A low-temperature medium simulation test device for a space turbine pump bearing

Abstract

The present application relates to a kind of aerospace turbine pump bearing low temperature medium simulation test device, belong to bearing test device technical field, the test device will test shafting be divided into low temperature cooling section and normal temperature lubrication section, by subsection design, effectively reduce test cost, improve test efficiency, by the preloading spring on axial loading piston and compensation intake structure, improve the loading accuracy of axial force, by the design of axial guide linear bearing, prevent low temperature jam and high speed skid phenomenon, by the design of shaft center liquid inlet channel and helical auxiliary liquid inlet, effectively cool the inner ring of test bearing, by the division of cooling space in test cavity, effectively improve the flowability and cooling efficiency of cooling medium, the entire test device has higher reliability, stability and safety, suitable for the simulation test of low temperature bearing, can reduce test cost and difficulty, improve test efficiency.

Description

Technical Field

[0001] This invention relates to the field of bearing testing, and more specifically to a cryogenic medium simulation test device for aerospace turbopump bearings. Background Technology

[0002] The turbopump is the heart of a rocket engine, and the turbopump bearing is crucial for its long-term stable operation. Turbopump bearings operate in ultra-low temperature environments and withstand high-speed, heavy-load conditions. Cryogenic bearing testing is an important means of evaluating bearing performance in low-temperature environments. It mainly involves testing the bearing's operational stability, friction characteristics, load-bearing capacity, and lifespan under low-temperature conditions. The main purpose is to assess the bearing's performance under high-speed loading in low-temperature environments, clarify the bearing's service limits, and ensure its reliability and durability under specific low-temperature conditions. However, existing cryogenic bearing testing equipment still has many shortcomings.

[0003] On the one hand, to simulate the actual working conditions of cryogenic bearings, existing technologies use liquid nitrogen as a cryogenic medium for bearing testing, introducing liquid nitrogen into the entire test chamber for testing. The traditional liquid nitrogen full-area cooling method requires the entire test fixture to be made of cryogenic materials (such as bearings and seals), which is complex to process and costly, significantly increasing the cost compared to conventional testing. On the other hand, existing cryogenic testing devices have unreasonable flow path designs for the cooling medium in the cryogenic chamber, resulting in a large consumption of cryogenic medium and a lack of effective cooling measures for the bearing inner ring. When the bearing is under high-speed operation, inadequate cooling of the inner ring can easily lead to temperature rise and cause failures such as burning of the bearing inner ring. Furthermore, during cryogenic testing, the accuracy of axial loading force is affected by various factors such as temperature and pressure within the chamber, which in turn affects the stability and accuracy of the test.

[0004] In the prior art, the test chamber is divided into a low-temperature test chamber and a normal-temperature test chamber. The test bearing is located in the low-temperature chamber and the process bearing is located in the normal-temperature chamber. This can reduce the test cost and improve the test efficiency to a certain extent. However, the design of the low-temperature cooling chamber in the existing patent is relatively simple and does not take into account the cooling problem of the bearing inner ring. The cooling efficiency is relatively low, and the problem of the accuracy of axial loading force is not considered. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this invention provides a cryogenic medium simulation test device for aerospace turbopump bearings. By optimizing a series of issues such as the test chamber, axial loading, and cooling efficiency, the stability, safety, and reliability of the cryogenic test device are effectively improved.

[0006] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0007] A cryogenic medium simulation test device for aerospace turbopump bearings includes a test spindle, a test bearing, a test auxiliary bearing, a radial loading piston, and an axial loading piston. The test auxiliary bearing includes a radial loading bearing and an axial positioning bearing. The test bearing and the test auxiliary bearing are positioned and installed on the test spindle to form a test shaft system. The test shaft system is divided into a cryogenic cooling section and a normal temperature lubrication section. The test bearing is located in the cryogenic cooling section, and a test chamber shell is provided outside the cryogenic cooling section. The test auxiliary bearing is located in the normal temperature lubrication section, and a test chamber shell is provided outside the normal temperature lubrication section. The test chamber shell and the test auxiliary chamber shell are sealed and isolated by a sealing assembly. The test bearing is installed in a test bearing housing. An axial loading cover is provided on the left side of the outer ring of the test bearing. An axial guide linear bearing is provided between the axial loading cover and the test bearing housing. The axial loading piston loads the test bearing through the axial loading cover. The axial loading piston is provided with a preload spring and a compensation air intake structure.

