CN112502859B - High-speed dynamic sealing element test device for rocket engine - Google Patents

High-speed dynamic sealing element test device for rocket engine Download PDF

Info

Publication number
CN112502859B
CN112502859B CN202011073170.4A CN202011073170A CN112502859B CN 112502859 B CN112502859 B CN 112502859B CN 202011073170 A CN202011073170 A CN 202011073170A CN 112502859 B CN112502859 B CN 112502859B
Authority
CN
China
Prior art keywords
sealing
seal
shell
rotating shaft
ring
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN202011073170.4A
Other languages
Chinese (zh)
Other versions
CN112502859A (en
Inventor
杨军
张小平
张树强
郑国真
李勇
姜圣杰
赵玉龙
任荣波
周小义
张士强
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Lanjian Spaceflight Technology Co ltd
Original Assignee
Lanjian Spaceflight Technology Co ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Lanjian Spaceflight Technology Co ltd filed Critical Lanjian Spaceflight Technology Co ltd
Priority to CN202011073170.4A priority Critical patent/CN112502859B/en
Publication of CN112502859A publication Critical patent/CN112502859A/en
Application granted granted Critical
Publication of CN112502859B publication Critical patent/CN112502859B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/96Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04BPOSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B51/00Testing machines, pumps, or pumping installations
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M3/00Investigating fluid-tightness of structures
    • G01M3/02Investigating fluid-tightness of structures by using fluid or vacuum
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16JPISTONS; CYLINDERS; SEALINGS
    • F16J15/00Sealings
    • F16J15/16Sealings between relatively-moving surfaces

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

The invention provides a high-speed dynamic sealing element test device for a rocket engine, which comprises the following components: the device comprises a main shell, an isolation shell, a sealing shell, an end cover, a testing assembly, a rotating shaft and a sealing structure. The rotating shaft penetrates through the interior of the main shell and is mounted on the main shell through a bearing. The both sides of main casing body are fixed mounting respectively have and keep apart casing and sealed casing. The test assembly is arranged on the sealing shell and the rotating shaft. The end cover is fixedly arranged on the sealing shell and used for sealing the sealing shell. The pivot passes and keeps apart the casing, and seal structure is used for keeping apart casing and pivot and sealing. The test device is good in compatibility, can test various dynamic sealing elements, and is convenient to disassemble and assemble. In addition, the test of normal temperature and low temperature environment can be realized, the requirements of different test environments are met, the real use environment is simulated to the maximum extent, the use range is wide, and the utilization rate is high.

