrier (907), sun gear (908), herringbone planet Gear (909) herringbone ring gear (910) and fan sleeve (911)；

The planet axis (906) shares three；The planet axis (906) is fixed on the cabinet (904)；The planet axis (906) one end has screw thread；The planet axis (906) has threaded one end and is mounted on the row by planet axis fixture nut It is in hollow cantilever design in carrier (907)；The planet axis (906) is evenly arranged on around the sun gear (908)；

3 herringbone planetary gears (909) are mounted on corresponding planet axis (906)；The herringbone planetary gear (909) with Sun gear (908) engagement, forms external gear pump transmission；The herringbone planetary gear (909) and the herringbone internal tooth Circle (910) is meshed, and forms Inside gear drive；

The herringbone ring gear (910) is connect by spline with the fan sleeve (911).

6. a kind of experiment side for simulating gear fanjet normal operating conditions using experimental provision described in claim 2 Method, which is characterized in that mainly comprise the steps that

1) preparing experiment device, main includes the experimental provision that simulation gear fanjet blade is lost；

2) entire experimental provision is debugged, specifically includes that whether the observation gear-rotor system (9) can normally rotate, ensure institute Stating torque rotary speed sensor I (6) and the torque rotary speed sensor II (7) has tach signal output；

3) test macro, oil system and the control system are checked by regulation, confirms the test macro, the oil system It can be worked normally with the control system；

4) gear-rotor system (9) revolving speed is slowly improved to a certain safe speed of rotation or nominal operation revolving speed, is formal real Offer reference data is provided；

5) under the premise of being no more than vibration limits value, the gear-rotor system (9) revolving speed is improved to the revolving speed of requirement of experiment；

6) different measuring points of observation in the loaded state；

7) it is recorded at different measuring points, the unbalance vibration response of the gear-rotor system (9)；

8) it is shut down by experimental provision operating instruction.

7. a kind of experimental method that gear fanjet windmill condition is simulated using experimental provision described in claim 2, It is characterized in that, mainly comprises the steps that

1) preparing experiment device, main includes the experimental provision that simulation gear fanjet blade is lost；

2) in the experimental provision that simulation gear fanjet blade is lost, the mass block I (11) is placed on the simulation At the hole I of the disk (8) of fan propeller；

3) entire experimental provision is debugged, specifically includes that whether the observation gear-rotor system (9) can normally rotate, ensure institute Stating torque rotary speed sensor I (6) and the torque rotary speed sensor II (7) has tach signal output；

4) test macro, oil system and the control system are checked by regulation, confirms the test macro, the oil system It can be worked normally with the control system；

5) gear-rotor system (9) revolving speed is slowly improved to a certain safe speed of rotation or nominal operation revolving speed, is formal real Offer reference data is provided；

6) under the premise of being no more than vibration limits value, the gear-rotor system (9) revolving speed is improved to the revolving speed of requirement of experiment；

7) different measuring points of observation in the loaded state；

8) it is recorded at different measuring points, the unbalance vibration response of the gear-rotor system (9)；

9) it is shut down by experimental provision operating instruction.

8. a kind of experimental method that gear fanjet windmill condition is simulated using experimental provision described in claim 2, It is characterized in that, mainly comprises the steps that

1) preparing experiment device, main includes the experimental provision that simulation gear fanjet blade is lost；

2) it in the experimental provision that simulation gear fanjet blade is lost, is bored on the disk (8) of the simulation fan propeller The hole II out；At this point, the disk (8) of the simulation fan propeller is shaved mass block II (12)；

3) debug entire experimental provision, it is main include observe the gear-rotor system (9) whether can normally rotate, ensure it is described Torque rotary speed sensor I (6) and the torque rotary speed sensor II (7) have tach signal output；

4) test macro, oil system and the control system are checked by regulation, confirms the test macro, the oil system It can be worked normally with the control system；

5) gear-rotor system (9) revolving speed is slowly improved to a certain safe speed of rotation or nominal operation revolving speed, is formal real Offer reference data is provided；

6) under the premise of being no more than vibration limits value, the revolving speed of the gear-rotor system (9) is improved to requirement of experiment and is turned Speed；

7) different measuring points of observation in the loaded state；

8) it is recorded at different measuring points, the unbalance vibration response of the gear-rotor system (9)；

9) it is shut down by experimental provision operating instruction.