[0008] Furthermore, multiple axial guide linear bearings are evenly distributed circumferentially between the axial loading cap and the test bearing housing. The axial guide linear bearings include balls and ball cages. The ball cages can distribute and limit the balls. Corresponding ball grooves are provided between the axial loading cap and the test bearing housing. The balls are installed and held in the ball grooves by the ball cages.

[0009] Furthermore, the inner side of the test bearing housing and the outer side of the axial loading cover are designed as parallel conical surfaces, with the left side being larger than the right side, and the angle of the conical surfaces is set according to actual needs.

[0010] Furthermore, multiple rectangular grooves are evenly distributed circumferentially on the end face of the axial loading gland that contacts the outer ring of the test bearing to increase the friction between the axial loading gland and the outer ring of the test bearing.

[0011] Furthermore, the axial loading piston is mounted on the left end cover of the test chamber housing via an axial piston mounting seat. The axial loading piston is provided with a retaining ring, which divides the axial piston mounting seat into a left chamber and a right chamber. The left chamber is provided with a preload spring and has a compensation air inlet, while the right chamber is provided with an air outlet.

[0012] Furthermore, the test bearing is installed at the left end of the test spindle, and an inner ring cover is provided on the left side of the test bearing. The inner ring cover is fixed to the end face of the test spindle. The left end of the test spindle is provided with a spindle inlet channel and a spindle outlet nozzle. The spindle inlet channel is a blind hole located at the center of the left end of the test spindle. The spindle outlet nozzle is located on the right side of the test bearing and extends radially along the test spindle. One end is connected to the spindle inlet channel, and the other end is connected to the outside of the test spindle. The inner ring cover of the test bearing is provided with a spindle inlet port that is connected to the spindle inlet channel.

[0013] Furthermore, the axial liquid inlet is a spiral auxiliary liquid inlet, which is formed by setting an inner hole in the middle of the inner ring cover of the test bearing and setting a spiral groove on the inner hole wall.

[0014] Furthermore, the test chamber shell is provided with an inlet and an outlet for the cooling medium to enter and exit. The test bearing seat divides the interior of the test chamber shell into a left test chamber and a right test chamber. A sealing ring mounting seat is provided between the test bearing seat and the left end cover of the shell. The sealing ring mounting seat divides the left test chamber into an inlet space and an outlet space. The inlet is connected to the inlet space, and the outlet is connected to the outlet space.

[0015] Furthermore, the test chamber shell located outside the test bearing housing is provided with multiple sets of horizontal and vertical intersecting flow channels, which connect the liquid inlet space of the left test chamber and the right test chamber for the passage of cooling medium.

[0016] Furthermore, the test bearing housing is installed and fixed on the test chamber shell by the left and right pressure caps of the bearing housing. A sealing ring is provided between the left pressure cap of the bearing housing and the sealing ring mounting seat. The bearing housing is provided with an axially extending flow channel hole, which connects the liquid inlet space of the left test chamber and the right test chamber.

[0017] Beneficial effects:

[0018] This invention, through its segmented design of a normal temperature lubrication section and a low temperature cooling section, allows for the replacement of only the low temperature test section components during each test, reducing material costs and processing difficulty. The normal temperature oil lubrication section can be designed with margins, increasing redundancy in speed, load, and lifespan to ensure stable operation of the low temperature test fixture under various low temperature bearing operating conditions, thereby improving the reliability, safety, and adaptability of the entire test fixture.

[0019] This invention reduces the risk of inaccurate axial loading force or even zero axial force in the test bearing due to low-temperature jamming, thus improving loading reliability. Simultaneously, the conical design of the axial loading cap and test bearing housing effectively compensates for uneven axial shrinkage caused by temperature differences, preventing off-center loading and improving loading smoothness. Furthermore, the design of the axial loading preload spring and compensating air intake avoids reverse axial force on the piston caused by the liquid nitrogen pressure in the low-temperature test chamber, improving the accuracy of the axial force loading on the test bearing.

