Test method for load-carrying capacity of aviation lubricating oil high-speed gears

Abstract

The present invention relates to the field of lubricant oil testing technology, and specifically discloses a method for testing the load-bearing capacity of aviation lubricant high-speed gears. During the test, the pinion speed reaches 10,000±10 r / min, the test lubricant oil inlet temperature is 74±2.5°C, the test lubricant oil flow rate is 1,000±5 mL / min, and the test time is 10 min±10 s. The FZG-AR gear pair and the FZG-CR gear pair used in the high-speed FZG gear testing machine both include a large gear and a small gear, and the gear ratio between the large gear and the small gear is 3: 2. The center distance between the large and small gears is 91.5 mm. The sum of the modification coefficients for both the FZG-AR and FZG-CR gear pairs is 0.34-0.36. The modification coefficients for the small and small gears in the FZG-AR gear pair range from 0.45-0.58; the modification coefficients for the small and small gears in the FZG-CR gear pair range from 0.15-0.27. The FZG-AR gear pair is used to test helicopter gearbox lubricants, while the FZG-CR gear pair is used to test aviation turbine engine lubricants. This solution addresses the lack of existing methods for testing the load-bearing capacity of aviation lubricants under high-speed gears, other than the Ryder gear load-bearing capacity test method.

Description

Technical Field

[0001] The invention relates to the technical field of lubricating oil testing, and in particular to a method for testing the load-bearing capacity of aviation lubricating oil high-speed gears. Background Art

[0002] Aviation lubricants provide lubrication, cooling, and impurity transport for aircraft engine bearings, gears, and other components. To ensure the aircraft engine's ability to operate safely, stably, and for extended periods under high-temperature, high-speed conditions, the lubricant's load-bearing capacity is crucial. Lubricant load-bearing capacity testing is also a necessary inspection before the lubricant undergoes airworthiness certification and is put into civil aviation use. To assess the lubricant's load-bearing capacity, the lubricant needs to be tested under operating conditions that simulate actual aircraft engines.

[0003] In the prior art, the Ryder gear load capacity test method is used to test the load-bearing capacity of lubricants under high-speed and high-load conditions. However, since the Ryder gear load capacity test method (hereinafter referred to as the Ryder test method) is a single-source method from abroad, and the Ryder gear testing machine used for this test method is also unique to abroad, domestic lubricant manufacturers must send the lubricants to foreign laboratories for testing if they want to test the load-bearing capacity of lubricants. However, cross-border testing requires extremely high financial and time costs, which limits the production of domestic lubricants.

[0004] To solve the above problems, the inventors tried other ways to test the load-bearing capacity of lubricating oil, such as improving the existing standard FZG gear testing machine in terms of power and lubricating oil usage to obtain a high-speed FZG gear testing machine capable of performing high-speed gear testing (such as the high-speed gear load-bearing capacity testing machine disclosed in the enterprise standard number Q / 510107C.SD4001-2021, hereinafter referred to as the "high-speed FZG gear testing machine"). The reason for choosing the high-speed FZG gear testing machine for the test is that the tooth ratio of the test gear on the high-speed FZG gear testing machine is 3:2, while the tooth ratio of the Ryder gear testing machine is 1:1, but the actual gear tooth ratio in the domestic aircraft engine gearbox is more in line with the tooth ratio on the high-speed FZG gear testing machine. Therefore, from this point of view, the use of the high-speed FZG gear testing machine can better and more accurately restore the actual operating conditions of the domestic aircraft engine.

[0005] During the test, the high-speed FZG gear tester was used to test the load-bearing capacity of lubricating oils under low-speed gears. The standard FZG gear tester is designed for testing the load-bearing capacity of lubricating oils under low-speed gears. When testing under low-speed gears, the standard FZG gear tester offers two different gear pair options: the standard FZG-A gear pair and the standard FZG-C gear pair. During the test, one of these gear pairs was selected based on the testing requirements of different aviation lubricating oils. The gear pair speed was approximately 1450 r / min, the test duration for each load level was 15 minutes at a constant speed, the oil bath was 1.25 L, the lubricating oil temperature was ambient temperature under load level 5, and the oil temperature was controlled at 90°C for load levels 5 and above. Under this test method, the load-bearing capacity test level of the lubricating oil is 1-12.

