Aero-engine dynamic stress test lead dissociation force evaluation test device and method

Abstract

The invention relates to an aero-engine dynamic stress test lead dissociation force evaluation test device and method. The device comprises a tension simulation control mechanism, a lead holding mechanism, a tension sensor, a data acquisition instrument and a computer. The tension simulation control mechanism is connected with one end of the dynamic stress test lead, and the other end of the dynamic stress test lead is connected with the lead holding mechanism; and the tension sensor is arranged on the dynamic stress test lead and is electrically connected with the computer through the data acquisition instrument. According to the invention, the tensile force loading condition of the dynamic stress test lead under the actual assembly and test working conditions can be simulated, the dissociation force can be measured and evaluated, the fixing mode of the dynamic stress test lead can be optimized, and a reliable lead fixing scheme is provided for the dynamic stress test of an aero-engine; the test fault caused by the lead fixing problem in the dynamic stress test process is reduced, the dynamic stress test precision is improved, the effective survival period of the dynamic stress test strain gauge is delayed, and the dynamic stress test cost of the aero-engine is saved.

Description

Technical Field

[0001] The invention belongs to the technical field of mechanical testing, and in particular relates to a test device and method for evaluating the pull-out force of a lead wire in a dynamic stress test of an aero-engine. Background Art

[0002] As a high-precision, ultra-complex rotating mechanical system, many core components of aircraft engines are constantly subjected to large loads from multiple operating conditions, such as aerodynamics, temperature, and centrifugal force, during the operation of the engine. Considering the engine's high thrust, ultra-high performance, and low fuel consumption, the thin-body structure of core components such as engine disks, blades, and casings has higher margin requirements for strength reliability. Therefore, the dynamic stress performance of core components such as disks, blades, and casings during engine operation has always been the focus of attention during engine design tests and production finalization.

[0003] At present, dynamic stress testing basically relies on strain gauges to test and feedback the dynamic stress level of core components. However, since many core components are located inside the engine duct, the testing of such core components requires transmitting the internal test signal to the outside of the engine through leads for data collection and judgment.

[0004] Therefore, the connection reliability of the dynamic stress test lead directly determines the accuracy of the test results and the effective life cycle of the test strain gauge. If there is adverse pulling caused by human factors during the test assembly process or the engine is subjected to centrifugal force load during operation, the dynamic stress test lead will not be able to avoid the risk of external pulling force impacting its connection reliability, and will also have an adverse effect on the dynamic stress test of core components. Summary of the invention

[0005] In view of the problems existing in the prior art, the present invention provides a test device and method for evaluating the withdrawal force of a dynamic stress test lead of an aircraft engine, which can simulate the tensile loading conditions of a dynamic stress test lead under actual assembly and testing conditions, and can measure and evaluate the withdrawal force of the dynamic stress test lead under the simulated tensile loading conditions, and can be used to optimize the holding method of the dynamic stress test lead, thereby providing a reliable lead holding solution for the dynamic stress test of the aircraft engine, thereby reducing test failures caused by lead holding problems during the dynamic stress test, further improving the accuracy of the dynamic stress test, delaying the effective life cycle of the dynamic stress test strain gauge, and effectively saving the cost of the dynamic stress test of the aircraft engine.

[0006] In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: an aircraft engine dynamic stress test lead extraction force evaluation test device, including a tension simulation control mechanism, a lead holding mechanism, a tension sensor, a data acquisition instrument and a computer; the tension simulation control mechanism is connected to one end of the dynamic stress test lead, and the other end of the dynamic stress test lead is connected to the lead holding mechanism; the tension sensor is installed on the dynamic stress test lead, the signal output end of the tension sensor is electrically connected to the signal input end of the data acquisition instrument, and the signal output end of the data acquisition instrument is electrically connected to the computer.

[0007] The tension simulation control mechanism comprises a motor and a pulling disk, the pulling disk is fixedly mounted on the power output shaft of the motor, and one end of the dynamic stress test lead is fixedly connected to the pulling disk.

[0008] The lead holding mechanism includes a base plate, a holding pressure plate, an electrode hole, an electrode head, a battery panel and an electric shock button; the holding pressure plate is buckled on the base plate, and the other end of the dynamic stress test lead is clamped between the holding pressure plate and the base plate; the electrode holes are distributed on the upper surface of the base plate; the electrode heads are distributed on the lower surface of the holding pressure plate, and the electrode heads extend into the electrode holes; the battery panel is arranged on the upper surface of the holding pressure plate, and the electric shock button is arranged on the upper surface of the battery panel; the electrode head is connected to the positive electrode of the battery panel through a wire and an electric shock button in turn; the base plate is connected to the negative electrode of the battery panel through a wire; the electrode head and the electrode hole are spot-welded and fixedly matched by discharge.