[0020] This invention improves the cooling conditions of the inner ring of the test bearing by using a spiral auxiliary liquid inlet in the inner ring cap design, along with the liquid inlet channel and liquid outlet nozzle in the test shaft. This effectively reduces the temperature of the inner ring and prevents burn-out of the bearing inner ring due to insufficient cooling capacity under high-speed operating conditions. The low-temperature test chamber of this invention features cross-flow channels on the shell, allowing the cooling medium to cool the shell and ensure a low-temperature environment throughout the test chamber. Flow channel holes are provided on the test bearing seat, through which the cooling medium flows to the test bearing, achieving sufficient cooling of the outer ring. These designs enable the cooling medium to circulate fully within the test chamber, achieving high cooling effects on both the outer and inner rings of the test bearing, while also improving cooling efficiency, reducing cooling medium consumption, and lowering test costs.

[0021] The bearing cryogenic medium simulation test device of the present invention can not only be applied to aerospace turbopump bearings, but also can be widely used in the cryogenic bearing testing industry, effectively reducing test costs and difficulties and improving test efficiency. Attached Figure Description

[0022] Figure 1 This is a schematic cross-sectional view of the experimental device of the present invention;

[0023] Figure 2 This is a schematic diagram of the experimental shaft system of the present invention;

[0024] Figure 3 This is a schematic diagram of the axial guide linear bearing of the present invention. (wherein, Figure 3 (a) is Figure 3 (b) NN-direction cross-sectional schematic diagram);

[0025] Figure 4 This is a schematic diagram of the axially loaded pressure cap structure, (wherein, Figure 4 (a) is Figure 4 (b) Right view diagram);

[0026] Figure 5 yes Figure 1 A partial structural diagram at point A in the middle;

[0027] Figure 6 yes Figure 1 A schematic diagram of the local structure at point B.

[0028] Figure reference numerals: 01 Coupling, 02 Inner ring cover of test bearing, 03 Right side end cover of housing, 04 Test chamber housing, 05 Axial positioning bearing, 06 Stepped spacer of test bearing, 07 Outer ring cover of radial loading bearing, 08 Outer ring spacer of radial loading bearing, 09 Radial loading bearing, 10 Radial loading piston, 11 Radial bearing carrier of test bearing, 12 Gas seal cover of test bearing, 13 Central sealing baffle, 14 Sealing carbon ring, 15 Right side cover of bearing housing, 16 Test chamber housing, 17 Test bearing housing, 18 Left side cover of bearing housing, 19 Liquid inlet, 2 0 Left side housing end cap, 21 Sealing ring mounting seat, 22 Axial piston sealing ring baffle, 23 Axial piston mounting seat, 24 Axial loading piston, 241 Retaining ring, 242 Compensating air inlet, 243 Air outlet, 25 Preload spring, 26 Liquid outlet, 27 Axial loading gland, 28 Axial guide linear bearing, 281 Ball bearing, 282 Ball cage, 283 Ball groove, 284 Rectangular groove, 29 Test bearing, 30 Test spindle, 31 Test bearing inner ring gland, 32 Shaft inlet liquid channel, 33 Shaft outlet liquid nozzle, 34 Spiral auxiliary liquid inlet. Detailed Implementation

[0029] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that in the present invention, the terms "upper", "lower", "front", "rear", "left", "right", "inner", "outer", etc., indicate the orientation or positional relationship based on the relative orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the present invention and do not indicate or imply that the device or element referred to must have a specific orientation.

[0030] like Figure 1 As shown, this invention provides a cryogenic medium simulation test device for aerospace turbopump bearings. The device includes a test spindle 30, a test bearing 29, a companion bearing, a radial loading piston 10, and an axial loading piston 24. The test bearing 29 is a cryogenic bearing; in this embodiment, it is an aerospace turbopump bearing. The companion bearings include a radial loading bearing 09 and an axial positioning bearing 05. Each bearing is positioned and mounted on the test spindle 30 to form a test shaft system. The test shaft system is divided into a cryogenic cooling section and a normal temperature lubrication section. The test bearing 29 is located in the cryogenic cooling section. An external test chamber housing 16 is provided to form a low-temperature test chamber. The test bearing is located in the normal temperature lubrication section. An external test chamber housing 04 is provided outside the normal temperature lubrication section to form a normal temperature lubrication chamber. The test chamber housing 16 and the test chamber housing 04 are sealed and isolated by a sealing assembly. The test chamber housing 16 is provided with a cooling medium inlet 19 and an outlet 26. The cooling medium enters the low-temperature test chamber through the inlet 19, circulates in the low-temperature test chamber, and is discharged through the outlet 26. The normal temperature test chamber housing 16 is provided with an oil supply port and an oil return port for normal temperature lubrication of the normal temperature lubrication section.