Description

High-speed dynamic sealing element test device for rocket engine
Technical Field
The invention relates to the technical field of high-speed dynamic sealing of rocket engines, in particular to a test device for a high-speed dynamic sealing element, and specifically relates to a test device for the high-speed dynamic sealing element for the rocket engine.
Background
The high-speed dynamic sealing element plays an important role in a rocket engine, and the high-speed dynamic sealing element is required to be used at a plurality of places, wherein the high-speed dynamic sealing element comprises a turbine end face seal, an end face seal between two pumps, a floating ring seal, an oxidant pump end face seal, a fuel pump section seal and the like. According to the use condition, whether the sealing performance, the sealing effect and the like of the sealing element meet the design requirements or not is required to be examined, and the sealing performance of the dynamic sealing element is related to the working pressure, the temperature, the rotating speed and other factors. The prior art also has a device for testing the sealing element, but the test object of the prior test device is often single and can not test various sealing elements. This causes some inconvenience to the test. When various sealing elements need to be tested, various testing devices are often needed, which not only wastes testing time, but also greatly reduces testing efficiency. And the test temperature of the existing test device is single, and two test environments of normal temperature and low temperature cannot be provided.
Patent CN108708802A discloses a low-temperature high-speed end face seal test device for a liquid rocket engine turbine pump. The device is applied to the spot inspection test, the running-in test and the research test of the rocket engine end face sealing assembly of the liquid hydrogen liquid oxygen propellant, the end face sealing assembly product is assembled into the testing device, and the working environment of the engine turbo pump is simulated. This device has the following disadvantages: firstly, when a sealed product is tested, the compatibility of a testing device is poor, and the test of various sealing elements cannot be realized; secondly, the sealing test under two different working conditions of normal temperature and low temperature cannot be carried out; thirdly, the utilization ratio of the test device is low, and the disassembly and the assembly are inconvenient.
Therefore, a dynamic seal testing device with good compatibility, capability of realizing tests in normal temperature and low temperature environments, convenience in mounting of testing components and high device utilization rate is urgently needed by the technical personnel in the field.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a high-speed dynamic sealing element testing device for a rocket engine. The testing device is good in compatibility, can test various dynamic sealing elements, is convenient to disassemble and assemble, can realize tests in normal temperature and low temperature environments, and is wide in application range and high in utilization rate.
The invention provides a high-speed dynamic sealing element test device for a rocket engine, which comprises the following components: the testing device comprises a main shell, an isolation shell, a sealing shell, an end cover, a testing assembly, a rotating shaft and a sealing structure, wherein the rotating shaft penetrates through the interior of the main shell and is mounted on the main shell through a bearing; the isolation shell and the sealing shell are fixedly mounted on two sides of the main shell respectively; the testing assembly is arranged on the sealing shell and the rotating shaft; the end cover is fixedly arranged on the sealing shell and used for closing the sealing shell; the rotating shaft penetrates through the isolating shell, and the sealing structure is used for sealing the isolating shell and the rotating shaft; the sealing structure comprises a liquid sealing wheel, and the liquid sealing wheel is fixed on the rotating shaft and used for sealing and fixing the position of the bearing.
In an embodiment of the present invention, the test assembly comprises: the sealing device comprises a movable ring sealing element and a static ring sealing element, wherein the movable ring sealing element is arranged at the rear end of the rotating shaft and is fixed in position through a shaft end gland fixed at the rear end part of the rotating shaft and a sealing shaft sleeve between the movable ring sealing element and the rotating shaft; the static ring sealing element is fixed on the sealing shell through a static ring gland, and the dynamic ring sealing element is in contact with the static ring sealing element; and a sealing ring is further arranged on the inner ring of the sealing shaft sleeve and used for sealing between the sealing shaft sleeve and the rotating shaft.
In an embodiment of the present invention, the test assembly includes a stationary ring seal fixed to the seal housing by a stationary ring gland, and the stationary ring seal is in transition fit with a seal sleeve fixed to the rotating shaft.
In an embodiment of the present invention, the sealing structure further includes: the sealing part is positioned at the opening of the isolation shell and used for sealing a gap between the isolation shell and the rotating shaft; and the leather cup sealing part is positioned between the liquid sealing wheel and the air sealing part and is used for sealing a gap between the isolation shell and the rotating shaft.
Further, the packing cup sealing portion includes: the leather cup and the pressing ring are made of flexible materials and are arranged in a sealing groove in the inner ring of the isolation shell, and the clamping ring is clamped in the sealing groove and used for limiting the positions of the leather cup and the pressing ring; the leather cup is in interference fit with the rotating shaft.
Further, the air sealing part comprises a plurality of annular grooves on the inner diameter of the isolation shell and an air supply hole communicated with the middles of the annular grooves; the air supply hole air feed, it is a plurality of that gas gets into one by one the ring channel form the malleation in the ring channel for prevent that the medium from getting into the ring channel.
In an embodiment of the invention, one end of the liquid seal wheel is in contact with the bearing, the other end of the liquid seal wheel is in clearance fit with the isolation shell, and the end face of the liquid seal wheel in clearance fit with the isolation shell is provided with a plurality of sealing edges for throwing a medium out of the clearance during rotation.
In the embodiment of the invention, the bearings on the rotating shaft are fixed in position through shaft sleeves; the bearing at the rear end of the rotating shaft is fixed in position through a bearing gland; and the bearing positioned at the front end of the rotating shaft is fixed in position through the liquid seal wheel.
Further, the bearing gland is provided with a sealing groove, a leather cup made of flexible materials is installed in the sealing groove, the leather cup is fixed in position through a clamping ring, and the leather cup is in interference fit with the rotating shaft and is used for sealing the bearing gland and the rotating shaft.
In an embodiment of the invention, an annular sealing gasket is arranged on a contact surface of the main shell and the isolation shell and used for sealing the contact surface; the annular sealing gasket is arranged on the contact surface of the main shell and the sealing shell and used for sealing the contact surface; and the contact surface of the sealing shell and the end cover is provided with the annular sealing gasket for sealing the contact surface.
According to the above embodiment, the high-speed dynamic seal testing device for the rocket engine provided by the invention has the following advantages: the test device is good in compatibility, can test various dynamic sealing elements, and is convenient to disassemble and assemble. The test assembly is disassembled by disassembling the sealing shell, and the corresponding sealing shell is installed according to the test assembly, so that the whole disassembly and assembly process is simple, the disassembly and assembly are convenient, the test state can be quickly entered, and the equipment and time for testing are greatly saved. In addition, the test device can realize tests in normal temperature and low temperature environments, and test assemblies in different working environments are conveniently tested. The utilization rate of the device is improved. Compared with the existing design, the test device is more reasonable in structure, good in sealing effect and more accurate in test.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description, serve to explain the principles of the invention.