[0006] When using the high-speed FZG gear tester for high-speed gear and high-load testing, whether using the standard FZG-A gear pair or the standard FZG-C gear pair, the test is carried out according to the operating conditions of the Ryder gear tester, that is, the pinion speed of the gear pair reaches 10,000 rpm, the test duration of each load level is constant speed operation for 10 minutes, the oil temperature of the tested lubricant sprayed onto the gear is 74°C, and the lubrication flow rate is 1 L / min. However, when using a standard FZG-A gear pair to test aviation turbine engine lubricants that meet the requirements of SAE AS5780, the gear failed at level 4 (corresponding to a loading load of 70 Nm), and the gear bonding temperature at the time of failure was 270°C. Because the failure level is too low (the loading load level for lubricant load capacity testing can theoretically reach 16 levels), it is impossible to accurately distinguish the load capacity of different aviation turbine engine lubricants. When using a standard FZG-C gear pair to test aviation turbine engine lubricants that meet the requirements of SAE AS5780, the gear failed at level 7 (corresponding to a loading load of 123 Nm), and the gear bonding temperature at the time of failure was 275°C. In both cases, when the gear fails, the tooth surface wear of the pinion will suddenly increase to more than 80% (for example, the wear is about 10% in the previous load test, while the wear of the next gear exceeds 80%), the testing machine will vibrate significantly, the lubricant will overheat, and the oil film will rupture and lose its lubricating properties. When testing helicopter gearbox lubricants that meet the requirements of MIL-PRF-85734 using the standard FZG-A gear pair, the test load reached level 7, the bonding temperature at which the gears failed was 395°C, the pinion tooth surface wear suddenly increased to over 80%, the testing machine vibrated significantly, the lubricant overheated, the oil film ruptured and lost its lubricating properties; and when testing helicopter gearbox lubricants that meet the requirements of MIL-PRF-85734 using the standard FZG-C gear pair, the pinion did not fail until the maximum load (level 16 load, corresponding to a loading load of 280Nm), making it impossible to distinguish the load-bearing capacity of this type of lubricant.

[0007] It can be seen that the high-speed FZG gear testing machine, regardless of whether it uses the standard FZG-A gear pair or the standard FZG-C gear pair, cannot be used to evaluate the load-bearing capacity of aviation lubricants under high-speed and high-load conditions. As a result, there is still no other method for testing the load-bearing capacity of aviation lubricants under high-speed gears and high loads except for the Ryder gear load-bearing capacity test method. Summary of the Invention

[0008] The present invention aims to provide a method for testing the load-bearing capacity of aviation lubricants for high-speed gears, so as to solve the problem in the prior art of lacking other methods for testing the load-bearing capacity of aviation lubricants under high-speed gears except the Ryder gear load-bearing capacity test method.

[0009] In order to achieve the above object, the present invention adopts the following technical solutions:

[0010] The test method for the load-bearing capacity of aviation lubricant high-speed gears is as follows: during the test, the pinion speed reaches 10000±10r / min, the test lubricant inlet temperature is 74±2.5℃, the test lubricant flow rate is 1000±5mL / min, and the test time is 10min±10s; the test is carried out using a high-speed FZG gear testing machine. The FZG-AR gear pair and FZG-CR gear pair used in the high-speed FZG gear testing machine both include a large gear and a small gear, and the gear ratio of the large gear to the small gear is 3:2. The center distance of the gears is 91.5mm. The sum of the modification coefficients of the FZG-AR and FZG-CR gear pairs is 0.34-0.36. The modification coefficients of the small gears in the FZG-AR gear pair range from 0.45-0.58; the modification coefficients of the small gears in the FZG-CR gear pair range from 0.15-0.27. The FZG-AR gear pair is used to test helicopter gearbox lubricants that meet the requirements of MIL-PRF-85734, and the FZG-CR gear pair is used to test aviation turbine engine lubricants that meet the requirements of SAE AS5780.

