Field installation performance testing method and device for aviation pipeline connection clamps

Abstract

The invention provides a method and a device for testing the field installation performance of a clamp for connecting an aviation pipeline. The method comprises: S1, assembling a clamp assembly; S2, detecting the installation torque of the clamp assembly; S3, detecting the installation error of the clamp assembly; S4, detecting the stress of the clamp assembly; obtaining a curve of the relationship between the leakage of the clamp assembly and the installation torque and the installation deviation and a relationship between the installation torque and the stress according to the test data, and obtaining the installation torque, installation deviation and stress data; the testing device comprises a clamp assembly, a transmission conduit, a fixing assembly, a torque wrench and a strain gauge, and the clamp assembly, the transmission conduit and the fixing assembly are used in combination to simultaneously complete the test of the installation torque, installation error and stress distribution of the clamp assembly, reasonably guide the field installation application of the clamp, provide data support for the iterative optimization design of the clamp, solve the problem of lack of installation adaptability-related data of the clamp when the clamp is currently used in the field, and can be widely used in the field of aerospace.

Description

Technical Field

[0001] The invention relates to the field of clamp performance detection, and in particular to an outfield installation performance testing method and a device for an aviation pipeline connection clamp. Background Art

[0002] Aviation pipeline connection clamps are mainly used in the environmental control system of aircraft. They are the most widely used aviation gas pipeline connection form at present. They play a very important role in the fixed connection, gas transmission and sealing of the environmental control system's conduit. The main principle of the clamp assembly to achieve pipeline connection and sealing is to apply a specified tightening torque to the clamp, so that the concave and convex joints on both sides are tightened axially after being stressed, and squeeze the sealing ring, thereby achieving the connection and sealing of the conduits at both ends. During the application process, if the clamp fails, it will not only lose the thrust of the engine, but may even cause the environmental control system to fail, endangering other systems and accessories, and leading to catastrophic consequences.

[0003] At present, in the actual field application of the clamp, there is a lack of relevant data support for the installation adaptability of the clamp, including relevant data and rules such as the installation torque limit, installation deviation limit, and installation stress distribution of the clamp. There is no more mature test equipment available, which has an adverse effect on the performance detection, qualification identification and application verification of the connecting clamp. Therefore, there is an urgent need to design a field installation performance test method and device for aviation pipeline connecting clamps. Summary of the invention

[0004] In view of the problems existing in the prior art, the present invention provides a method and a device for testing the field installation performance of aviation pipeline connecting clamps. Through the coordinated use of a clamp assembly, a transmission conduit and a fixing assembly, the installation torque, installation error and stress distribution of the clamp assembly can be tested simultaneously, so as to more reasonably guide the field installation application of the clamp, provide data support and reference for the iterative optimization design of the clamp, and solve the problem of the lack of installation adaptability-related testing methods and effective data in the field application of the clamp.

[0005] The present invention provides a method for testing the field installation performance of an aviation pipeline connection clamp, which comprises the following steps:

[0006] S1, assemble the clamp assembly;

[0007] S2. Detect the installation torque of the clamp assembly;

[0008] S21, open the switch valve on the gas storage tank, the gas enters the clamp assembly through the transmission conduit, and the installation torque is applied to the clamp assembly by a torque wrench;

[0009] S22, slowly pressurize the clamp assembly to the rated working pressure, maintain the pressure after the pressure stabilizes, and measure the leakage of the clamp assembly;

[0010] S23. Increase the installation torque. When the leakage of the clamp assembly N ≤ the leakage threshold, the torque value of the torque wrench is the minimum installation torque M. min Continue to increase the torque until the clamp assembly undergoes plastic deformation and damage. At this time, the torque value of the torque wrench is the maximum installation torque M. max ;

[0011] S24, fitting a curve of the relationship between the leakage amount and the installation torque of the clamp assembly according to the test data results;

[0012] S3, detecting the installation error of the clamp assembly;

[0013] S31. When the clamp assembly is assembled, the transmission conduit is fixed to the base through the first lock body, the second lock body and the bolts, and the installation positions of the first lock body and the second lock body that fix the transmission conduit are adjusted to set different radial deviations and angular deviations of the axis of the clamp assembly;