[0009] A method for evaluating the pull-out force of a lead wire for a dynamic stress test of an aircraft engine, using the test device for evaluating the pull-out force of a lead wire for a dynamic stress test of an aircraft engine, comprises the following steps:

[0010] Step 1: Tension Calibration

[0011] ①. Fix one end of the dynamic stress test lead to the pulling disk, and temporarily fix the other end of the dynamic stress test lead with a clamp to make the dynamic stress test lead in a straight state. The tension sensor has been pre-installed on the stress test lead.

[0012] ②. Clear the initial rotation angle of the power output shaft of the motor, then control the power output shaft of the motor to output torque, and generate tension on the dynamic stress test lead through the pulling disk;

[0013] ③. The tension on the dynamic stress test lead is measured by the tension sensor, and the measured tension data is fed back to the computer through the data acquisition instrument;

[0014] ④. Establish a relationship curve between the torque of the motor power output shaft and the tension of the dynamic stress test lead in the computer, and the tension calibration is completed;

[0015] Step 2: Lead retention

[0016] ① Disconnect the dynamic stress test lead from the temporary fixing fixture, and then insert the dynamic stress test lead into the space between the base plate and the holding plate of the lead holding mechanism;

[0017] ②. Manually press the electric shock button to trigger the discharge between the electrode head and the electrode hole, and then spot weld the holding plate to the base plate, so that the dynamic stress test lead is clamped between the base plate and the holding plate, and the lead holding is completed;

[0018] Step 3: Pull-out force assessment

[0019] ①. Start the motor and control the torque of the motor power output shaft to increase step by step. The pulling force generated by the pulling disk on the dynamic stress test lead also increases step by step.

[0020] ②. The tension sensor is used to measure the tension of the dynamic stress test lead in real time, and the real-time measured tension data is fed back to the computer through the data acquisition instrument;

[0021] ③. Compare the real-time measured tension data with the tension upper limit value set in the computer. When the real-time measured tension data reaches the tension upper limit value, the dynamic stress test lead has not loosened from the lead holding mechanism, which means that the lead holding method meets the design requirements. Then continue to increase the tension until the dynamic stress test lead loosens from the lead holding mechanism. At the same time, turn off the motor and the withdrawal force evaluation is completed. If the real-time measured tension data loosens from the lead holding mechanism before reaching the tension upper limit value, it means that the lead holding method does not meet the design requirements. At the same time, turn off the motor and the withdrawal force evaluation is completed.

[0022] Beneficial effects of the present invention:

[0023] The aircraft engine dynamic stress test lead extraction force evaluation test device and method of the present invention can simulate the tensile loading conditions of the dynamic stress test lead under actual assembly and test conditions, can measure and evaluate the extraction force of the dynamic stress test lead under the simulated tensile loading conditions, and can be used to optimize the holding method of the dynamic stress test lead, thereby providing a reliable lead holding solution for the dynamic stress test of the aircraft engine, thereby reducing test failures caused by lead holding problems during the dynamic stress test, further improving the dynamic stress test accuracy, delaying the effective life cycle of the dynamic stress test strain gauge, and effectively saving the cost of the aircraft engine dynamic stress test. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a structural principle diagram of an aircraft engine dynamic stress test lead extraction force evaluation test device of the present invention;

[0025] Figure 2 It is a structural schematic diagram of the lead holding mechanism of the present invention;

[0026] Figure 3 It is a spot welding layout diagram when the lead holding method in the embodiment adopts the first solution;

[0027] Figure 4 It is a spot welding layout diagram when the lead holding method in the embodiment adopts the second solution;

[0028] In the figure, 1 is a tension simulation control mechanism, 11 is a motor, 12 is a pulling disk, 2 is a lead holding mechanism, 21 is a base plate, 22 is a holding pressure plate, 23 is an electrode hole, 24 is an electrode head, 25 is a battery plate, 26 is an electric shock button, 3 is a tension sensor, 4 is a data acquisition instrument, 5 is a computer, and 6 is a dynamic stress test lead. DETAILED DESCRIPTION

[0029] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0030] like Figure 1 , 2 As shown, an aircraft engine dynamic stress test lead extraction force evaluation test device includes a tension simulation control mechanism 1, a lead holding mechanism 2, a tension sensor 3, a data acquisition instrument 4 and a computer 5; the tension simulation control mechanism 1 is connected to one end of the dynamic stress test lead 6, and the other end of the dynamic stress test lead 6 is connected to the lead holding mechanism 2; the tension sensor 3 is installed on the dynamic stress test lead 6, the signal output end of the tension sensor 3 is electrically connected to the signal input end of the data acquisition instrument 4, and the signal output end of the data acquisition instrument 4 is electrically connected to the computer 5.