[0011] The principle and advantage of this solution are: when using this method to test the lubricant load-bearing capacity of high-speed gears, the gear pair of the original Ryder gear testing machine is no longer used. Instead, the gear pair with a gear ratio of 3:2 of the high-speed FZG gear testing machine is used, so that the test can better and more accurately restore the actual operating conditions of domestic aircraft engines.

[0012] During the test, the gears with improved modification coefficients of the standard FZG-A gear pair and the standard FZG-C gear pair were tested (obtaining FZG-AR gear pair and FZG-CR gear pair). The modification coefficient of the improved pinion was in the range of 0.45-0.58, and the FZG-AR gear pair with a sum of modification coefficients of 0.34-0.36 was tested on a high-speed FZG gear testing machine for helicopter gearbox lubricants that met the requirements of MIL-PRF-85734. The tooth surface failure load level was increased from level 7 using the standard FZG-A gear pair to level 9-11 of this solution (level 9 corresponding to a load of 158 Nm, level 11 corresponding to a load of 193 Nm), and during the test process The tooth surface wear area increases basically linearly, and the situation in the prior art where the gear wear area suddenly increases before the gear fails will not occur. This makes it convenient for testers to accurately and quickly find the loading load at the time of tooth surface wear failure, and then predict in advance that after the previous level of load loading of the failure load is completed, the next level of load loading for foreseeable gear failure will no longer be continued, thereby ensuring that in the test process of helicopter gearbox lubricants that meet the requirements of MIL-PRF-85734, the load-bearing capacity of different helicopter gearbox lubricants can be distinguished, and it can be ensured that the load-bearing capacity test will not cause large-scale vibration and high temperature to affect the service life of the entire high-speed FZG gear testing machine.

[0013] When testing aviation turbine engine lubricants that meet SAE AS5780 requirements, the FZG-CR gear pair used in the test has a displacement coefficient range of 0.15-0.27 for the small gears. When tested with this gear pair, the tooth surface failure load level is increased from level 7 using the standard FZG-CR gear pair to levels 9-11 using this solution. Furthermore, the tooth surface wear area increases linearly during the test. There is no need to stop the test until large-scale bonding or transient high temperatures occur on the tooth surface, thus avoiding damage to the high-speed FZG gear testing machine.

[0014] It can be seen that this solution, through the improvement of the standard FZG-A gear pair and the standard FZG-C gear pair to obtain the FZG-AR gear pair and the FZG-CR gear pair, combined with the use of the high-speed FZG gear testing machine, can ensure that the load level of the lubricating oil required by SAE AS5780 and the lubricating oil required by MIL-PRF-85734 when reaching the maximum effective bonding temperature is not less than level 9. The test load level of at least level 9 can basically meet the testing requirements of existing domestic lubricants. Therefore, this solution breaks the situation where only the Ryder gear load capacity test method is used to test the load capacity of aviation lubricants, greatly reducing the cost of load capacity testing of aviation lubricants.

[0015] Preferably, as an improvement, during the test, the ratio of the pinion tooth surface wear area to 17%-20% is used as the basis for judging gear failure.

[0016] Beneficial effects: In the art, the tooth surface wear area of ​​the pinion when it fails is set to 22.5%. However, in many tests, the tooth surface wear area of ​​the pinion changes suddenly after 17%, resulting in large-scale bonding of the tooth surface and generation of instantaneous high temperature after adding one level of load, and damage to the high-speed FZG gear testing machine. However, this solution breaks away from the failure judgment basis of 22.5% of the tooth surface wear area specified in the art, and instead sets the tooth surface wear area of ​​the pinion when it fails to 17%-20%. On the one hand, this test method makes reasonable use of the linear growth of the gear wear area during the test to calculate the load-bearing capacity of the lubricant being tested. On the other hand, it avoids damage to the high-speed FZG gear testing machine on the basis of ensuring the load-bearing capacity of the lubricant obtained by the test. In addition, it can also make the range of the tooth surface wear area before the gear fails more stable, which is conducive to improving the reliability of the test.

[0017] Preferably, as an improvement, when the displacement coefficient of the small gear in the FZG-AR gear pair is in the range of 0.52-0.58, the loading load when the gear fails is 158Nm-210Nm.