[0014] S32. Under different installation deviations, the axis radial deviation and axis angle deviation of the clamp assembly gradually increase, and it is determined that the clamp assembly can be installed normally;

[0015] S33. As the radial deviation of the installation axis and the installation angle deviation increase, when the leakage amount N of the clamp assembly is greater than the leakage amount threshold, the radial deviation of the axis is the maximum radial deviation of the axis D. max , the angle deviation is the maximum angle deviation α max ;

[0016] S34, fitting a curve of the relationship between the leakage amount and the installation deviation of the clamp assembly according to the test data results;

[0017] S4. Detect the stress of the clamp assembly;

[0018] S41, applying different installation torques to the clamp assembly by a torque wrench, the torques gradually increasing, selecting multiple stress test position points P on the clamp ring in the clamp assembly, setting strain gauges at the measuring position points P, and using a dynamic tester to collect and record strain data of each stress test position point P;

[0019] S42, determining the elastic modulus E according to the material of the clamp, and obtaining the stress value through the relationship between the stress σ and the strain gauge strain ε: σ = E × ε;

[0020] S43, fitting a curve of the relationship between the installation torque and stress of the clamp assembly according to the test data results;

[0021] S5. Determine whether the clamp assembly can be installed normally. Combined with the relationship curve between the leakage amount and the installation torque of the clamp assembly in step S2, the relationship curve between the leakage amount and the installation deviation of the clamp assembly in step S3, and the relationship curve between the installation torque and stress of the clamp assembly in step S4, the installation torque and stress of the clamp assembly remain stable, and when the radial deviation of the axis of the clamp assembly is less than 0.2 mm and the angular deviation of the axis of the clamp assembly is less than 0.5°, the leakage is less than the leakage threshold, and the clamp assembly meets the performance requirements and can be installed normally.

[0022] Preferably, the installation torque ranges from 0.01 to 16 N / m, and the stress ranges from 0.01 to 100 MPa.

[0023] Preferably, the leakage threshold is DN×0.011 L / min, wherein DN is the nominal diameter of the transmission conduit.

[0024] The second aspect of the present invention provides an installation adaptability testing device for aviation pipeline connecting clamps, which includes a clamp assembly, a transmission conduit, a fixing assembly, a torque wrench, a strain gauge and an air tank, the clamp assembly is sleeved on the connection of the transmission conduit, the transmission conduit is set on the base through the fixing assembly, the torque wrench's sleeve is clamped with the second end of the locking rod of the clamp assembly, the output port of the air tank is connected to the transmission conduit through an air pipe, and the strain gauge is circumferentially arranged on the clamp ring of the clamp assembly.

[0025] Preferably, the clamp assembly includes a first clamp ring, a second clamp ring, a support frame, a rotating shaft and a locking rod, the first end of the first clamp ring is rotatably connected to the first end of the second clamp ring, the second end of the first clamp ring is arranged at the first end of the support frame through the rotating shaft, the two ends of the rotating shaft are passed through both sides of the support frame, and the rotating shaft can slide in the annular groove of the support frame, the second end of the second clamp ring is connected to the second end of the support frame, the first end of the locking rod is connected to the middle part of the rotating shaft, and the locking rod is threadedly connected to the threaded hole on the support frame.

[0026] Preferably, the fixing assembly comprises a first lock body, a second lock body and a base, and the first lock body and the second lock body are fixed to the base by bolts respectively.

[0027] Preferably, the position of the strain gauge on the clamp assembly is: the horizontal symmetry axis is 2 stress test points, and the positions at 45° to the horizontal axis are 4 stress test points, and the strain gauge is connected to the dynamic tester through a test line.