Fig. 1 is a cross-sectional view of a first embodiment of a high-speed dynamic seal testing device for a rocket engine provided by the invention.
Fig. 2 is a left side view of a first embodiment of a high-speed dynamic seal testing device for a rocket engine provided by the invention.
Fig. 3 is a right side view of a first embodiment of a high-speed dynamic seal testing device for a rocket engine provided by the invention.
Fig. 4 is a sectional view of a second embodiment of a high-speed dynamic seal testing apparatus for a rocket engine according to the present invention.
Fig. 5 is a sectional view of a third embodiment of a high-speed dynamic seal testing apparatus for a rocket engine according to the present invention.
Fig. 6 is a sectional view of a fourth embodiment of the high-speed dynamic seal testing apparatus for a rocket engine according to the present invention.
Fig. 7 is a left side view of a fourth embodiment of the high-speed dynamic seal testing apparatus for a rocket engine according to the present invention.
Fig. 8 is a right side view of a fourth embodiment of the high-speed dynamic seal testing apparatus for a rocket engine according to the present invention.
Fig. 9 is a cross-sectional view of a fifth embodiment of a high-speed dynamic seal testing apparatus for a rocket engine according to the present invention.
Fig. 10 is a sectional view of a sixth embodiment of a high-speed dynamic seal testing apparatus for a rocket engine according to the present invention.
Fig. 11 is a front view of a liquid seal wheel of a high-speed dynamic seal testing device for a rocket engine provided by the invention.
Fig. 12 is a test flowchart of a high-speed dynamic seal testing device for a rocket engine according to the present invention.
Description of reference numerals:
1-main shell, 2-isolation shell, 3-sealing shell, 4-end cover, 5-testing component, 6-rotating shaft, 7-bearing, 8-sealing structure, 9-moving ring sealing element, 10-static ring sealing element, 11-sealing shaft sleeve, 12-sealing ring, 13-shaft end gland, 14-static ring gland, 15-liquid sealing wheel, 16-leather cup sealing part, 17-air sealing part, 18-snap ring, 19-leather cup, 20-press ring, 21-annular groove, 22-air supply hole, 23-sealing edge, 24-shaft sleeve, 25-bearing gland, 26-annular sealing gasket, 27-graphite ring, 28-medium inlet, 29-medium outlet, 30-medium pressure measuring port, 31-bearing temperature detecting port, 32-a leakage amount detection port, 33-a leakage pressure measurement port, 34-a leakage temperature measurement port, 35-a medium temperature measurement port, 36-a medium discharge port and 37-an adjusting pad.
Detailed Description
Reference will now be made in detail to various exemplary embodiments of the invention, the detailed description should not be construed as limiting the invention but as a more detailed description of certain aspects, features and embodiments of the invention.
It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the present disclosure without departing from the scope or spirit of the disclosure. Other embodiments will be apparent to those skilled in the art from consideration of the specification. The specification and examples are exemplary only.
The invention provides a high-speed dynamic sealing element test device for a rocket engine, which comprises the following components: the device comprises a main shell 1, an isolation shell 2, a sealing shell 3, an end cover 4, a testing component 5, a rotating shaft 6 and a sealing structure 8.
As shown in fig. 6, the rotating shaft 6 passes through the inside of the main housing 1, and is fixedly mounted in an internal mounting hole of the main housing 1 through a bearing 7, and two ends of the rotating shaft 6 extend out of the mounting hole. The front end of the rotating shaft 6 is provided with a spline for connecting an external driving motor. The rear end of the rotating shaft 6 is connected with the testing component 5 and used for carrying out dynamic seal testing when the rotating shaft 6 rotates. Preferably, the rotating shaft 6 is made of 9Cr18, dynamic balance is required during processing, the dynamic balance rotating speed is not lower than 4000r/min, and the dynamic balance precision grade is G1 grade. The material of the main casing 1 is 2Cr 13.
The two sides of the main shell 1 are respectively fixedly provided with an isolation shell 2 and a sealing shell 3. The isolation housing 2 is located at the front end of the rotating shaft 6, and the sealing housing 3 is located at the rear end of the rotating shaft 6.
The test assembly 5 is arranged on the sealing shell 3 and the rotating shaft 6 and is positioned at the tail end of the rotating shaft 6, and a dynamic sealing test is carried out in the rotating process of the rotating shaft 6.
The end cover 4 is fixedly installed on the sealing shell 3 and used for sealing the sealing shell 3 and ensuring that the test assembly 5 performs a test in a relatively sealed environment to obtain an accurate test result.
The rotating shaft 6 penetrates through the isolation shell 2, and the sealing structure 8 is used for sealing the isolation shell 2 and the rotating shaft 6. The rotating shaft 6 penetrates through the isolation shell 2 and is used for being connected with an external driving motor to drive the rotating shaft 6 to rotate so as to provide power for a test. In order to ensure that the inside and the outside of the isolation shell 2 are isolated in the rotating process, a sealing structure 8 is required to be arranged at the contact position of the isolation shell 2 and the rotating shaft 6, so that the internal medium is ensured not to leak to the outside of the isolation shell 2, and the test result is influenced.
The sealing structure 8 comprises a liquid sealing wheel 15, and the liquid sealing wheel 15 is fixed on the rotating shaft 6 and used for sealing and fixing the position of the bearing 7. The liquid seal wheel 15 is fixedly connected with the rotating shaft 6 and rotates along with the rotating shaft 6. One end of the liquid seal wheel 15 is in contact with the bearing 7 and used for limiting the position of the bearing 7 and preventing the bearing 7 from axial displacement. The other end of the liquid seal wheel 15 is in clearance fit with the isolation shell 2. As shown in fig. 11, the end surface of the liquid seal wheel 15 which is in clearance fit with the separation casing 2 has a plurality of seal edges 23, the seal edges 23 are used for throwing the medium out of the clearance when rotating, and the medium forms a gas-liquid two-phase state at the periphery of the clearance. In addition, the medium moves outwards from the gap under the action of centrifugal force, the medium which is ready to enter the gap from the outside of the gap can be further blocked, the gap between the medium and the isolation shell 2 through the liquid seal wheel 15 is greatly reduced, and the purpose of sealing is further achieved.
The main shell 1 and the isolation shell 2 are respectively provided with a detection port and a medium inlet and a medium outlet, and the sealing shell 3 is provided with a detection port. The medium inlet and outlet are used for inputting and discharging the medium. In addition, the main housing 1 and the isolation housing 2 also have a test port for testing the test process. The sealed case 3 also has a detection port for detection.
In one embodiment of the invention, the test assembly 5 comprises: a dynamic ring seal 9 and a static ring seal 10. The movable ring sealing element 9 is mounted on the rear end of the rotating shaft 6, and is fixed in position by a shaft end gland 13 fixed on the rear end part of the rotating shaft 6 and a sealing shaft sleeve 11 between the movable ring sealing element 9 and the rotating shaft 6. The dynamic ring seal 9 and the sealing sleeve 11 also have an adjusting cushion 37 in the axial direction for position adjustment when different dynamic ring seals 9 are installed, in order to better fix the position of the dynamic ring seal 9. The static ring seal 10 is fixed on the seal housing 3 by a static ring gland 14, and the dynamic ring seal 9 is in contact with the static ring seal 10. The graphite ring 27 is arranged at the contact position between the movable ring sealing element 9 and the static ring sealing element 10, and the graphite ring 27 is soft in material, is generally used for a movable sealing structure, and can play a sealing effect to the greatest extent in the rotating process. The leakage position of the dynamic seal is the contact position between the dynamic ring seal 9 and the static ring seal 10, so the test device provided by the invention tests the leakage condition of the dynamic seal.
In addition, still be provided with sealing washer 12 on the inner ring of sealed axle sleeve 11, sealing washer 12 is used for sealing between sealed axle sleeve 11 and the pivot 6 and prevents that the medium from revealing through the clearance between sealed axle sleeve 11 and the pivot 6, influences the accuracy of experiment, reduces experimental error.