[0018] Preferably, as an improvement, when the modification coefficient of the small gear in the FZG-AR gear pair is in the range of 0.45-0.52, the loading load when the gear fails is 175Nm-210Nm.

[0019] Preferably, as an improvement, when the displacement coefficient of the small gear in the FZG-CR gear pair is in the range of 0.177-0.27, the loading load when the gear fails is 158Nm-193Nm.

[0020] Preferably, as an improvement, when the displacement coefficient of the small gear in the FZG-CR gear pair is in the range of 0.15-0.177, the loading load when the gear fails is 193Nm-228Nm.

[0021] Preferably, as an improvement, the carburized layer depth on the tooth surface of the FZG-AR gear pair is 0.9-1.3 mm, and the carburized layer depth on the tooth root is 0.75-1.15 mm.

[0022] Beneficial effects: This solution carburizes the tooth surface and tooth root to make the gear obtain higher surface hardness, wear resistance and high contact fatigue strength and bending fatigue strength.

[0023] Preferably, as an improvement, the carburized layer depth on the tooth surface and the carburized layer depth on the tooth root of the FZG-CR gear pair are both 1.0-1.2 mm.

[0024] Beneficial effects: This solution carburizes the tooth surface and tooth root to make the gear obtain higher surface hardness, wear resistance and high contact fatigue strength and bending fatigue strength.

[0025] Preferably, as an improvement, the gear pressure angle of the FZG-AR gear pair is 20°, and the gear pressure angle of the FZG-CR gear pair is 20°.

[0026] Preferably, as an improvement, the FZG-AR gear pair and the FZG-CR gear pair are both made of aviation materials.

[0027] Beneficial effect: By limiting the gear material to aviation material, the test gear is closer to the actual situation of domestic aircraft engines, which helps to make the test more accurate. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 Schematic diagram of the structure of the small gear in the FZG-AR gear pair in an embodiment of the present invention;

[0029] Figure 2 Schematic diagram of the structure of the large gear in the FZG-AR gear pair in an embodiment of the present invention;

[0030] Figure 3 Schematic diagram of the structure of the small gear in the FZG-CR gear pair in an embodiment of the present invention;

[0031] Figure 4 Schematic diagram of the structure of the large gear in the FZG-CR gear pair in an embodiment of the present invention;

[0032] Figure 5 This is the broken line graph of the loading load and gear bonding area before the gear fails in the test of test group 1;

[0033] Figure 6 This is the broken line graph of the loading load and gear bonding area before the gear fails in the test of test group 2;

[0034] Figure 7 This is the broken line graph of the loading load and gear bonding area before the gear fails in the test of test group 3;

[0035] Figure 8 This is the broken line graph of the loading load and gear bonding area before the gear fails in the test of test group 4;

[0036] Figure 9 This is the broken line graph of the loading load and gear bonding area before gear failure in test group 5;

[0037] Figure 10 This is a broken line graph of the loading load and gear bonding area before gear failure in test group 6. DETAILED DESCRIPTION

[0038] The following is further described in detail through specific implementation methods:

[0039] The embodiment is basically as shown in the attached Figures 1 to 10 As shown, the test method for the load-bearing capacity of aviation lubricant high-speed gears includes using a high-speed FZG gear testing machine for testing. The testing machine uses FZG-AR gear pairs and FZG-CR gear pairs. Both gear pairs include a large gear and a small gear. The gear ratio of the large gear and the small gear is 3:2. The center distance of the FZG-AR gear pair and the FZG-CR gear pair is the same, both 91.5mm. In this embodiment, the number of teeth of the large gear is 24, the number of teeth of the small gear is 16, and the module is 4.5; the gear pressure angle of the FZG-AR gear pair is 20°, and the gear pressure angle of the FZG-CR gear pair is 20°; the gear surface hardness of the FZG-AR gear pair is 58-63HRC, the core hardness is 33-41HRC, the tooth surface carburized layer depth is 0.9-1.3mm, and the tooth root carburized layer depth is 0.75-1.15mm; the FZG-CR gear pair The gear surface hardness is 58-63HRC, the core hardness is 30-42HRC, and the tooth surface and tooth root carburized layer depths are both 1.0-1.2mm. The sum of the modification coefficients of the FZG-AR and FZG-CR gear pairs is 0.34-0.36. The modification coefficients of the small gears in the FZG-AR gear pair range from 0.45-0.58, and the modification coefficients of the small gears in the FZG-CR gear pair range from 0.15-0.27. The gears in both the FZG-AR and FZG-CR gear pairs are made of AISI 9310 aviation material. The basic parameters of the FZG-AR and FZG-CR gear pairs in this embodiment are shown in Table 1 below.