[0028] Compared with the prior art, the present invention has the following advantages:

[0029] The invention discloses a method and a device for testing the field installation performance of an aviation pipeline connection clamp. By applying pressure and installation torque to the clamp and simultaneously measuring the installation torque, installation error and stress distribution of the clamp, the method can guide the field installation application of the clamp in a more scientific and reasonable manner, and can also provide data support and reference for iterative optimization design of the clamp, and can be widely used in the aerospace field. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of the overall structure of the installation adaptability testing device for aviation pipeline connection clamps of the present invention;

[0031] Figure 2 It is a structural schematic diagram of a clamp assembly in a device for testing the installation adaptability of an aviation pipeline connection clamp of the present invention;

[0032] Figure 3 It is a structural schematic diagram of a fixing assembly in a field installation performance testing device for an aviation pipeline connection clamp of the present invention;

[0033] Figure 4 It is a flow chart of a method for testing the field installation performance of an aviation pipeline connection clamp of the present invention;

[0034] Figure 5 It is a relationship diagram between installation torque and leakage in the field installation performance test method for aviation pipeline connection clamps of the present invention;

[0035] Figure 6 It is a relationship diagram between the radial deviation of the central axis and the leakage amount in the field installation performance test method for the aviation pipeline connection clamp of the present invention;

[0036] Figure 7 It is a relationship diagram between the axis angle deviation and the leakage amount in the field installation performance test method for the aviation pipeline connection clamp of the present invention;

[0037] Figure 8a-8f It is a diagram showing the relationship between the installation torque and stress at each position point P in the field installation performance test method for the aviation pipeline connection clamp of the present invention.

[0038] Main reference numerals:

[0039] Clamp assembly 1, first clamp ring 11, second clamp ring 12, support frame 13, ring groove 131, rotating shaft 14, locking rod 15, transmission conduit 2, fixing assembly 3, first lock body 31, second lock body 32, base 33, torque wrench 4, strain gauge 5, gas storage tank 6, dynamic tester 7. DETAILED DESCRIPTION

[0040] In order to fully describe the technical content, structural features, objectives and effects of the present invention, the following will be described in detail with reference to the accompanying drawings.

[0041] The present invention is used for the field installation performance testing method of the aviation pipeline connection clamp, such as Figure 4 As shown, the following steps are included:

[0042] S1. Assemble the clamp assembly.

[0043] S2. Check the installation torque of the clamp assembly.

[0044] S3. Check the installation error of the clamp assembly.

[0045] S4. Detect the stress of the clamp assembly.

[0046] In a preferred embodiment of the present invention, the installation torque range in steps S2, S3 and S4 is 0-16 N / m, the stress range is 0-100 MPa, and the leakage threshold is DN×0.011 L / min, where DN is the nominal diameter of the transmission conduit.

[0047] Installation adaptability test device for aviation pipeline connection clamps, such as Figure 1 As shown, it includes a clamp assembly 1, a transmission conduit 2, a fixing assembly 3, a torque wrench 4, a strain gauge 5 and an air storage tank 6. The clamp assembly 1 is sleeved on the connection of the transmission conduit 2, and the transmission conduit 2 is set on the base 33 through the fixing assembly 3. The clamping sleeve of the torque wrench 4 is clamped with the second end of the locking rod 15 of the clamp assembly 1, and the output port of the air storage tank 5 is connected to the transmission conduit 2 through the air pipe. The strain gauge 5 is circumferentially arranged on the clamp ring of the clamp assembly 1.

[0048] like Figure 2 As shown, the clamp assembly 1 includes a first clamp ring 11, a second clamp ring 12, a support frame 13, a rotating shaft 14 and a locking rod 15. The first end of the first clamp ring 11 is rotatably connected to the first end of the second clamp ring 12. The second end of the first clamp ring 11 is arranged at the first end of the support frame 13 through the rotating shaft 14. The two ends of the rotating shaft 14 are arranged on both sides of the support frame 13, and the rotating shaft 14 can slide in the annular groove 131 of the support frame 13. The second end of the second clamp ring 12 is connected to the second end of the support frame 13. The first end of the locking rod 1 is connected to the middle of the rotating shaft 14, and the locking rod 1 is threadedly connected to the threaded hole on the support frame 13. The position of the strain gauge 5 on the clamp assembly 1 is: the horizontal symmetry axis is 2 stress test points, and the position at 45° with the horizontal axis is 4 stress test points. The strain gauge 5 is connected to the dynamic tester 7 through a test line.

[0049] like Figure 3 As shown, the fixing assembly 3 includes a first lock body 31 , a second lock body 32 and a base 33 , and the first lock body 31 and the second lock body 32 are fixed to the base 33 by bolts respectively.