In the embodiment of the present invention, a test chamber is formed between the stationary ring seal 10 and the bearing 7 at the rear end of the rotating shaft 6. A leakage cavity is formed between the static ring sealing element 10 and the sealing shell 3. A bearing cavity is formed between the bearing 7 at the rear end of the rotating shaft 6 and the isolating shell 2.
In another embodiment of the present invention, as shown in fig. 5, the testing assembly 5 includes a stationary ring seal 10, the stationary ring seal 10 is fixed on the seal housing 3 by a stationary ring gland 14, and the stationary ring seal 10 is in transition fit with a seal sleeve 11 fixed on the rotating shaft 6. The static ring seal 10 is provided with a graphite ring 27 at the contact position with the seal shaft sleeve 11. The graphite ring 27 is fixed on the stationary ring seal 10, is soft in material, is generally used for a dynamic seal structure, and can play a sealing effect to the greatest extent in the rotating process.
In a specific embodiment of the present invention, the sealing structure 8 further includes: a cup seal 16 and an airtight seal 17. As shown in fig. 6, the air sealing portion 17 is located at the opening of the isolation housing 2, that is, at a position where the through hole of the isolation housing 2 through which the rotating shaft 6 passes is close to the outside, and the air sealing portion 17 is used for sealing the gap between the isolation housing 2 and the rotating shaft 6. The airtight sealing portion 17 includes a plurality of annular grooves 21 on the inner diameter of the insulating case 2, and a gas supply hole 22 communicating to the middle position of the plurality of annular grooves 21. The air supply holes 22 supply air, the air enters the plurality of annular grooves 21 one by one, and positive pressure is formed in the annular grooves 21 to prevent media from entering the annular grooves 21, so that the dynamic seal of the rotating shaft is realized. The air outlet of the air supply hole 22 is arranged at the middle position of the annular grooves 21 so as to lead the sealing air to spread from the middle to two sides along the axial direction, thereby achieving the sealing effect.
The cup seal 16 is located between the hydraulic seal wheel 15 and the pneumatic seal 17. The cup seal portion 16 includes: snap ring 18, cup 19 and clamping ring 20. Wherein, the leather cup 19 and the pressure ring 20 made of flexible materials are arranged in a sealing groove on the inner wall of the through hole of the isolation shell 2, and the sealing groove is an annular sealing groove. The leather cup 19 and the pressing ring 20 are arranged in the sealing groove, and the snap ring 18 is clamped in the sealing groove and used for limiting the positions of the leather cup 19 and the pressing ring 20. The compression ring 20 serves to compress one or more cups 19. The leather cup 19 is made of flexible materials, the preferable leather cup 19 is made of polytetrafluoroethylene and graphite, and a good sealing effect is achieved during low-temperature tests. Therefore, the leather cup 19 is in interference fit with the rotating shaft 6, and the optimal sealing effect is achieved.
In the embodiment of the invention, the bearings 7 on the rotating shaft 6 are fixed in position by the shaft sleeve 24. The bearing 7 at the rear end of the rotating shaft 6 is fixed in position by a bearing cover 25. The bearing 7 at the front end of the rotating shaft 6 is fixed in position by a liquid seal wheel 15.
In order to avoid excessive ingress of the medium into the bearing chamber, a seal is required between the test chamber and the bearing chamber. Therefore, the bearing gland 25 is provided with a sealing groove, the sealing groove is internally provided with the leather cup 19 made of flexible materials, the leather cup 19 is fixed in position through the snap ring 18, and the leather cup 19 is in interference fit with the rotating shaft 6 and used for sealing. The leather cup 19 is made of flexible materials, the preferable leather cup 19 is made of polytetrafluoroethylene and graphite, and a good sealing effect is achieved during a low-temperature test. Therefore, the leather cup 19 is in interference fit with the rotating shaft 6, and the optimal sealing effect is achieved.
In the embodiment of the present invention, the contact surface between the main housing 1 and the isolation housing 2 is provided with an annular sealing gasket 26 for sealing the contact surface and preventing the medium from leaking from the contact surface. The contact surface of the main housing 1 and the seal housing 3 is provided with an annular seal 26 for sealing the contact surface and preventing the medium from leaking from the contact surface. The contact surface of the seal housing 3 and the end cover 4 is provided with an annular seal 26 for sealing the contact surface and preventing the medium from leaking from the contact surface.
When the testing device is assembled, the jumping quantity of the rotating shaft 6 is required to be not more than 0.02mm, a specially designed coaxial adjusting tool is adopted, the vertical offset of the rotating shaft 6 and the end face of the isolation shell 2 is adjusted to be not more than 0.02mm, and otherwise, a shaft system needs to be adjusted or reassembled. After the assembly is finished, a clearance check is carried out on the sealing effect between the shells by using a 0.02mm thick feeler gauge.
The high-speed dynamic sealing element testing device for the rocket engine can test various dynamic sealing structures and can test at low temperature and normal temperature. Therefore, the seal housing 3 of the test apparatus is replaced according to a test for performing a different dynamic seal structure. When the test is carried out at low temperature, the test can be carried out only by replacing the test assembly and the corresponding sealing shell 3. Similarly, when the test is carried out at normal temperature, the test can be carried out only by replacing the test assembly and the corresponding sealing shell 3. When the normal temperature test is changed to the low temperature test or the low temperature test is changed to the normal temperature test, the bearing 7 needs to be replaced, and the inlet and the outlet of the detection hole and the medium need to be plugged or opened, besides the corresponding sealing shell 3 is replaced according to the replaced test component 5. The whole test process is convenient to disassemble and assemble, the types of tests are rich, and the test cost can be greatly saved.
The embodiment shown in fig. 6 was tested in a cryogenic environment for turbine end face sealing, and in this example the medium was liquid nitrogen to provide a cryogenic environment for the test. As shown in fig. 8, a media inlet 28 is located on the main housing 1 and communicates with the test chamber for providing media to the test chamber. A medium outlet 29 is located at the other end of the main housing 1, i.e. the front end of the main housing 1, communicating with the bearing chamber for discharging the medium. Further, the main casing 1 has a medium pressure measuring port 30 and a bearing temperature detecting port 31. The medium pressure measuring port 30 is communicated with the test cavity and used for measuring the pressure of the test cavity after being filled with the medium. The bearing temperature detection port 31 is used for measuring the temperature condition of the bearing in the test cavity. The sealing housing 3 has a leakage detecting port 32 for detecting the leakage of the testing component 5 during operation, so as to obtain the sealing effect of the sealing component 5. The end cover 4 is further provided with a leakage pressure measuring port 33 and a leakage temperature measuring port 34, the leakage pressure measuring port 33 is used for detecting the pressure in the leakage cavity, and the leakage temperature measuring port 34 is used for detecting the temperature in the leakage cavity.
As shown in fig. 7, the front end of the main casing 1 further has a bearing temperature detection port 31 and a medium temperature measurement port 35. The bearing temperature detection port 31 is used for measuring the temperature condition of the bearing in the bearing cavity. The medium temperature measuring port 35 is used for detecting the temperature of the medium in the bearing cavity. The isolation shell 2 is also provided with a medium outlet 36, and the medium outlet 36 is communicated between the cup sealing part 16 and the air sealing part 17 and is used for discharging the medium leaked between the cup sealing part 16 and the air sealing part 17.
All inlet and outlet pipelines and sensor connection modes on the testing device provided by the invention are connected in a 60-degree and 37-degree horn-mouth ball-head sealing mode. Wherein, for reducing filler neck dismouting number of times, specially will fill the whole welding of mouth on each casing that corresponds, can effectively avoid filling many times dismouting of mouth to damage the screw thread. In addition, during low-temperature test, the bearing 7 at the front end of the rotating shaft 6 adopts a deep groove ball bearing and only needs to bear radial force. The bearing 7 at the rear end of the rotating shaft 6 is a low-temperature four-point contact bearing which can bear axial force and radial force.