[0031] The tension simulation control mechanism 1 includes a motor 11 and a pulling disk 12 . The pulling disk 12 is fixedly mounted on the power output shaft of the motor 11 . One end of the dynamic stress test lead 6 is fixedly connected to the pulling disk 12 .

[0032] The lead holding mechanism 2 includes a base plate 21, a holding pressure plate 22, an electrode hole 23, an electrode head 24, a battery panel 25 and an electric shock button 26; the holding pressure plate 22 is buckled on the base plate 21, and the other end of the dynamic stress test lead 6 is clamped between the holding pressure plate 22 and the base plate 21; the electrode holes 23 are distributed on the upper surface of the base plate 21; the electrode heads 24 are distributed on the lower surface of the holding pressure plate 22, and the electrode heads 24 extend into the electrode holes 23; the battery panel 25 is arranged on the upper surface of the holding pressure plate 22, and the electric shock button 26 is arranged on the upper surface of the battery panel 25; the electrode head 24 is connected to the positive electrode of the battery panel 25 through a wire and the electric shock button 26 in turn; the base plate 21 is connected to the negative electrode of the battery panel 25 through a wire; the electrode head 24 and the electrode hole 23 are spot welded and fixedly matched by discharge.

[0033] A method for evaluating the pull-out force of a lead wire for a dynamic stress test of an aircraft engine, using the test device for evaluating the pull-out force of a lead wire for a dynamic stress test of an aircraft engine, comprises the following steps:

[0034] Step 1: Tension Calibration

[0035] ①, one end of the dynamic stress test lead 6 is fixedly connected to the pulling disk 12, and the other end of the dynamic stress test lead 6 is temporarily fixed by a clamp, so that the dynamic stress test lead 6 is in a straight state, and the tension sensor 3 has been pre-installed on the stress test lead 6;

[0036] ②, the initial rotation angle of the power output shaft of the motor 11 is reset to zero, and then the power output shaft of the motor 11 is controlled to output torque, and a pulling force is generated on the dynamic stress test lead 6 through the pulling disk 12;

[0037] ③, the tension on the dynamic stress test lead 6 is measured by the tension sensor 3, and the measured tension data is fed back to the computer 5 via the data acquisition instrument 4;

[0038] ④. A relationship curve between the torque of the power output shaft of the motor 11 and the tension borne by the dynamic stress test lead 6 is established in the computer 5, and the tension calibration is completed;

[0039] Step 2: Lead retention

[0040] ①, disconnect the dynamic stress test lead 6 from the temporary fixing fixture, and then insert the dynamic stress test lead 6 into between the base plate 21 and the holding plate 22 of the lead holding mechanism 2;

[0041] ② Manually press the electric shock button 26 to trigger the discharge between the electrode head 24 and the electrode hole 23, and then spot weld the holding plate 22 to the base plate 21, so that the dynamic stress test lead 6 is clamped between the base plate 21 and the holding plate 22, and the lead holding is completed;

[0042] Step 3: Pull-out force assessment

[0043] ①, start the motor 11, control the torque of the power output shaft of the motor 11 to increase step by step, and the pulling force generated by the pulling disk 12 on the dynamic stress test lead 6 also increases step by step;

[0044] ②, the tension sensor 3 is used to measure the tension on the dynamic stress test lead 6 in real time, and the real-time measured tension data is fed back to the computer 5 via the data acquisition instrument 4;

[0045] ③. Compare the real-time measured tension data with the tension upper limit value set in the computer 5. When the real-time measured tension data reaches the tension upper limit value, the dynamic stress test lead 6 has not loosened from the lead holding mechanism 2, which means that the lead holding method meets the design requirements. Then continue to increase the tension until the dynamic stress test lead 6 is loosened from the lead holding mechanism 2, and turn off the motor 11 at the same time, and the withdrawal force evaluation is completed; if the real-time measured tension data is loosened from the lead holding mechanism 2 before reaching the tension upper limit value, it means that the lead holding method does not meet the design requirements, and turn off the motor 11 at the same time, and the withdrawal force evaluation is completed.

[0046] In this embodiment, the dynamic stress test lead wire 6 can be fixed after being gathered in a single bundle or multiple bundles. The initial tensile loading value is 5N, and the value of each level increase is 5N. The lead wire fixing method includes two schemes. The spot welding layout form of the first scheme is as follows: Figure 3 As shown, the spot welding layout of the second scheme is as follows Figure 4 shown.