[0050] The following is a further description of the field installation performance testing method for the aviation pipeline connection clamp of the present invention in conjunction with the embodiments:

[0051] The testing method of the present invention is implemented as follows:

[0052] S1. Assemble the clamp assembly 1.

[0053] S2. Detect the installation torque of the clamp assembly 1.

[0054] S21, open the switch valve on the gas storage tank 6, the gas enters the clamp assembly 1 through the transmission conduit 2, and the installation torque is applied to the clamp assembly 1 through the torque wrench 4.

[0055] S22. Slowly pressurize the clamp assembly 1 to the rated working pressure. After the pressure stabilizes, maintain the pressure for 15 minutes, and measure the leakage of the clamp assembly 1 for 1 minute.

[0056] S23, increase the installation torque. When the leakage amount N of the clamp assembly 1 reaches the leakage amount threshold, the torque value of the torque wrench 4 is the minimum installation torque M. min Continue to increase the torque until the clamp assembly 1 undergoes plastic deformation and damage. At this time, the torque value of the torque wrench 4 is the maximum installation torque M max .

[0057] S24, such as Figure 5 As shown, the relationship curve between the leakage of the clamp assembly and the installation torque is fitted according to the test data results, and the installation torque-leakage test results are shown in Table 1.

[0058] Table 1 Installation torque-leakage test results

[0059]

[0060] By analyzing the leakage data of the clamp assembly under different installation torques, we can obtain:

[0061] (1) When the installation torque of the clamp assembly is 12 Nm, the maximum leakage of the clamp assembly 1 is 1.242 L / min, which exceeds the maximum value of 1.1 L / min specified in the standard and does not meet the requirements.

[0062] (2) When the installation torque is 13 Nm, the maximum leakage of the clamp assembly 1 is 0.984 L / min, which is less than the maximum value of 1.1 L / min specified in the standard and meets the theoretical value requirements. As the installation torque increases, the leakage tends to decrease. However, when the installation torque exceeds 14 Nm, the leakage tends to stabilize. Continuing to increase the installation torque will only increase the stress of the clamp assembly 1, but has no practical significance for improving the sealing of the clamp assembly 1. Therefore, the recommended installation torque of the clamp is about 14 Nm.

[0063] S3, detecting the installation error of the clamp assembly 4.

[0064] S31. When the clamp assembly 4 is assembled, the transmission conduit 2 is fixed to the base 33 by the first lock body 31, the second lock body 32 and bolts. By adjusting the installation positions of the first lock body 31 and the second lock body 32 that fix the transmission conduit 2, different axial radial deviations and angular deviations of the clamp assembly 1 are set.

[0065] S32. Under different installation deviations, the axis radial deviation and the axis angular deviation gradually increase, and it is determined that the clamp assembly 1 can be installed normally.

[0066] S33. As the radial deviation of the installation axis and the installation angle deviation increase, when the leakage amount N of the clamp assembly 1 is greater than the leakage amount threshold, the radial deviation of the axis is the maximum radial deviation D. max , this angle deviation is the maximum angle deviation.

[0067] S34, such as Figure 6 and Figure 7 As shown, the relationship curve between the leakage and installation deviation of the clamp assembly 1 is fitted according to the test data results. During the test, it was found that when the radial deviation of the axis was 0.3mm and the installation angle deviation α=1°, the clamp assembly could not be installed normally, so the upper limit and interval of the deviation were adjusted, and an offset test was performed every 0.1mm and 0.5°. The test results are shown in Tables 2 and 3.

[0068] Table 2 Axis radial offset test results

[0069]

[0070] By analyzing the installation status and leakage data under different axis radial deviations, it can be seen that: when the axis radial deviation is less than 0.2mm, the clamp assembly can be installed normally, and the leakage is less than the maximum theoretical value of 1.1L / min. When the deviation exceeds 0.2mm, the clamp assembly 1 will not be able to be installed normally. Therefore, the axis radial offset limit is about 0.2mm. It is recommended to control the axis radial installation deviation within 0.2mm as much as possible during actual installation.