The embodiment shown in fig. 9 is tested in a cryogenic environment for oxidant pump end face sealing, and in this embodiment the medium is liquid nitrogen to provide a cryogenic environment for the test. In this embodiment, the media inlet and outlet and the detection port on the main housing 1, the isolation housing 2, the seal housing 3 and the end cap 4 are the same as those in the embodiment shown in fig. 6. The only difference is that the test assembly 5, seal housing 3, shaft end gland 13, stationary ring gland 14, shaft sleeve 24 and adjustment pad 37 have been replaced. The detection port in the sealed housing 3 is unchanged.
The embodiment shown in fig. 10 is used for testing the end face seal of the fuel pump in a low-temperature environment, and the medium in the embodiment is liquid nitrogen which is used for providing the low-temperature environment for the test. In this embodiment, the media inlet and outlet and the detection port on the main housing 1, the isolation housing 2, the seal housing 3 and the end cap 4 are the same as those in the embodiment shown in fig. 6. The only difference is that the test assembly 5, seal housing 3, shaft end gland 13, stationary ring gland 14, shaft sleeve 24 and adjustment pad 37 have been replaced. The detection port in the sealed housing 3 is unchanged.
The embodiment shown in fig. 1 is used for testing the end face seal of the turbine under normal temperature environment, and the medium in the embodiment is nitrogen gas used for providing normal temperature environment for the test. Compressed air may also be used as the medium in this embodiment. In this embodiment, the test assembly 5, the seal housing 3, the end cap 4, the bearing 7, the shaft sleeve 24 and the shaft end cover 13 are mainly replaced with respect to the embodiment shown in fig. 6. Wherein the bearing 7 is replaced by an angular contact ball bearing. In addition, the other side of the bearing 7 provided with the liquid seal wheel 15 is provided with a wave spring, and the wave spring is used for providing axial pretightening force for the bearing 7, so that the bearing 7 can bear axial force and radial force at the same time. Alternatively, the hydraulic seal wheel 15 may be replaced by a compression nut, which is also fixed to the rotating shaft 6 to limit the position of the bearing 7. The material of the preferred compression nut is 06Cr19Ni 10.
In this embodiment, two test assemblies 5 can be tested at the same time according to the condition of normal temperature detection. The end cap 4 has no detection holes. As shown in fig. 3, the main casing 1 has two medium outlets 29 and a bearing temperature detection port 31 on the rear end thereof, respectively. The medium outlet 29 is used for discharging the medium. The bearing temperature detection port 31 is used for detecting the temperature of the bearing in the test process. The seal housing 3 has a medium inlet 28, a medium pressure measuring port 30, and a leakage amount detecting port 32. The end cap 4 does not have a detection port. Wherein the medium inlet 28 is connected between the two test modules 5 for supplying a test medium gas. The medium pressure measuring port 30 is also communicated between the two test assemblies 5 and is used for detecting the pressure between the two test assemblies 5 in the test process.
As shown in fig. 2, only the bearing temperature detection port 31 is formed in the front end of the main housing 1 for detecting the temperature of the bearing during the test. The other openings on the main shell 1 are all in a blocking state. All openings in the insulating housing 2 are closed.
The embodiment shown in fig. 4 is used for testing the end face seal between two pumps in a normal temperature environment, and the medium in the embodiment is nitrogen gas used for providing the normal temperature environment for the test. Compressed air may also be used as the medium in this embodiment. In this embodiment, the media inlet and outlet and the detection port on the main housing 1, the isolation housing 2, the seal housing 3 and the end cap 4 are the same as those in the embodiment shown in fig. 1. The only difference is that the test assembly 5, the seal housing 3 and the shaft sleeve 24 are replaced. The detection port in the sealed housing 3 is unchanged. The sleeve 24 is also replaced according to different test assemblies 5 to meet test requirements.
The embodiment shown in fig. 5 is used for testing the floating ring seal in a normal temperature environment, and the medium in the embodiment is nitrogen gas used for providing the normal temperature environment for the test. Compressed air may also be used as the medium in this embodiment. In this embodiment, the media inlet and outlet and the detection port on the main housing 1, the isolation housing 2, the seal housing 3 and the end cap 4 are the same as those in the embodiment shown in fig. 1. The only difference is that the test assembly 5, seal housing 3, shaft end gland 13 and shaft sleeve 24 have been replaced. The detection port in the sealed housing 3 is unchanged. The sleeve 24 is also replaced according to different test assemblies 5 to meet test requirements.
As shown in fig. 12, the test device is mounted on a bracket on the sealed test platform and fastened by bolts with corresponding specifications, the coaxiality of the shaft of the test device and the high-speed shaft of the gearbox is adjusted, a coupling between the high-speed shaft of the gearbox and the main shaft of the test device is mounted and fastened by nylon ropes, and flexible connection is formed. And connecting a medium inlet and a medium outlet and a detection port which are required by the test device. And the gas distribution system blows gas off the test system, low-pressure compressed air is introduced into the test device after blowing off is finished, and leakage detection liquid is used for detecting leakage of each sealing surface of the test device. And after the leakage detection is qualified, detecting the static normal temperature gas leakage amount of the testing component 5 under the specified pressure. And after the normal-temperature gas leakage detection is finished, opening a valve of the medium inlet and a valve of the medium outlet, and filling liquid nitrogen into the test device through the process pipeline system by the medium supply system to pre-cool the test device. And simultaneously, compressed air is supplied to the air supply hole 22 for air sealing of the separation housing 2 to form a seal air. And when the temperature of the medium temperature measuring port is lower than minus 180 ℃, the static low-temperature gas leakage amount of the testing component 5 under the specified pressure is detected. When the temperature of the medium temperature measuring port is lower than-190 ℃, the driving motor can be started. The pressure of each test cavity in the test device is adjusted by pressurizing a liquid nitrogen storage tank through the gas distribution system, and then the motor is started. The variable frequency starting system controls the high-speed driving system to start and drives the test device to operate through the speed increasing system. And slowly increasing the pressure to a specified rotating speed according to test conditions, and adjusting the medium inlet flow of the test cavity on the premise of keeping the medium inlet pressure and temperature when the pressure of the test cavity reaches the working pressure. Measuring medium inlet flow, test cavity pressure, bearing outlet temperature, gear box bearing temperature, test device vibration, leakage cavity pressure, leakage cavity temperature, leakage amount, working speed, test system power and the like, judging whether the sealing performance of a sealing assembly product is qualified or not by judging a leakage amount curve, closing a motor after test time is up, detecting static low-temperature gas leakage amount of the test assembly under specified pressure, closing a medium inlet valve, and ending the test.
After the testing device recovers to normal temperature, static normal-temperature gas leakage amount detection is carried out on the sealing assembly under specified pressure, then the testing device is disassembled, the abrasion conditions of the moving ring and the static ring assembly of the engine are measured and recorded, and all measurement parameter curves are obtained. The sealing performance and structural rationality of the test assembly product are analyzed according to the test cavity pressure, temperature and leakage, and technical support and basis are provided for improving various problems in the design of the test assembly product.
The foregoing is merely an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention should fall within the protection scope of the present invention.