[0040] Table 1 Basic parameters of FZG-AR gear pair and FZG-CR gear pair

[0041]

[0042] When the FZG-AR gear pair and the FZG-CR gear pair are used in conjunction with a high-speed FZG gear testing machine for testing, the pinion speed reaches 10,000±10 r / min, the test lubricant oil inlet temperature is 74±2.5°C, the test lubricant oil flow rate is 1000±5 mL / min, and the test time is 10 min±10 s; the FZG-AR gear pair is used to test helicopter gearbox lubricants that meet the requirements of MIL-PRF-85734, and the FZG-CR gear pair is used to test aviation turbine engine lubricants that meet the requirements of SAE AS5780; during the test, the pinion tooth surface wear area ratio of 17%-20% is used as the basis for judging gear failure. In this embodiment, the pinion tooth surface wear area of ​​18% can be selected as the basis for judging gear failure.

[0043] To verify this embodiment, three gear sets were set for the FZG-AR gear pair and the FZG-CR gear pair in Table 1 above. Three pairs of gear sets with the same parameters were produced. The sum of the modification coefficients of each pair of gears was 0.3532. The modification coefficients of all gear sets are shown in Table 2. The correspondence between the load level, loading load and Ryder test method using this method is shown in Table 3 below (this correspondence has been disclosed in the existing standard).

[0044] Table 2 Parameters of FZG-AR and FZG-CR gear pairs under different modification coefficients

[0045]

[0046] Table 3 Correspondence between load level and loading load

[0047] Load level The load in this embodiment is N·m Ryder test method load, kPa 1 18.0 34.0 2 35.0 68.0 3 53.0 102.0 4 70.0 136.0 5 88.0 170.0 6 105.0 204.0 7 123.0 238.0 8 140.0 272.0 9 158.0 306.0 10 175.0 340.0 11 193.0 374.0 12 210.0 408.0 13 228.0 442.0 14 245.0 476.0 15 263.0 510.0 16 280.0 544.0

[0048] A total of 18 gear pairs were tested in the three test groups mentioned above. A total of 9 gear pairs in test groups 1, 2, and 3 were tested using helicopter gearbox lubricant that meets the requirements of MIL-PRF-85734 (AeroShell Turbine Oil 555, a helicopter gearbox lubricant currently used in over 70% of the global civil aviation market, was selected as the test reference oil). The test results are shown in Table 4:

[0049] Table 4 Test data of FZG-AR gear pair

[0050]

[0051]

[0052]

[0053] An aviation turbine engine lubricant meeting the requirements of SAE AS5780 (e.g., Mobil Jet Oil II, an aviation turbine engine lubricant currently used in over 55% of the global civil aviation market, was selected as the test reference oil) was used to test a total of 9 gear pairs in Test Groups 4, 5, and 6. The test results are shown in Table 5 below.

[0054] Table 5 Test data of FZG-CR gear pair

[0055]

[0056]

[0057]

[0058] According to the data in Table 4 above, when the gear pair of Test Group 1 was tested on a high-speed FZG gear tester under the operating conditions of a Ryder gear tester using helicopter gearbox lubricants that meet the requirements of MIL-PRF-85734, the load level at which the gears failed could reach level 9 or even level 10. This ensures that when the helicopter gearbox lubricants are tested under this gear pair, they can be tested to a load level of at least level 8 without completely damaging the FZG tester.

[0059] When the gear pair in Test Group 2 was tested on a high-speed FZG gear tester under the operating conditions of a Ryder gear tester using helicopter gearbox lubricants that meet the requirements of MIL-PRF-85734, the load level at which the gears failed was able to reach level 10 or even level 12. This ensures that when testing helicopter gearbox lubricants using this gear pair, they can be tested to a load level of at least level 9 without completely damaging the FZG tester.