[0071] Table 3 Angular deviation limit test results

[0072]

[0073]

[0074] By analyzing the installation status and leakage data under different installation angle deviations, it can be seen that: when the radial deviation of the axis is less than 0.5°, the clamp assembly can be installed normally, and the leakage is less than the maximum theoretical value of 1.1L / min. When the installation angle deviation exceeds 0.5°mm, the clamp assembly 1 will not be able to be installed normally, and the angular deviation limit is about 0.5°. It is recommended to control the angle installation deviation within 0.5° during actual installation.

[0075] S4, detecting the stress of the clamp assembly 1.

[0076] S41. Apply different installation torques to the clamp assembly 1 through the torque wrench 4, and the torque gradually increases. Select 6 stress test position points P on the clamp ring in the clamp assembly 1, set strain gauges at the measurement position points P, and use the dynamic tester 7 to collect and record the strain data of each position point P.

[0077] S42. Determine the elastic modulus E according to the material of the clamp. The material of the clamp is GH4169, and its elastic modulus is 199.9 GPa. The stress value is obtained through the relationship between stress σ and strain gauge strain ε: σ=E×ε.

[0078] S43, such as Figure 8a-8f As shown, the relationship curve between the installation torque and stress of the clamp assembly is fitted according to the test data results, and the test results are shown in Table 4.

[0079] Table 4 Installation torque-stress distribution test results

[0080]

[0081]

[0082] By analyzing the stress test data of each point P under different installation torques, we can obtain:

[0083] (1) As the installation torque increases, the stresses at the six points P tend to increase.

[0084] (2) The stress levels at points P1 and P6 are the highest, followed by those at points P2 and P5, and the lowest at points P3 and P4. When the installation torque is 12 Nm, the maximum stress is at point P1, with a stress of 488.9 MPa, and the minimum stress is at point P4, with a stress of 305.5 MPa. When the installation torque is 16 Nm, the maximum stress is at point P1, with a stress of 607.1 MPa, and the minimum stress is at point P4, with a stress of 319.8 MPa. Preliminary analysis shows that since points P1 and P6 are located on both sides of the tightening bolts and the forces are most concentrated, the stress at points P1 and P6 is relatively the largest.

[0085] S5. Determine whether the clamp assembly can be installed normally. Combined with the relationship curve between the leakage amount and the installation torque of the clamp assembly in step S2, the relationship curve between the leakage amount and the installation deviation of the clamp assembly in step S3, and the relationship curve between the installation torque and stress of the clamp assembly in step S4, take the XXX-400 clamp assembly as an example. When the clamp assembly is not deformed, the installation torque and stress of the clamp assembly remain stable, and the installation torque is 14 Nm, the radial deviation of the axis is less than 0.2 mm, and the angular installation deviation is less than 0.5°, the leakage is less than 1.1 L / min, and the clamp assembly meets the performance requirements and can be installed normally.

[0086] The present invention is a method and device for testing the field installation performance of an aviation pipeline connecting clamp. Through the coordinated use of a clamp assembly 1, a transmission conduit 2 and a fixing assembly 3, the installation torque, installation error and stress distribution of the clamp assembly 1 can be tested simultaneously, and the field installation application of the clamp can be guided more scientifically and reasonably, and data support and reference can be provided for the iterative optimization design of the clamp, thus solving the problem of the lack of installation adaptability-related data of the clamp when the clamp is currently used in the field, and the method and device can be widely used in the aerospace field.