Claims (8)

1. A test device for a high-speed dynamic seal for a rocket engine is characterized by comprising: a main shell (1), an isolation shell (2), a sealing shell (3), an end cover (4), a testing component (5), a rotating shaft (6) and a sealing structure (8),
the rotating shaft (6) penetrates through the interior of the main shell (1) and is mounted on the main shell (1) through a bearing (7);
the two sides of the main shell (1) are respectively fixedly provided with the isolation shell (2) and the sealing shell (3);
the testing assembly (5) is arranged on the sealing shell (3) and the rotating shaft (6);
the end cover (4) is fixedly arranged on the sealing shell (3) and is used for closing the sealing shell (3);
the rotating shaft (6) penetrates through the isolating shell (2), and the sealing structure (8) is used for sealing the isolating shell (2) and the rotating shaft (6);
the sealing structure (8) comprises a liquid sealing wheel (15), and the liquid sealing wheel (15) is fixed on the rotating shaft (6) and used for sealing and fixing the position of the bearing (7);
the sealing structure (8) further comprises: a cup seal (16) and an air seal (17), wherein,
the air sealing part (17) is positioned at the opening of the isolation shell (2) and is used for sealing a gap between the isolation shell (2) and the rotating shaft (6); and
the leather cup sealing part (16) is positioned between the liquid sealing wheel (15) and the air sealing part (17) and is used for sealing a gap between the isolation shell (2) and the rotating shaft (6);
the bearing (7) positioned at the rear end of the rotating shaft (6) is fixed in position through a bearing gland (25);
bearing gland (25) are gone up and have the seal groove, leather cup (19) that the installation was made by flexible material in the seal groove, leather cup (19) carry out the rigidity through snap ring (18), leather cup (19) with be interference fit between pivot (6), be used for right bearing gland (25) with form sealedly between pivot (6).
2. A rocket engine high speed dynamic seal test device according to claim 1, characterized in that said test assembly (5) comprises: a dynamic ring seal (9) and a static ring seal (10), wherein,
the movable ring sealing element (9) is arranged at the rear end of the rotating shaft (6) and is fixed in position through a shaft end gland (13) fixed at the rear end of the rotating shaft (6) and a sealing shaft sleeve (11) between the movable ring sealing element (9) and the rotating shaft (6);
the static ring seal (10) is fixed on the seal shell (3) through a static ring gland (14), and the dynamic ring seal (9) is in contact with the static ring seal (10);
and a sealing ring (12) is further arranged on the inner ring of the sealing shaft sleeve (11) and used for sealing between the sealing shaft sleeve (11) and the rotating shaft (6).
3. A rocket engine high speed dynamic seal test device according to claim 1, wherein said test assembly (5) comprises a static ring seal (10), said static ring seal (10) is fixed on said seal housing (3) by a static ring gland (14), said static ring seal (10) is transition fitted with a seal bushing (11) fixed on said rotating shaft (6).
4. The high-speed dynamic seal testing apparatus for rocket engines according to claim 1, wherein said cup seal portion (16) comprises: a snap ring (18), a cup (19) and a press ring (20), wherein,
the leather cup (19) and the pressing ring (20) which are made of flexible materials are arranged in a sealing groove on the inner ring of the isolation shell (2), and the clamping ring (18) is clamped in the sealing groove and used for limiting the positions of the leather cup (19) and the pressing ring (20);
the leather cup (19) is in interference fit with the rotating shaft (6).
5. The test apparatus for a high-speed dynamic seal for a rocket engine according to claim 1, wherein said air-tight sealing portion (17) comprises a plurality of annular grooves (21) on the inner diameter of said insulated housing (2), and an air supply hole (22) communicating with the middle of said plurality of annular grooves (21);
the air feed hole (22) air feed, it is a plurality of that gas gets into one by one ring channel (21) form the malleation in ring channel (21) for prevent that the medium from getting into ring channel (21).
6. A high-speed dynamic seal test device for a rocket engine according to claim 1, wherein one end of the liquid seal wheel (15) is in contact with the bearing (7), the other end is in clearance fit with the isolation housing (2), and the end surface of the liquid seal wheel (15) in clearance fit with the isolation housing (2) is provided with a plurality of sealing ribs (23) for throwing the medium out of the clearance during rotation.
7. A high-speed dynamic seal test device for rocket engines according to claim 1, characterized in that the bearings (7) on the rotating shaft (6) are fixed in position by a shaft sleeve (24);
and the bearing (7) positioned at the front end of the rotating shaft (6) is fixed in position through the liquid seal wheel (15).
8. A rocket engine high speed dynamic seal test device according to claim 1, wherein the contact surface of said main casing (1) and said isolated casing (2) is provided with an annular sealing gasket (26) for sealing the contact surface;
the annular sealing gasket (26) is arranged on the contact surface of the main shell (1) and the sealing shell (3) and used for sealing the contact surface; and
the contact surface of the sealing shell (3) and the end cover (4) is provided with the annular sealing gasket (26) for sealing the contact surface.
CN202011073170.4A 2020-10-09 2020-10-09 High-speed dynamic sealing element test device for rocket engine Active CN112502859B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202011073170.4A CN112502859B (en) 2020-10-09 2020-10-09 High-speed dynamic sealing element test device for rocket engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202011073170.4A CN112502859B (en) 2020-10-09 2020-10-09 High-speed dynamic sealing element test device for rocket engine