[0031] based on Figure 1-2 As shown, on the test shaft system, the test bearing 29 is installed at the left end of the test spindle 30, located in the low-temperature cooling section. A test bearing seat 17 is provided outside the test bearing 29, and the test bearing seat 17 is fixedly connected to the test chamber housing 16. The left end of the test bearing 29 is provided with a test bearing inner ring cover 31 and an axial loading cover 27. The axial loading piston 24 applies axial load to the test bearing 29 through the axial loading cover 27. The right side of the test bearing 29 is positioned by a shaft shoulder. A companion bearing is installed at the right end of the test spindle 30, located in the normal temperature lubrication section. The companion bearing includes a radial loading bearing 09 and an axial positioning bearing 05. The radial loading bearing 09 is located to the left of the axial positioning bearing 05. The radial loading bearing 09 includes a pair of bearings separated by an inner ring spacer and a radial loading bearing outer ring spacer 08. A test bearing radial support body 11 is provided on the outside of the loading bearing 09. The radial loading piston 10 loads the radial loading bearing 09 through the test bearing radial support body 11. The left side of the radial loading bearing 09 is positioned by a step on the test spindle 30. The right side is provided with a test bearing step spacer 06 and a radial loading bearing outer ring cover 07. The right side of the test bearing step spacer 06 is an axial positioning bearing 05. The outer ring of the axial positioning bearing 05 mates with the test chamber housing 04. The right side of the axial positioning bearing 05 is provided with a test bearing inner ring cover 02 and a right housing end cover 03. The right housing end cover 03 is fixed to the test chamber housing 04 with screws and is sealed with the test bearing inner ring cover 02 by threads. The right housing end cover 03 is also provided with an oil supply port and an oil supply channel. A coupling 01 is connected to the right side of the test spindle 30.

[0032] like Figure 1 and 5 As shown, the left end of the test chamber housing 16 is provided with a left housing end cover 20. The axial loading piston 24 is mounted on the left housing end cover 20 through an axial piston mounting seat 23. The axial piston mounting seat 23 is located outside the left housing end cover 20. There are two sealing rings between the axial loading piston 24 and the left housing end cover 20. An axial piston sealing ring baffle 22 is provided on the inner side of the left housing end cover 20. The right side of the axial loading piston 24 is pressed against the axial loading cover 27. The axial loading piston 24 is provided with a retaining ring 241. The retaining ring 241 divides the interior of the axial piston mounting seat 23 into two chambers, left and right. The left chamber is provided with a preload spring 25 and has a compensation air inlet 242. The right chamber is provided with an air outlet 243. The preload spring 25 provides a certain axial thrust to the piston rod. During axial loading, air can also be injected into the left chamber through the compensation air inlet 242 to compensate for the reverse thrust of the liquid nitrogen pressure in the low temperature test chamber on the axial loading piston 24, improve the accuracy of the axial loading force of the test bearing 29, and improve the test stability.

[0033] like Figure 1 As shown, the test bearing 29 is mounted inside the test chamber housing 16 via the test bearing seat 17. The left and right ends of the test bearing seat 17 are respectively provided with a left bearing seat cover 18 and a right bearing seat cover 15. The left bearing seat cover 18 and the right bearing seat cover 15 are respectively connected to the test chamber housing 16 by screws, thereby fixing the test bearing seat 17 on the test chamber housing 16. The axial loading cover 27 is located inside the test bearing seat 17. The right end of the axial loading cover 27 contacts the outer ring of the test bearing 29 and is used to transmit axial loading force. An axial guide linear bearing 28 is provided between the axial loading cover 27 and the test bearing seat 17.