[0087] The embodiments described above are only descriptions of the preferred implementation modes of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. A method for testing the field installation performance of an aviation pipeline connection clamp, characterized in that: It includes the following steps: S1, assemble the clamp assembly; S2. Detect the installation torque of the clamp assembly; S21, open the switch valve on the gas storage tank, the gas enters the clamp assembly through the transmission conduit, and the installation torque is applied to the clamp assembly by a torque wrench; S22, slowly pressurize the clamp assembly to the rated working pressure, maintain the pressure after the pressure stabilizes, and measure the leakage of the clamp assembly; S23. Increase the installation torque. When the leakage of the clamp assembly N ≤ the leakage threshold, the torque value of the torque wrench is the minimum installation torque M. min Continue to increase the torque until the clamp assembly undergoes plastic deformation and damage. At this time, the torque value of the torque wrench is the maximum installation torque M. max ; S24, fitting a curve of the relationship between the leakage amount and the installation torque of the clamp assembly according to the test data results; S3, detecting the installation error of the clamp assembly; S31. When the clamp assembly is assembled, the transmission conduit is fixed to the base through the first lock body, the second lock body and the bolts, and the installation positions of the first lock body and the second lock body that fix the transmission conduit are adjusted to set different radial deviations and angular deviations of the axis of the clamp assembly; S32. Under different installation deviations, the axis radial deviation and axis angle deviation of the clamp assembly gradually increase, and it is determined that the clamp assembly can be installed normally; S33. As the radial deviation of the installation axis and the installation angle deviation increase, when the leakage amount N of the clamp assembly is greater than the leakage amount threshold, the radial deviation of the axis is the maximum radial deviation of the axis D. max , the angle deviation is the maximum angle deviation α max ; S34, fitting a curve of the relationship between the leakage amount and the installation deviation of the clamp assembly according to the test data results; S4. Detect the stress of the clamp assembly; S41, applying different installation torques to the clamp assembly by a torque wrench, the torques gradually increasing, selecting multiple stress test position points P on the clamp ring in the clamp assembly, setting strain gauges at the measuring position points P, and using a dynamic tester to collect and record strain data of each stress test position point P; S42, determine the elastic modulus E according to the material of the clamp, and obtain the stress value through the relationship between stress σ and strain gauge strain ε: σ = E × ε; S43, fitting a curve of the relationship between the installation torque and stress of the clamp assembly according to the test data results; S5. Determine whether the clamp assembly can be installed normally. Combined with the relationship curve between the leakage amount and the installation torque of the clamp assembly in step S2, the relationship curve between the leakage amount and the installation deviation of the clamp assembly in step S3, and the relationship curve between the installation torque and stress of the clamp assembly in step S4, the installation torque and stress of the clamp assembly remain stable, and when the radial deviation of the axis of the clamp assembly is less than 0.2 mm and the angular deviation of the axis of the clamp assembly is less than 0.5°, the leakage is less than the leakage threshold, and the clamp assembly meets the performance requirements and can be installed normally.

2. The field installation performance testing method for aviation pipeline connection clamp according to claim 1 is characterized in that: The installation torque ranges from 0.01 to 16 N / m, and the stress ranges from 0.01 to 100 MPa.

3. The field installation performance testing method for aviation pipeline connection clamp according to claim 1 is characterized in that: The leakage threshold is DN×0.011 L / min, wherein DN is the nominal diameter of the transmission conduit.

4. A testing device for the field installation performance testing method of an aviation pipeline connection clamp according to any one of claims 1 to 3, characterized in that: It includes a clamp assembly, a transmission conduit, a fixing assembly, a torque wrench, a strain gauge and an air storage tank. The clamp assembly is sleeved on the connection of the transmission conduit, and the transmission conduit is arranged on the base through the fixing assembly. The clamping sleeve of the torque wrench is clamped with the second end of the locking rod of the clamp assembly. The output port of the air storage tank is connected to the transmission conduit through an air pipe, and the strain gauge is circumferentially arranged on the clamp ring of the clamp assembly; the fixing assembly includes a first lock body, a second lock body and a base. The first lock body and the second lock body are respectively fixed to the base by bolts.

5. The testing device for the field installation performance testing method of the aviation pipeline connection clamp according to claim 4 is characterized in that: The clamp assembly includes a first clamp ring, a second clamp ring, a support frame, a rotating shaft and a locking rod. The first end of the first clamp ring is rotatably connected to the first end of the second clamp ring, the second end of the first clamp ring is arranged at the first end of the support frame through the rotating shaft, the two ends of the rotating shaft are passed through the two sides of the support frame, and the rotating shaft can slide in the annular groove of the support frame, the second end of the second clamp ring is connected to the second end of the support frame, the first end of the locking rod is connected to the middle of the rotating shaft, and the locking rod is threadedly connected to the threaded hole on the support frame.

6. The testing device for the field installation performance testing method of the aviation pipeline connection clamp according to claim 4 is characterized in that: The position of the strain gauge on the clamp assembly is: the horizontal symmetry axis is 2 stress test points, and the positions at 45° to the horizontal axis are 4 stress test points. The strain gauge is connected to the dynamic tester through a test line.

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