Publications (2)

Publication Number Publication Date
CN112502859A CN112502859A (en) 2021-03-16
CN112502859B true CN112502859B (en) 2022-03-04

Family

ID=74953653

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202011073170.4A Active CN112502859B (en) 2020-10-09 2020-10-09 High-speed dynamic sealing element test device for rocket engine

Country Status (1)

Country Link
CN (1) CN112502859B (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113405735B (en) * 2021-04-30 2022-11-11 北京航天动力研究所 High-speed helium end face sealing test device for liquid rocket engine turbine pump
CN113390627B (en) * 2021-06-30 2022-11-15 四川航天烽火伺服控制技术有限公司 Pressure reducing valve centrifugal overload test device
CN115200786B (en) * 2022-07-07 2024-06-25 北京航天动力研究所 High-pressure floating ring seal test equipment for turbine pump of heavy liquid rocket engine

Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB936823A (en) * 1961-08-25 1963-09-11 Gen Motors Corp Method of and apparatus for testing a lip seal
GB1472474A (en) * 1973-05-11 1977-05-04 Chausson Usines Sa Apparatus for detecting leaks in hollow bodies
EP0609749A2 (en) * 1993-01-28 1994-08-10 Johnson Service Company Test apparatus for seal members in a pressurized oxygen environment
US6276194B1 (en) * 1999-06-01 2001-08-21 Federal-Mogul World Wide, Inc. Apparatus and method for testing the effectiveness of dynamic seals in a dust-laden operating environment
CN1354332A (en) * 2001-12-27 2002-06-19 天津新技术产业园区鼎名密封有限公司 Three-pivot seal testing device
KR20040009468A (en) * 2002-07-23 2004-01-31 현대모비스 주식회사 The apparatus for airtight test of fluid fuel rocket engine
KR20060068507A (en) * 2004-12-16 2006-06-21 한국항공우주연구원 Test device of cold flow and leak of the combustor using coaxial swirl injector
CN103630301A (en) * 2013-08-12 2014-03-12 浙江工业大学 Method for testing liquid lubrication machine seal sealing performance and devices thereof
KR20170040478A (en) * 2015-10-05 2017-04-13 한국수력원자력 주식회사 Apparatus for life evaluation test of pump mechanical seal and its method
CN107387261A (en) * 2017-08-25 2017-11-24 西安航天动力研究所 A kind of combined mechanical sealing device
CN108708802A (en) * 2018-04-19 2018-10-26 北京航天动力研究所 A kind of liquid-propellant rocket engine turbine pump low-temperature and high-speed end face seal experimental rig
CN110030381A (en) * 2019-03-12 2019-07-19 北京星际荣耀空间科技有限公司 One kind being suitable for high speed and high pressure dynamic sealing device and aircraft
CN110514357A (en) * 2019-08-12 2019-11-29 大连理工大学 A kind of ultralow temperature medium dynamic sealing experimental rig
CN111413093A (en) * 2020-03-20 2020-07-14 蓝箭航天技术有限公司 Integrated test system for cryogenic bearing and dynamic seal
CN111636981A (en) * 2020-06-12 2020-09-08 哈尔滨工业大学 Test bench for testing floating ring seal of rocket turbopump