[0060] When the gear pair of Test Group 3 was tested on a high-speed FZG gear tester under the operating conditions of a Ryder gear tester using helicopter gearbox lubricants that meet the requirements of MIL-PRF-85734, the load level at which the gears failed was able to reach levels 11-12. This ensures that when the helicopter gearbox lubricant is tested under this gear pair, it can be tested to a load level of at least 10 without completely damaging the FZG tester.

[0061] Therefore, from the test data set in Table 4 above, it can be seen that when the FZG-AR gear pair of this embodiment is tested on a helicopter gearbox lubricant that meets the requirements of MIL-PRF-85734 on a high-speed FZG gear tester according to the operating conditions of a Ryder gear tester, the tooth surface failure load level can reach 9-12 (level 9 corresponds to a load of 158Nm, and level 12 corresponds to a load of 210Nm). Figures 5 to 7It can be seen that during the test of the FZG-AR gear pair for helicopter gearbox lubricants that meet the requirements of MIL-PRF-85734, the tooth surface wear area shows a basically linear increase. It can also find the load-bearing capacity of the lubricant when the total wear area of ​​the 16 tooth surfaces of the pinion accounts for 18% of the total effective contact area (that is, the load-bearing capacity of the lubricant under the basis for judging gear failure). Unlike the standard FZG-A gear pair, there is no need to stop the test until large-area bonding occurs on the gear surface, resulting in instantaneous high temperature. This greatly reduces the impact on the life of the high-speed FZG gear testing machine.

[0062] As for the FZG-CR gear pair, according to the data in Table 5, when the gear pair of Test Group 4 was tested on the high-speed FZG gear tester according to the operating conditions of the Ryder gear tester, the load level at which the gear failed could reach level 9 or even level 10. This ensures that when the aviation turbine engine lubricant meeting the requirements of SAE AS5780 is tested on the gear pair of Test Group 4, the load level can be tested to at least level 8 without completely damaging the high-speed FZG tester.

[0063] When the gear pair in Test Group 5 was tested on a high-speed FZG gear tester under the operating conditions of a Ryder gear tester, the load level at which the gear failed was able to reach level 11. This ensures that when aviation turbine engine lubricants that meet SAE AS5780 requirements are tested on the gear pair in Test Group 5, the load level can be tested to at least level 10 without completely damaging the high-speed FZG tester.

[0064] When the gear pair in Test Group 6 was tested on a high-speed FZG gear tester under the operating conditions of a Ryder gear tester, the load level at which the gear failed was able to reach 12-13. This ensures that when aviation turbine engine lubricants that meet SAE AS5780 requirements are tested on the gear pair in Test Group 6, the load level can be tested to at least 11 without completely damaging the high-speed FZG tester.

[0065] From the above analysis, it can be seen that when the aviation turbine engine lubricant that meets the requirements of SAE AS5780 is tested on a high-speed FZG gear tester according to the operating conditions of the Ryder gear tester, the bonding temperature of the gear is greatly increased, and nearly 90% of the test data can achieve the 9th level lubricant load capacity test under the premise of ensuring that the high-speed FZG tester is completely undamaged. At the same time, the gear wear area basically increases linearly under different load levels (combined with Figures 8 to 10), it is also possible to find the load-bearing capacity of the lubricant when the total wear area of ​​the 16 tooth surfaces of the pinion accounts for 18% of the total effective contact area (that is, the load-bearing capacity of the lubricant under the basis for judging gear failure). During the test, there is no need to stop the test only when large-scale bonding and instantaneous high temperature occur on the tooth surfaces, so as to avoid damage to the high-speed FZG gear testing machine. In addition, it can also make the range of the tooth surface wear area before the gear failure more stable, which is conducive to improving the reliability of the test.