[0034] like Figure 3-4 As shown, the axially guided linear bearing 28 includes balls 281 and a ball cage 282. The balls 281 are distributed axially, and the ball cage 282 is used to limit the distribution of the balls 281. The axial loading cover 27 and the test bearing housing 17 are provided with corresponding ball grooves 283. The balls 281 are installed and held in the ball grooves 283 by the ball cage 282, which can guide the axial loading and prevent the axial loading cover 27 from rotating during operation. It also prevents the outer ring of the test bearing 29 from rotating. Figure 3 In the embodiment shown, a total of 8 axial guide linear bearings 28 are designed between the axial loading cover 27 and the test bearing seat 17, and the 8 axial guide linear bearings 28 are evenly distributed along the circumferential direction.

[0035] Furthermore, the inner side of the test bearing housing 17 and the outer side of the axial loading cover 27 are designed as parallel conical surfaces, with the left side being larger than the right side. The specific conical angle is set according to actual needs to prevent uneven loading or jamming caused by uneven bearing housing temperature. In this embodiment, the conical angle is 1°. Specifically, during the test, due to the high-speed rotation and increased temperature of the test bearing 29, the temperature of the test bearing housing 17 near the test bearing 29 is higher than that of the axial loading side. This causes the shrinkage of the test bearing housing 17 and the axial loading cover 27 to differ along the axial direction. If it were a conventionally designed cylindrical surface, the shrinkage of the inner hole of the test bearing housing 17 would differ along the axial direction, with a larger shrinkage near the axial loading piston 24 and a smaller shrinkage near the test bearing 29. This would cause the axial loading cover 27 to tilt, ultimately resulting in an unbalanced axial load. By designing the mating surface of the two as a conical surface, this invention can compensate for the different shrinkage on the left and right sides of the axial loading cover 27, ensuring that the axial loading cover 27 and the shaft centerline maintain good coaxiality within the normal temperature difference range of the test chamber, thus avoiding the occurrence of unbalanced load.

[0036] In addition, such as Figure 4As shown, multiple rectangular grooves 284 are evenly distributed circumferentially on the end face of the axial loading cover 27 that contacts the outer ring of the test bearing 29. During loading, the presence of these rectangular grooves 284 can increase the friction between the axial loading cover 27 and the outer ring of the test bearing 29, thus preventing the outer ring of the bearing from rotating and causing a running ring failure.

[0037] As shown in Figure 1, within the low-temperature test chamber, the test bearing housing 17 divides the interior of the low-temperature test chamber into a left test chamber and a right test chamber. A sealing ring mounting seat 21 is provided between the left pressure cap 18 of the bearing housing and the left housing end cap 20. The sealing ring mounting seat 21 divides the left test chamber into a liquid inlet space and a liquid outlet space. Specifically, the left side of the sealing ring mounting seat 21 is connected to the left housing end cap 20 by screws, and the right side is sealed to the left pressure cap 18 of the bearing housing by a sealing ring. The sealing ring mounting seat 21 has an opening in the middle for an axially loaded piston. 24 passes through the opening and abuts against the axial loading cover 27. The liquid outlet 26 is located on the left end cover 20 of the housing and communicates with the liquid outlet space inside the sealing ring mounting seat 21. The liquid inlet 19 is located on the left end face of the test chamber housing 16 and communicates with the liquid inlet space outside the sealing ring mounting seat 21. The sealing ring mounting seat 21 divides the liquid inlet 19 and the liquid outlet 26 into different areas, so that the cooling medium entering through the liquid inlet 19 will not flow directly to the liquid outlet 26, but will flow out from the liquid outlet 26 after being cooled, flowed and circulated in the test chamber.

[0038] Multiple liquid inlets 19 and liquid outlets 26 are provided and are evenly distributed along the circumference. The circumference of the liquid outlet 26 is located inside the circumference of the liquid inlet 19. In a specific embodiment, there are three liquid inlets 19 and three liquid outlets 26.

[0039] The test chamber shell 16 is a thick-walled shell with multiple sets of horizontal and vertical intersecting flow channels. The cooling medium flows in the flow channels, which can reduce the temperature of the test chamber shell 16. In addition, the thick-walled design can form a good heat preservation effect for the entire test chamber. The flow channels on the test chamber shell 16 correspond to the liquid inlet 19 and are provided in three sets.

[0040] The flow channel on the test chamber housing 16 connects the left and right test chambers. Simultaneously, the test bearing housing 17 has multiple axially extending flow channel holes. The left and right pressure caps 18 and 15 of the bearing housing also have corresponding through holes. Cooling medium enters the left test chamber through the inlet 19. A portion flows through the flow channel on the test chamber housing 16 into the right test chamber, cooling the test chamber housing 16 and ensuring a low-temperature environment inside. Another portion flows through the flow channel holes on the test bearing housing 17 into the right test chamber, cooling the test bearing housing 17 and the outer ring of the test bearing 29. The cooling medium in the right test chamber enters the internal space of the axial loading pressure cap 27 via the test bearing 29, immersing the test bearing 29 entirely in the low-temperature medium. The left end face of the axial loading pressure cap 27 has a through hole. The cooling medium passes through the through holes on the axial loading pressure cap 27 and the sealing ring mounting seat 21, enters the sealing ring mounting seat 21, and finally flows out from the outlet 26. The cooling medium achieves a large circulation within the test chamber.

[0041] like Figure 1 and Figure 6 As shown, further, to improve the cooling effect at the shaft center, the present invention provides a shaft center liquid inlet channel 32 and a shaft center liquid outlet nozzle 33 at the left end of the test spindle 30, facilitating the entry of the cooling medium into the shaft center to cool the inner ring of the test bearing 29. The shaft center liquid inlet channel 32 is a blind hole located at the left end of the test spindle 30. The shaft center liquid outlet nozzle 33 is located on the right side of the test bearing 29, extending radially along the test spindle 30, with one end connected to the shaft center liquid inlet channel 32 and the other end connected to the right test chamber on the right side of the test bearing 29. To improve the fluidity of the cooling medium, a connection is provided in the middle of the inner ring cap 31 of the test bearing, which is connected to the shaft center. The spiral auxiliary inlet 34, which is connected to the liquid inlet channel 32, is formed by setting an inner hole on the inner ring cover 31 of the test bearing and setting a spiral groove on the inner hole wall. The spiral auxiliary inlet 34 plays a guiding role during the test, which can drive the cooling medium into the shaft liquid inlet channel 32 in a flowing state, thereby improving the fluidity of the cooling medium. The cooling medium entering the shaft liquid inlet channel 32 flows out from the shaft liquid outlet nozzle 33 to the right test chamber on the right side of the test bearing 29, forming a small circulation at the inner ring of the test bearing 29, effectively reducing the temperature of the inner ring of the bearing and preventing the bearing inner ring burn-out failure caused by insufficient cooling capacity under high-speed operating conditions.

[0042] The experimental apparatus designed in this invention features a highly fluid and efficient cooling medium within the test chamber. The thick-walled design and flow channel design of the test chamber shell 16 enhance the insulation effect, ensuring a low-temperature environment throughout the test chamber. The design of the flow channel holes on the test bearing seat 17 and the axial flow channel holes on the test spindle 30 allows the cooling medium to effectively cool the outer and inner rings of the test bearing 29. The cooling medium forms both large and small circulation loops within the test chamber, resulting in high cooling efficiency and ensuring sufficient cooling effect. This guarantees the safety of the test under high-speed rotation while simultaneously improving the utilization rate of the cooling medium and reducing its consumption.

[0043] The test chamber housing 16 and the auxiliary test chamber housing 04 of the present invention are sealed and isolated by a sealing assembly. The sealing assembly includes a central sealing baffle 13, a sealing carbon ring 14, and an airtight pressure cap 12. The auxiliary test chamber housing 04 and the test chamber housing 16 are connected by screws. The central sealing baffle 13 is fixed to the right end of the test chamber housing 16 by screws, and a sealing ring is installed on the contact surface between the two. The central sealing baffle 13 is located between the test chamber housing 16 and the auxiliary test chamber housing 04, and can isolate the test chamber housing 16 and the auxiliary test chamber housing 04. The internal cavity of 04 is isolated, and the central sealing baffle 13 has an inner hole. Multiple sealing carbon rings 14 are installed between the inner hole of the central sealing baffle 13 and the outer diameter of the test spindle 30. The gas-tight pressure cover 12 is located inside the test chamber shell 04 and is installed on the test spindle 30 on the left side of the test bearing. The gas-tight pressure cover 12 can introduce compressed air to form an air film at the gap to seal the gap on the test spindle 30, thereby achieving a sealing effect and preventing the medium in the two cavities from communicating. The sealing component used in this invention has a simple structure and a good sealing effect.

[0044] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present invention. Any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention without departing from the scope of the present invention shall still fall within the scope of the present invention.

Claims

1. A cryogenic medium simulation test apparatus for aerospace turbopump bearings, comprising a test spindle, a test bearing, a test auxiliary bearing, a radial loading piston, and an axial loading piston, wherein the test auxiliary bearing includes a radial loading bearing and an axial positioning bearing, and the test bearing and the test auxiliary bearing are positioned and mounted on the test spindle to form a test shaft system, characterized in that, The test shaft system is divided into a low-temperature cooling section and a normal-temperature lubrication section. The test bearing is located in the low-temperature cooling section, which is surrounded by a test chamber shell. The auxiliary bearing is located in the normal-temperature lubrication section, which is surrounded by a auxiliary chamber shell. The test chamber shell and the auxiliary chamber shell are sealed and isolated by a sealing assembly. The test bearing is installed in a test bearing housing. An axial loading cover is located on the left side of the outer ring of the test bearing. Multiple axial guide linear bearings are evenly distributed circumferentially between the axial loading cover and the test bearing housing. Each axial guide linear bearing includes balls and a ball cage. The ball cage can distribute and limit the balls. Corresponding ball grooves are provided between the axial loading cover and the test bearing housing. The balls are installed and held in the ball grooves by the ball cage. The inner side of the test bearing housing and the outer side of the axial loading cover are designed as parallel conical surfaces, with the left side larger than the right side. The angle of the conical surface is set according to actual needs. The axial loading piston loads the test bearing through the axial loading cover. The axial loading piston is equipped with a preload spring and a compensating air intake structure. The test bearing is installed at the left end of the test spindle. The test bearing housing divides the interior of the test chamber into a left test chamber and a right test chamber. The left end of the test spindle is provided with a spindle inlet channel and a spindle outlet nozzle. The spindle inlet channel is a blind hole located at the center of the left end of the test spindle. The spindle outlet nozzle is located on the right side of the test bearing and extends radially along the test spindle. One end is connected to the spindle inlet channel, and the other end is connected to the right test chamber. The left side of the test bearing is provided with a test bearing inner ring cover. The test bearing inner ring cover is fixed to the end face of the test spindle. The middle of the test bearing inner ring cover is provided with a spindle inlet port that communicates with the spindle inlet channel. The spindle inlet port is a spiral auxiliary inlet port, which is formed by setting an inner hole in the middle of the test bearing inner ring cover and setting a spiral groove on the inner hole wall.

2. The cryogenic medium simulation test device for aerospace turbopump bearings according to claim 1, characterized in that, Multiple rectangular grooves are evenly distributed circumferentially on the end face of the axial loading gland that contacts the outer ring of the test bearing to increase the friction between the axial loading gland and the outer ring of the test bearing.

3. The cryogenic medium simulation test device for aerospace turbopump bearings according to claim 1, characterized in that, The axial loading piston is mounted on the left end cover of the test chamber housing via an axial piston mounting seat. The axial loading piston is equipped with a retaining ring, which divides the axial piston mounting seat into a left chamber and a right chamber. The left chamber is equipped with a preload spring and has a compensation air inlet, while the right chamber is equipped with an air outlet.

4. The cryogenic medium simulation test device for aerospace turbopump bearings according to claim 1, characterized in that, The test chamber shell is provided with an inlet and an outlet for the cooling medium to enter and exit. A sealing ring mounting seat is provided between the test bearing seat and the left end cover of the shell. The sealing ring mounting seat divides the left test chamber into an inlet space and an outlet space. The inlet is connected to the inlet space and the outlet is connected to the outlet space.

5. The cryogenic medium simulation test device for aerospace turbopump bearings according to claim 4, characterized in that, The test chamber shell located outside the test bearing housing is provided with multiple sets of horizontal and vertical intersecting flow channels. These flow channels connect the liquid inlet space of the left test chamber and the right test chamber, allowing the cooling medium to pass through.

6. The cryogenic medium simulation test device for aerospace turbopump bearings according to claim 4, characterized in that, The test bearing housing is fixed to the test chamber shell by the left and right pressure caps of the bearing housing. A sealing ring is provided between the left pressure cap of the bearing housing and the sealing ring mounting seat. The bearing housing is provided with an axially extending flow channel hole, which connects the liquid inlet space of the left test chamber and the right test chamber.

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