[0047] Specifically, it can be seen from Table 1 that when the lead holding method adopts the spot welding layout of the first solution, the dynamic stress test lead 6 will not be loosened from the lead holding mechanism 2 until the withdrawal force reaches 34.6N, indicating that the spot welding layout under the lead holding method can withstand a greater withdrawal force, which is more advantageous for ensuring the reliability of the dynamic stress test of the aircraft engine. Therefore, the first solution can be used in practical applications. When the lead holding method adopts the spot welding layout of the second solution, the dynamic stress test lead 6 will be loosened from the lead holding mechanism 2 when the withdrawal force reaches 24.1N, indicating that the spot welding layout under the lead holding method cannot ensure the reliability of the dynamic stress test of the aircraft engine. Therefore, the second solution is not recommended for practical applications.

[0048] Table 1

[0049]

[0050] The solutions in the embodiments are not intended to limit the protection scope of the present invention. All equivalent implementations or changes that do not deviate from the present invention are included in the protection scope of the present invention.

Claims

1. An aircraft engine dynamic stress test lead extraction force evaluation test device, characterized in that: It includes a tension simulation control mechanism, a lead holding mechanism, a tension sensor, a data acquisition instrument and a computer; the tension simulation control mechanism is connected to one end of the dynamic stress test lead, and the other end of the dynamic stress test lead is connected to the lead holding mechanism; the tension sensor is installed on the dynamic stress test lead, the signal output end of the tension sensor is electrically connected to the signal input end of the data acquisition instrument, and the signal output end of the data acquisition instrument is electrically connected to the computer.

2. The aircraft engine dynamic stress test lead extraction force evaluation test device according to claim 1, characterized in that: The tension simulation control mechanism comprises a motor and a pulling disk, the pulling disk is fixedly mounted on the power output shaft of the motor, and one end of the dynamic stress test lead is fixedly connected to the pulling disk.

3. The lead extraction force evaluation test device for dynamic stress testing of an aircraft engine according to claim 1, characterized in that: The lead holding mechanism includes a base plate, a holding pressure plate, an electrode hole, an electrode head, a battery panel and an electric shock button; the holding pressure plate is buckled on the base plate, and the other end of the dynamic stress test lead is clamped between the holding pressure plate and the base plate; the electrode holes are distributed on the upper surface of the base plate; the electrode heads are distributed on the lower surface of the holding pressure plate, and the electrode heads extend into the electrode holes; the battery panel is arranged on the upper surface of the holding pressure plate, and the electric shock button is arranged on the upper surface of the battery panel; the electrode head is connected to the positive electrode of the battery panel through a wire and an electric shock button in turn; the base plate is connected to the negative electrode of the battery panel through a wire; the electrode head and the electrode hole are spot-welded and fixedly matched by discharge.

4. A method for evaluating the pull-out force of a lead wire for a dynamic stress test of an aircraft engine, using the test device for evaluating the pull-out force of a lead wire for a dynamic stress test of an aircraft engine as claimed in claim 1, characterized in that: The steps include: Step 1: Tension Calibration ①. Fix one end of the dynamic stress test lead to the pulling disk, and temporarily fix the other end of the dynamic stress test lead with a clamp to make the dynamic stress test lead in a straight state. The tension sensor has been pre-installed on the stress test lead. ②. Clear the initial rotation angle of the power output shaft of the motor, then control the power output shaft of the motor to output torque, and generate tension on the dynamic stress test lead through the pulling disk; ③. The tension on the dynamic stress test lead is measured by the tension sensor, and the measured tension data is fed back to the computer through the data acquisition instrument; ④. Establish a relationship curve between the torque of the motor power output shaft and the tension of the dynamic stress test lead in the computer, and the tension calibration is completed; Step 2: Lead retention ① Disconnect the dynamic stress test lead from the temporary fixing fixture, and then insert the dynamic stress test lead into the space between the base plate and the holding plate of the lead holding mechanism; ②. Manually press the electric shock button to trigger the discharge between the electrode head and the electrode hole, and then spot weld the holding plate to the base plate, so that the dynamic stress test lead is clamped between the base plate and the holding plate, and the lead holding is completed; Step 3: Pull-out force assessment ①. Start the motor and control the torque of the motor power output shaft to increase step by step. The pulling force generated by the pulling disk on the dynamic stress test lead also increases step by step. ②, The tension sensor is used to measure the tension of the dynamic stress test lead in real time, and the real-time measured tension data is fed back to the computer through the data acquisition instrument; ③. Compare the real-time measured tension data with the tension upper limit value set in the computer. When the real-time measured tension data reaches the tension upper limit value, the dynamic stress test lead has not loosened from the lead holding mechanism, which means that the lead holding method meets the design requirements. Then continue to increase the tension until the dynamic stress test lead loosens from the lead holding mechanism. At the same time, turn off the motor and the withdrawal force evaluation is completed. If the real-time measured tension data loosens from the lead holding mechanism before reaching the tension upper limit value, it means that the lead holding method does not meet the design requirements. At the same time, turn off the motor and the withdrawal force evaluation is completed.

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