[0066] From the above explanation, combined with the test data, it can be seen that this solution, through improvements to the standard FZG-A and FZG-C gear pairs, combined with the use of a high-speed FZG gear testing machine, can ensure that the load level of lubricants required by SAE AS5780 and MIL-PRF-85734 when reaching the maximum effective bonding temperature is not less than level 9. The test load level of level 9 basically meets the testing requirements of existing domestic lubricants. Therefore, this solution breaks the situation where the Ryder gear load capacity test method is the only method used to test the load capacity of aviation lubricants, greatly reducing the cost of aviation lubricant load capacity testing. In addition, as shown in Tables 4 and 5 above, the maximum failure load difference of the three parallel tests of gear pairs in the same test group does not exceed 1 level, indicating high test repeatability, which also indicates that the reliability of the test method is high.

[0067] The above is only an embodiment of the present invention, and the common knowledge such as the specific technical solutions and / or characteristics in the solution are not described in detail here. It should be pointed out that for those skilled in the art, without departing from the technical solution of the present invention, several variations and improvements can be made, which should also be regarded as the scope of protection of the present invention, and these will not affect the effect of the implementation of the present invention and the practicality of the patent. The scope of protection required by this application shall be based on the content of its claims, and the specific implementation methods and other records in the description can be used to interpret the content of the claims.

Claims

1. Aviation lubricant high-speed gear load capacity test method: During the test, the pinion speed reaches 10000±10 r / min, the test lubricant inlet temperature is 74±2.5℃, the test lubricant flow rate is 1000±5mL / min, and the test time is 10min±10s; the characteristics are: The test was conducted using a high-speed FZG gear testing machine. The FZG-AR and FZG-CR gear pairs used in the high-speed FZG gear testing machine both include a large gear and a small gear. The gear ratio of the large gear to the small gear is 3:2, and the center distance between the large gear and the small gear is 91.5mm. The sum of the modification coefficients of the FZG-AR and FZG-CR gear pairs is 0.34-0.

36. The modification coefficient of the small gear in the FZG-AR gear pair ranges from 0.45-0.58; the modification coefficient of the small gear in the FZG-CR gear pair ranges from 0.15-0.

27. The FZG-AR gear pair is used to test helicopter gearbox lubricants that meet the requirements of MIL-PRF-85734, and the FZG-CR gear pair is used to test aviation turbine engine lubricants that meet the requirements of SAE AS5780; When the modification coefficient of the small gear in the FZG-AR gear pair ranges from 0.52 to 0.58, the load at the time of gear failure is 158Nm-210Nm; When the modification coefficient of the small gear in the FZG-AR gear pair ranges from 0.45 to 0.52, the loading load at the time of gear failure is 175Nm-210Nm.

2. The method for testing the load-bearing capacity of aviation lubricant high-speed gears according to claim 1, characterized in that: During the test, the ratio of the pinion tooth surface wear area to 17%-20% was used as the basis for judging gear failure.

3. The method for testing the load-bearing capacity of aviation lubricant high-speed gears according to claim 1, characterized in that: When the modification coefficient of the small gear in the FZG-CR gear pair ranges from 0.177 to 0.27, the loading load when the gear fails is 158 Nm to 193 Nm.

4. The method for testing the load-bearing capacity of aviation lubricant high-speed gears according to claim 1, characterized in that: When the modification coefficient of the small gear in the FZG-CR gear pair ranges from 0.15 to 0.177, the loading load when the gear fails is 193 Nm to 228 Nm.

5. The method for testing the load-bearing capacity of aviation lubricant high-speed gears according to any one of claims 1 to 4, characterized in that: The carburized layer depth of the tooth surface of the FZG-AR gear pair is 0.9-1.3 mm, and the carburized layer depth of the tooth root is 0.75-1.15 mm.

6. The method for testing the load-bearing capacity of aviation lubricant high-speed gears according to any one of claims 1 to 4, characterized in that: The carburized layer depth on the tooth surface and the carburized layer depth on the tooth root of the FZG-CR gear pair are both 1.0-1.2 mm.

7. The method for testing the load-bearing capacity of aviation lubricant high-speed gears according to any one of claims 1 to 4, characterized in that: The gear pressure angle of the FZG-AR gear pair is 20°, and the gear pressure angle of the FZG-CR gear pair is 20°.

8. The method for testing the load-bearing capacity of aviation lubricant high-speed gears according to any one of claims 1 to 4, characterized in that: The FZG-AR gear pair and the FZG-CR gear pair are both made of aviation materials.

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