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB823662A (en) * 1957-02-21 1959-11-18 Napier & Son Ltd Sealing assemblies and rotary fluid machines employing such assemblies
CN201771838U (en) * 2010-07-08 2011-03-23 中国航天科技集团公司第六研究院第十一研究所 Sealing structure of turbine pump
CN102128692B (en) * 2010-11-24 2012-10-24 南京林业大学 End-face-sealed friction surface temperature measuring method
CN102207418A (en) * 2011-04-06 2011-10-05 北京化工大学 Integrated test stand of high-speed high-pressure air seal for rotating shaft
CN103267613B (en) * 2013-05-06 2015-08-19 南京林业大学 A kind of mechanical sealing performance tester
CA3115274A1 (en) * 2018-10-08 2020-04-16 John Crane Uk Limited Mechanical seal with sensor
CN111502865B (en) * 2020-04-16 2021-05-04 西安航天动力研究所 Test run method of open-cycle liquid oxygen kerosene engine system

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB936823A (en) * 1961-08-25 1963-09-11 Gen Motors Corp Method of and apparatus for testing a lip seal
GB1472474A (en) * 1973-05-11 1977-05-04 Chausson Usines Sa Apparatus for detecting leaks in hollow bodies
EP0609749A2 (en) * 1993-01-28 1994-08-10 Johnson Service Company Test apparatus for seal members in a pressurized oxygen environment
US6276194B1 (en) * 1999-06-01 2001-08-21 Federal-Mogul World Wide, Inc. Apparatus and method for testing the effectiveness of dynamic seals in a dust-laden operating environment
CN1354332A (en) * 2001-12-27 2002-06-19 天津新技术产业园区鼎名密封有限公司 Three-pivot seal testing device
KR20040009468A (en) * 2002-07-23 2004-01-31 현대모비스 주식회사 The apparatus for airtight test of fluid fuel rocket engine
KR20060068507A (en) * 2004-12-16 2006-06-21 한국항공우주연구원 Test device of cold flow and leak of the combustor using coaxial swirl injector
CN103630301A (en) * 2013-08-12 2014-03-12 浙江工业大学 Method for testing liquid lubrication machine seal sealing performance and devices thereof
KR20170040478A (en) * 2015-10-05 2017-04-13 한국수력원자력 주식회사 Apparatus for life evaluation test of pump mechanical seal and its method
CN107387261A (en) * 2017-08-25 2017-11-24 西安航天动力研究所 A kind of combined mechanical sealing device
CN108708802A (en) * 2018-04-19 2018-10-26 北京航天动力研究所 A kind of liquid-propellant rocket engine turbine pump low-temperature and high-speed end face seal experimental rig
CN110030381A (en) * 2019-03-12 2019-07-19 北京星际荣耀空间科技有限公司 One kind being suitable for high speed and high pressure dynamic sealing device and aircraft
CN110514357A (en) * 2019-08-12 2019-11-29 大连理工大学 A kind of ultralow temperature medium dynamic sealing experimental rig
CN111413093A (en) * 2020-03-20 2020-07-14 蓝箭航天技术有限公司 Integrated test system for cryogenic bearing and dynamic seal
CN111636981A (en) * 2020-06-12 2020-09-08 哈尔滨工业大学 Test bench for testing floating ring seal of rocket turbopump

Also Published As

Publication number Publication date
CN112502859A (en) 2021-03-16

Similar Documents

Publication Publication Date Title
CN112502859B (en) High-speed dynamic sealing element test device for rocket engine
CN113405735B (en) High-speed helium end face sealing test device for liquid rocket engine turbine pump
CN101457658A (en) Turbocharger center housing and rotating assembly
CN108708802A (en) A kind of liquid-propellant rocket engine turbine pump low-temperature and high-speed end face seal experimental rig
CN214196502U (en) High-speed dynamic sealing element test device
CN109752141A (en) A kind of mechanical seal product testing processing unit (plant) and method
CN112432733A (en) Novel hydrostatic pressure type main pump mechanical seal test device
CN113670602B (en) Rotary dynamic seal loss testing device and method
CN114739563A (en) Static ring movable mechanical seal radial membrane pressure distribution testing device
CN208476485U (en) A kind of large-diameter mechanical seal test device
CN112324591B (en) Low-temperature high-rotating-speed floating ring sealing test device for rocket engine
CN114754944A (en) Positive/negative pressure dynamic sealing performance test platform
CN213775555U (en) Low-temperature high-rotating-speed floating ring sealing test device for rocket engine turbine pump
CN209416598U (en) A kind of mechanical seal product testing processing unit (plant)
CN115541134A (en) Low-temperature high-speed double-station end face seal test device and method for hydrogen-oxygen turbine pump
CN215065255U (en) Low-temperature high-speed bearing tester
CN208396963U (en) Two phase flow fluid machinery flow passage components polishing machine test device
CN116429334B (en) Metal skeleton rotation axis lip seal circle capability test evaluation device
CN220452722U (en) Powder stirring shaft sealing device
CN213842551U (en) Air tightness test device for bearing
CN115182829B (en) Large-pressure-difference high-rotation-speed floating ring sealing test bed
CN219657665U (en) Experimental device for testing critical rotation speed of rotary oil seal
CN212254507U (en) Low-temperature dynamic seal test bed
CN117309268A (en) Sealing ring testing device for aerospace rotary machine
CN211042962U (en) Thrust bearing bush test bench

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant