CN115200786B - High-pressure floating ring seal test equipment for turbine pump of heavy liquid rocket engine - Google Patents
High-pressure floating ring seal test equipment for turbine pump of heavy liquid rocket engine Download PDFInfo
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- CN115200786B CN115200786B CN202210803769.1A CN202210803769A CN115200786B CN 115200786 B CN115200786 B CN 115200786B CN 202210803769 A CN202210803769 A CN 202210803769A CN 115200786 B CN115200786 B CN 115200786B
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/025—Details with respect to the testing of engines or engine parts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D15/00—Control, e.g. regulation, of pumps, pumping installations or systems
- F04D15/0088—Testing machines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3204—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings with at least one lip
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/40—Sealings between relatively-moving surfaces by means of fluid
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/04—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides high-pressure floating ring sealing test equipment for a turbine pump of a heavy liquid rocket engine, which comprises a rotor assembly for transmission and a shell assembly for supporting the rotor assembly and forming a test environment, wherein the floating ring assembly to be tested is sleeved on the rotor assembly and fixed on the shell assembly, a sealing cavity is formed among the floating ring assembly, the shell assembly and the rotor assembly, a leakage cavity is formed at the outer side of the floating ring assembly, and test media are stored in the sealing cavity; the dynamic seal assembly and the impeller seal assembly are adopted to seal the leakage cavity, different structures and forms are adopted according to different sealing pressures and sealing positions, and the sealing capacity of the leakage cavity of the test device under high working pressure is effectively improved by combining with a matching mode of a matching shafting, so that accurate measurement of leakage quantity is realized, and test precision is improved.
Description
Technical Field
The invention relates to the technical field of dynamic seal tests of liquid rocket engines, in particular to high-pressure floating ring seal test equipment for a turbine pump of a heavy liquid rocket engine.
Background
The floating ring sealing structure is used as an important component in a turbine pump of a heavy rocket engine, and dynamic pressure films are formed by gaps between the floating ring and the rotor after the rotor is started, so that the sealing throttling effect is realized. The working performance of the floating ring also determines the safety and reliability of the rocket engine, and when the rocket engine fails, serious accidents can be caused to cause rocket emission failure. In the development process of the heavy oxyhydrogen engine, a bench simulation test is required to be carried out on the high-pressure floating ring, and after the working performance of the high-pressure floating ring is verified, the subsequent engine test run and spaceflight emission can be carried out. The working pressure of the high-pressure floating ring is very high and is usually more than 15MPa, the stress state is complex in actual working, the formation and thickness of a dynamic pressure liquid film are influenced by various factors, the dynamic pressure liquid film is different from a theoretical design value, and the dynamic pressure liquid film is influenced by a plurality of nonlinear factors in operation, so that the cold state test of the floating ring component of the turbine pump of the heavy-duty engine has higher requirements on the strength, the high-pressure static sealing characteristic, the dynamic sealing characteristic, the vibration stability characteristic and the like of test equipment.
The existing test device seals the leakage cavity by adopting a leather cup and other modes, and the sealing effect cannot meet the sealing pressure requirement under the high working pressure of the high-pressure floating ring, so that the accuracy of measuring the leakage quantity is affected.
Disclosure of Invention
The invention solves the technical problems that: the high-pressure floating ring sealing test device for the turbine pump of the heavy liquid rocket engine has the advantages that the defects of the prior art are overcome, the dynamic sealing assembly and the impeller sealing assembly are adopted to seal the test cavity, the sealing capacity of the test device under the high-pressure test condition is improved, and the accurate measurement of the leakage quantity is realized.
The technical scheme of the invention is as follows:
The high-pressure floating ring sealing test equipment for the turbine pump of the heavy liquid rocket engine comprises a rotor assembly for transmission and a shell assembly for supporting the rotor assembly and forming a test environment, wherein the floating ring assembly to be tested is sleeved on the rotor assembly and fixed on the shell assembly, a sealing cavity is formed between one side of the floating ring assembly and the shell assembly and between one side of the floating ring assembly and the rotor assembly, a leakage cavity is formed between the other side of the floating ring assembly and the shell assembly and between the other side of the floating ring assembly and the rotor assembly, and test mediums are stored in the sealing cavity; the leakage cavity is sealed by adopting a dynamic seal assembly, the dynamic seal assembly is arranged in a first annular groove on the shell assembly and comprises a first seal part and a second seal part, the first seal part is positioned at one side close to the leakage cavity, the second seal part is positioned at one side far away from the leakage cavity, the first seal part and the second seal part are hollow revolution bodies and are respectively provided with a first seal lip and a second seal lip which are of bending structures, the first seal lip points to one side of the leakage cavity, the part matched with the rotor assembly is of a stepped structure, one side close to the leakage cavity is in clearance fit with the rotor assembly, one side far away from the leakage cavity is in interference fit with the rotor assembly, and the contact mode is surface contact; the second sealing lip points to one side far away from the leakage cavity, one side close to the leakage cavity, which is matched with the rotor assembly, is in interference fit with the rotor assembly, and the contact mode is line contact, and one side far away from the leakage cavity is in clearance fit with the rotor assembly.
Preferably, the impeller sealing assembly is positioned at one end of the leakage cavity close to the dynamic sealing assembly, the impeller sealing assembly comprises an impeller arranged on the rotor component and an impeller sealing ring arranged on the end face of the shell assembly, a radial gap is formed between the impeller sealing ring and the impeller, a plurality of impeller sealing rings are radially arranged on the impeller, and the impeller sealing rings are matched with a plurality of corresponding sealing ring grooves arranged on the end face of the shell assembly provided with the impeller sealing ring to form multistage sealing.
Preferably, the sealing pressure of the impeller satisfies the following expression:
Wherein: p is the impeller sealing pressure, n is the impeller rotating speed, D 1 is the impeller inner diameter, D 2 is the impeller outer diameter, ρ is the sealing cavity test medium density, g is the gravitational acceleration, h 1 is the impeller blade height, and delta 1 is the axial distance between the impeller and the shell component.
Preferably, the impeller sealing ring is in clearance fit with the sealing ring groove matched with the impeller sealing ring.
Preferably, a first impeller sealing ring closest to the rotor assembly among the impeller sealing rings is located between the inner wall of the housing assembly and the first lip, and forms clearance fit with the inner wall of the housing assembly and the first lip respectively.
Preferably, the radial clearance between the impeller and the impeller sealing ring is less than or equal to 3mm.
Preferably, the dynamic seal assembly further comprises one or more third seal parts arranged between the first seal part and the second seal part, the third seal parts are hollow revolution bodies with third seal lips of bent structures, the third seal lips point to one side far away from the leakage cavity, are in interference fit with the rotor assembly, and are in line contact.
Preferably, the interference of the first sealing lip and the rotor assembly interference fit part is 0.01-0.05 mm, and the clearance of the first sealing lip and the rotor assembly clearance fit part is 0-0.05 mm.
Preferably, the interference of the second sealing lip and the rotor assembly interference fit part is 0.05-0.12 mm, and the clearance of the second sealing lip and the rotor assembly clearance fit part is 0-0.05 mm.
Preferably, the surface roughness of the matching surface of the rotor assembly and the dynamic seal assembly is less than or equal to 0.4 and R a, and the surface hardness is more than 40.
Compared with the prior art, the invention has the advantages that:
(1) The high-pressure floating ring sealing test equipment for the turbine pump of the heavy liquid rocket engine adopts a dynamic sealing assembly to seal a leakage cavity, is designed into different structural forms according to different sealing pressure and sealing positions, combines the matched shafting surface treatment technical requirements, improves the sealing capacity of the leakage cavity of the test device to the greatest extent, and prolongs the service life of a sealing structure;
(2) The leakage cavity is sealed by adopting an impeller sealing structure, liquid medium is thrown out by virtue of centrifugal force generated by high-speed rotation of an impeller to form hydrodynamic seal, the requirement of sealing pressure is met by the design of impeller size, axial sealing gap and radial gap between the impeller and an impeller sealing ring, and the sealing capacity of the leakage cavity of the test device is improved;
(3) The impeller sealing structure is provided with a multi-stage impeller sealing ring which is matched with a sealing ring groove arranged on the shell assembly to form multi-stage gap sealing, so that larger flow resistance is formed for a fluid medium, and the sealing capacity of a leakage cavity of the test device is further improved;
(4) The invention adopts the combined sealing structure of the axial dynamic sealing component and the impeller sealing component, the maximum sealing pressure which can be formed is more than 2Mpa and is more than 2 times of the sealing pressure of the common leather cup sealing structure, and the sealing performance of the leakage cavity is effectively improved, so that the test device can accurately measure the leakage amount when the maximum working pressure is more than 15 Mpa.
Drawings
FIG. 1 is a schematic view of a first embodiment of the present invention;
FIG. 2 is a schematic view of the dynamic seal assembly and impeller seal assembly of the present invention;
FIG. 3 is a schematic view of the impeller seal assembly of the present invention;
FIG. 4 is a side view of the impeller seal assembly of the present invention;
FIG. 5 is a schematic view of structural parameters of the dynamic seal assembly of the present invention;
fig. 6 is a schematic diagram of a second embodiment of the present invention.
Detailed Description
The utility model provides a heavy liquid rocket engine turbine pump is with high-pressure floating ring seal test equipment, is including being used for driven rotor subassembly and being used for supporting rotor subassembly and forming test environment's casing subassembly, the floating ring subassembly cover that awaits measuring is located rotor subassembly and be fixed on the casing subassembly, form sealed chamber 11 between floating ring subassembly, casing subassembly and the rotor subassembly the outside of floating ring subassembly forms the leakage chamber, test medium has been stored in sealed chamber 11, during the test, rotor subassembly rotates, and the floating ring subassembly that awaits measuring seals the rotor subassembly, through measuring test medium follow leak between floating ring subassembly and the rotor subassembly in sealed chamber 11 to leak the leak quantity of the floating ring subassembly that awaits measuring carries out the sealing performance analysis.
As shown in fig. 1, a first embodiment of the present invention comprises a housing assembly and a rotor member, the housing comprising a first housing 1, a second housing 9 and a third housing 15;
The rotor component includes a main shaft 14, a first bearing and a second bearing;
One end of the main shaft 14 is fixedly mounted on the first shell 1 through the first bearing, and the other end of the main shaft passes through the second shell 9 and is fixedly mounted on the third shell 15; the inner ring of the first bearing or the second bearing is arranged on a bearing sleeve, and the bearing sleeve is in clearance fit with the main shaft 14 and transmits circumferential force with the main shaft 14 through a flat key; the outer ring is arranged on a bearing pressing sleeve, the end face of the outer ring is pressed by a bearing pressing cover, the bearing pressing sleeve is arranged on a shell by a screw, and the bearing pressing cover presses the inner ring of the bearing and simultaneously presses the bearing sleeve and the main shaft 14; the outer ring of the second bearing is contacted with the disc spring, the disc spring is arranged in the disc spring retainer, the pretightening force of the disc spring is regulated through the thickness of a bearing regulating gasket at the side edge of the disc spring retainer, and finally, the pressing force is brought by screwing the second bearing cover and the second bearing sleeve through bolts.
A first end cover is arranged on the first shell 1, and a second end cover is arranged on the third shell 15;
The floating ring assembly to be tested is arranged on the main shaft 14 and comprises a first floating ring assembly 10 and a second floating ring assembly 12 which are respectively fixed on the second shell 9, and a sealing cavity 11 is formed between the first floating ring assembly 10 and the second floating ring assembly 12 and between the second shell 9 and the main shaft 14; a high-pressure static sealing aluminum pad is arranged between the flange surface of the floating ring and the flange surface of the second shell 9, the matched flange surface of the floating ring and the sealing aluminum pad are fastened simultaneously by adopting high-strength bolts uniformly distributed on the circumference, and a saddle-shaped elastic pad is arranged at the head of the bolts for preventing looseness; the spindle 14 part for installing the floating ring assembly is provided with a spindle sleeve assembly, in the embodiment, the spindle sleeve assembly comprises three parts, wherein the first spindle sleeves positioned at two sides have the same structural size as the third spindle sleeve, the surface matched with the floating ring is sprayed with chromium oxide, and when in assembly, the spindle sleeve positioned at one side is firstly installed at the middle spindle shoulder of the spindle 14, and then the middle spindle sleeve, an aluminum pad and the spindle sleeve positioned at the other side are sequentially installed; the shaft sleeve component is in clearance fit with the main shaft 14, is compressed through a double-nut structure, and is provided with a first nut matched with the floating ring in the double-nut structure after the shaft sleeve component is assembled, and the first nut is slightly screwed down so that the shaft sleeve component does not fall under the action of gravity; the installed main shaft 14 and shaft sleeve assembly is installed in a concentricity instrument, the needle heads of dial indicators are respectively propped against the outer surfaces of the first shaft sleeve and the third shaft sleeve, and the main shaft 14 is rotated at the same time; if the circle jumping amount of the outer surfaces of the first shaft sleeve and the third shaft sleeve is larger than 0.015mm, a leather hammer is adopted to tap the shaft sleeve, the circle jumping amount is adjusted, the straight circle jumping amount is smaller than or equal to 0.015mm, the first nut is screwed down, the screwing torque is checked, and finally the second nut in the double-nut structure is installed, and the screwing torque is screwed down and checked.
A first leakage cavity 8 is formed between the first floating ring assembly 10 and the end face of the first shell 1, and a second leakage cavity 13 is formed between the second floating ring assembly 12 and the end face of the third shell 15;
A first bearing cavity is formed between the first end cover and the end face of the first shell 1, and a second bearing cavity is formed between the second end cover and the end face of the second shell 9.
The bearing cavity and the leakage cavity are sealed by adopting a dynamic sealing assembly, the dynamic sealing assembly comprises a first dynamic sealing assembly and a second dynamic sealing assembly, the first dynamic sealing assembly is positioned in a first annular groove of the first shell 1, and the second dynamic sealing assembly is positioned in a second annular groove of the third shell 15. As shown in fig. 2, the dynamic seal assembly includes a first seal portion 5 and a second seal portion 2, where the first seal portion 5 is located at a side close to the seal cavity 11, is a hollow revolution body, has a cross section similar to an L shape, and has a first seal lip with a curved structure, the first seal lip points to a side of the leak cavity, is in a stepped structure with a portion matched with the main shaft 14, is in clearance fit with the main shaft 14 near the leak cavity, has a clearance amount of 0-0.05 mm, forms a clearance seal by forming a very small clearance with the main shaft 14, has a throttling effect on a liquid medium, has an interference fit with the main shaft 14 far from the leak cavity, has a contact mode of surface contact, has an interference amount of 0.01-0.05 mm, and is tightly attached to the main shaft 14 through elastic deformation to form a blocking effect on a leakage channel of the liquid medium. The first sealing part 5 forms a unidirectional maximum sealing pressure of more than 1MPa through the combined action of clearance sealing and interference fit contact sealing. In this embodiment, the first sealing portion 5 is made of a composite material of polytetrafluoroethylene and graphite, and has good wear resistance and low temperature resistance.
The second sealing part 2 is located near one side of the bearing cavity and is a hollow revolution body, the cross section shape of the second sealing part is similar to that of a J shape, the second sealing part is provided with a second sealing lip which is of a bent structure, the second sealing lip points to one side of the bearing cavity, the matching part of the second sealing lip and the main shaft 14 is of a stepped structure, one side near the leakage cavity is in interference fit with the main shaft 14, the contact mode is line contact, the interference is 0.05-0.12 mm, the second sealing lip is tightly attached to the main shaft 14 through elastic deformation, the line contact mode is changed into surface contact, and the blocking effect on the leakage channel of the liquid medium is formed. One side close to the bearing cavity is in clearance fit with the main shaft 14, the clearance amount is 0-0.05 mm, and the length of the clearance fit part is more than 3mm. The liquid medium is throttled by forming a gap seal with the spindle 14 with a very small gap. The formed unidirectional maximum sealing pressure is more than 1MPa through the combined action of the clearance seal and the interference fit contact seal.
In this embodiment, the spring 16 is disposed at the outer side of the bending portion of the second sealing lip, and the spring 16 provides centripetal pressure to the sealing member, so as to ensure contact pressure between the sealing lip and the shaft, so that the sealing lip and the shaft are in fit contact with sufficient stability, and dynamic sealing performance is improved.
Preferably, the dynamic seal assembly further includes one or more third seal portions 4 disposed between the first seal portion 5 and the second seal portion 2, in this embodiment, one third seal portion 4 is a hollow revolving body with a third seal lip having a curved structure, the third seal lip points to one side of the bearing cavity, is in interference fit with the main shaft 14, and has a contact form of line contact, the interference is 0.05-0.12 mm, and is tightly attached to the main shaft 14 through elastic deformation, so as to form a blocking effect on the leakage path of the liquid medium, and the maximum sealing pressure that can be formed is greater than 0.5MPa.
Further, a dynamic seal adjusting pad 3 is disposed between the first, second and third sealing portions, and is used for adjusting the axial distance between the dynamic seal portions, and may also be used for adjusting the axial distance between the dynamic seal assembly and the housing assembly.
In this embodiment, a third dynamic seal assembly having the same structure as the first and second dynamic seal assemblies is disposed between the second end cap and the main shaft 14 to further seal the second bearing chamber.
The surface roughness of the matching surface of the main shaft 14 and the dynamic seal assembly meets Ra less than or equal to 0.4, and the surface hardness meets HRC more than 40.
The leakage cavity is further sealed through an impeller sealing assembly, as shown in fig. 2,3 and 4, the impeller sealing assembly is located at one end of the leakage cavity, which is close to the dynamic sealing assembly, the impeller sealing assembly comprises an impeller 6 and an impeller sealing ring 7, the impeller 6 comprises a hub 21 and impeller blades 20 evenly distributed along the axial direction of the hub 21, in this embodiment, the impeller blades 20 are cuboid, the number of the impeller blades is 10, and one side of the hub 21, which faces the sealing cavity 11, is in a round table structure.
The impeller sealing ring 7 is fastened on the shell component through a screw, a radial gap is formed between the impeller sealing ring 7 and the impeller 6, and the axial length of the impeller sealing ring 7 is equal to the sum of the axial length L 1 of the impeller hub 21, the height h 1 of the impeller blades 20 and the axial gap delta 1 between the impeller and the shell component.
Further, a plurality of impeller sealing rings are sequentially arranged on the end face of the impeller 6 facing the bearing cavity along the radial direction, and are matched with a plurality of corresponding sealing ring grooves arranged on the end face of the shell assembly provided with the impeller sealing ring 7 to form multi-stage sealing, as shown in fig. 2 and 3, in the embodiment, three impeller sealing rings are arranged, namely a first impeller sealing ring 17, a second impeller sealing ring 18 and a third impeller sealing ring 19 from inside to outside in sequence, the second impeller sealing ring 18 and the third impeller sealing ring 19 are positioned in the sealing ring grooves on the end face of the first shell 1 or the third shell 15, the matched forms are clearance fit, the clearance is 0.5mm, and the matched axial clearance is the same as the radial clearance.
The first impeller sealing ring 17 closest to the rotating shaft is located between the inner wall of the shell and the first lip, and is in clearance fit with the inner wall of the shell, the clearance is 0.5mm, and the clearance is 0.01mm.
In this embodiment, the axial lengths of the second impeller seal ring 18 and the third impeller seal ring 19 are the same, and the axial length of the first impeller seal ring 17 is greater than the axial lengths of the second impeller seal ring 18 and the third impeller seal ring 19, so as to enhance the effect of axial throttling.
Specifically, the impeller seal assembly comprises a first impeller seal assembly located in the first leakage cavity 8 and a second impeller seal assembly located in the second leakage cavity 13, the first impeller seal assembly comprises a first impeller and a first impeller seal ring, the second impeller assembly comprises a second impeller and a second impeller seal ring, the first impeller and the second impeller are mounted on the main shaft 14, the first impeller seal ring and the second impeller seal ring are respectively fixed on the first shell 1 and the third shell 15, and the first impeller seal assembly and the second impeller seal assembly are oppositely arranged.
The sealing pressure of the impeller seal assembly satisfies the following expression:
Wherein: p is the impeller sealing pressure, n is the impeller rotating speed, D 1 is the impeller inner diameter, D 2 is the impeller outer diameter, ρ is the test medium density of the sealing cavity 11, g is the gravity acceleration, h 1 is the impeller blade 20 height, delta 1 is the axial distance between the impeller and the shell assembly, and the impeller size parameters are shown in figure 5.
The structural and dimensional parameters of the impeller sealing assembly are designed by adopting the following method:
(1) The structure and the size of the impeller sealing component are preliminarily designed according to the expression that the impeller sealing pressure meets;
(2) Establishing an impeller three-dimensional model, extracting a fluid domain model, introducing finite element analysis software, establishing a fluid finite element simulation model, calculating impeller inlet and outlet pressure and fluid resistance moment M under the working conditions of rated rotation speed and pressure, calculating impeller stirring power W=nM/9550, correcting the structural size of the impeller according to the result, performing simulation calculation, and obtaining the structural size of the impeller meeting the sealing requirement through continuous iteration;
(3) Assembling the impeller three-dimensional model and the fluid domain model, carrying out fluid-solid coupling analysis, analyzing the back stress of the impeller, and improving the stress condition of the impeller by changing the back included angle alpha of the impeller to finally obtain the included angle alpha with the best mechanical property of the impeller;
(4) And assembling the finally obtained bilobed wheel fluid domain model with bilobed wheels, assembling the combination body on a rotor, and designing and calculating the dynamic characteristics of the rotor through fluid-solid coupling analysis to reach a rigid rotor meeting the rotating speed requirement.
In this embodiment, the impeller back included angle α=104.3°.
The first impeller is in threaded connection with the main shaft 14, the rotation direction of the matched threads is left-handed, and the axial clearance between the first impeller and the first shell 1 is adjusted through the length of the impeller shaft sleeve; during installation, the first shell 1, the first end cover, the first bearing and the first bearing sleeve are not assembled, other parts are assembled, the spline end of the rotating main shaft 14 faces downwards, the distance from the first impeller to the end face of the first shell 1 is measured, the axial sealing gap of the first impeller is calculated according to a size chain, the axial size of a required impeller shaft sleeve is calculated, and the impeller sealing axial gap is ensured.
The second impeller and the spindle 14 are matched with each other in the direction of right-hand threads, and the structural size and the axial clearance adjustment method are the same as those of the first impeller.
The impeller can be of different specifications according to the pressure required to be sealed during the test. When the sealing pressure is high, selecting an impeller with a large outer diameter; and when the sealing pressure is smaller, selecting an impeller with a small outer diameter.
The impeller sealing ring 7 is used for determining the inner diameter and the axial length according to the test pressure, is respectively fastened on the first shell 1 and the third shell 15 through screws and is matched with the first impeller and the second impeller to form different radial sealing gaps and different radial sealing gap lengths.
The first impeller sealing assembly and the second impeller sealing assembly are axially symmetrically distributed, the sizes are consistent, the sealing pressure at two ends is guaranteed to be the same, axial force existing in the axial direction due to impeller pressure difference can be balanced, further additional axial force on the whole shaft system can be eliminated, stability of bearing pretightening force is guaranteed, and running stability is greatly improved.
The impeller sealing assembly is rotated at a high speed, the liquid medium is thrown to the maximum outer diameter of the impeller by virtue of the impeller blades 20, the radial pressure is reduced along with the reduction of the diameter, and the pressure at the bottom of the impeller blades 20 is the lowest; when the impeller rotates at a high speed, the impeller sealing ring at the bottom of the impeller blade 20 and the sealing ring groove form clearance seal, meanwhile, each stage of impeller sealing ring and the sealing ring groove form a section of flow passage with great flow resistance, and liquid medium generates certain pressure drop after passing through the multistage impeller sealing ring 7. The maximum pressure of the seal is related to the rotational speed, the higher the rotational speed the greater the seal pressure.
The outer surfaces of the first shell 1, the second shell 9 and the third shell 15 are provided with a plurality of through holes and filler necks along the circumferential direction, which are used for communicating the inlet and outlet of each working cavity and realizing the temperature and pressure measurement of each working cavity and parts. The first shell 1 and the third shell 15 of the shell are provided with the same first filler neck used for bearing temperature measurement, and the low-temperature sensors can be inserted into the outer ring of the bearing through the first filler neck and fastened, and the number of the low-temperature sensors is 2; the first shell 1 and the third shell 15 are respectively provided with two second filler necks with inclined holes and straight holes, and the second filler necks are led between the impeller blades 20 and the shells and are used for measuring the pressure at the bottoms of the impeller blades 20 and for exhausting, and the number of the second filler necks is 4; the first shell 1 and the third shell 15 are provided with the same third filler neck which is used for introducing a cooling medium to cool and discharge heat generated by bearing operation, and the total number of the third filler necks is 4;
The outer circular surface of the largest diameter of the second shell 9 is provided with three uniformly distributed 37-degree fourth filler neck which are used for introducing a low-temperature test medium into the inner sealing cavity 11 of the shell; the second shell 9 is also provided with a fifth filler neck for measuring the pressure of the sealing cavity 11, and the number of the fifth filler necks is 1; the sixth filler neck is used for measuring the pressure between the upper and lower stages of the floating ring, and the number of the sixth filler neck is 2; a seventh filler neck for measuring the pressure of the leakage chamber, 2 in number. An eighth filler neck is arranged in the middle of the uppermost part of the second shell 9 and is used for discharging gasification gas in a precooling stage and accelerating the cooling rate of the floating ring, wherein the total number of the filler necks is 1.
The second shell 9 is provided with a ninth filler neck for measuring the leakage quantity of the floating rings, the number of the ninth filler neck is 6, the center lines of the middle connecting lines of the two floating rings are symmetrically distributed, when the low-temperature floating ring assessment test is carried out, in order to accurately measure the leakage quantity, a vaporizer is connected behind a pipeline arranged on the ninth filler neck, and the low-temperature gas-liquid two-phase medium can be completely converted into a gas medium, and a gas volume flowmeter is connected behind the vaporizer, so that the accurate measurement of the gas-liquid two-phase flow is realized.
The other end of the main shaft 14 penetrates out of the second end cover and is connected with a flexible coupler, and an interference ring in interference fit with the main shaft 14 is arranged on the main shaft 14 and is used for axially positioning the coupler; the other end of the coupling is connected with a driving shaft, and the driving end can be driven by a motor and a gear box, driven by an electric spindle 14 or driven by a turbine.
The test device is fixed on a test bed through the second shell 9, the second shell 9 is fastened with the test bed through a test equipment fixing bolt and a test equipment fixing nut, and the test bed is fastened with a test equipment bottom plate through a test equipment bottom plate fixing bolt and a test equipment bottom plate fastening nut; four top and bottom bolts are arranged near four test equipment fixing nuts on the test bed, the test bed and the test equipment bottom plate can be jacked up for a certain distance by screwing in the top and bottom bolts, a horseshoe-shaped gasket is plugged into or withdrawn from the position where the test bed is connected with the test equipment bottom plate by the bolts, the horseshoe-shaped gasket is made of stainless steel, and the thickness of the horseshoe-shaped gasket is composed of a series of sizes of 0.05mm, 0.06mm, 0.07mm, 0.08mm, 0.09mm and 0.1mm … …, so that the aim of adjusting the center height is fulfilled; the top edge fixing frame of the test bed is fixed on the bottom plate of the test equipment through top edge fixing bolts, one top edge fixing frame is arranged in the front, the rear, the left and the right directions of the test bed, at least two top edge bolts are fixed on each fixing edge, and the left, the right, the front and the rear of the coaxiality can be adjusted by adjusting the screwing length of the top edge bolts.
The sensor rack is fastened with the bottom plate through a sensor rack fixing bolt, the eddy current displacement sensor is fastened on the sensor rack through a nut, and the distance between the probe and the coupler is not more than 0.2mm. When the equipment runs at high speed, the vibration state of the flexible coupling can be obtained by the eddy current displacement sensor. In addition, at the radial position of the bearing after the assembly is completed, a plane for installing a sensor is machined at the bottommost part of the first shell 1 and the third shell 15, and a vibration acceleration sensor is installed on the first shell 1 and the third shell 15 and used for monitoring the working states of the two bearing positions.
The test device can realize the test of the floating ring under different working conditions by replacing the main shaft 14 and the shaft sleeve, as shown in fig. 6, which is a second embodiment of the invention, and the test device is used for the working state of the normal-temperature floating ring test, wherein the working medium comprises air, nitrogen and other gas mediums. In order to realize the conversion between the two structures shown in fig. 1 and 6, the device shown in fig. 1 is first disassembled, normal-temperature floating rings 23 and 24 shown in fig. 6 are respectively mounted on the adapter sleeves 22 and 25, and then the adapter sleeves 22 and 25 are mounted on the second housing 9 through high-strength bolts. Wherein the main shaft 14 and the shaft sleeve are locked by double nuts, and the installation method of the main shaft 14 is identical to that of fig. 1.
The bearing of this embodiment has two schemes: (1) lubricating a bearing by grease; (2) The low-temperature bearing is adopted, the cooling medium adopts purified water, the purified water enters the bearing through the third filler neck to cool, and the water cooler is connected before the medium inlet filler neck.
The floating ring assembly in the embodiment shown in fig. 1 is replaced by the adapter sleeves 22 and 25 shown in fig. 6, and the main shaft 14 and the shaft sleeve parts are replaced to replace the least parts, so that the examination of the normal-temperature gas floating ring under different rotating speeds and different pressures is realized.
What is not described in detail in the present specification is a well known technology to those skilled in the art.
Claims (10)
1. The high-pressure floating ring sealing test equipment for the turbine pump of the heavy liquid rocket engine is characterized by comprising a rotor assembly for transmission and a shell assembly for supporting the rotor assembly and forming a test environment, wherein the floating ring assembly to be tested is sleeved on the rotor assembly and fixed on the shell assembly, a sealing cavity is formed between one side of the floating ring assembly and the shell assembly and between one side of the floating ring assembly and the rotor assembly, a leakage cavity is formed between the other side of the floating ring assembly and the shell assembly and between the other side of the floating ring assembly and the rotor assembly, and test mediums are stored in the sealing cavity; the leakage cavity is sealed by adopting a dynamic seal assembly, the dynamic seal assembly is arranged in a first annular groove on the shell assembly and comprises a first seal part (5) and a second seal part (2), the first seal part (5) is positioned at one side close to the leakage cavity, the second seal part (2) is positioned at one side far away from the leakage cavity, the first seal part (5) and the second seal part (2) are hollow revolution bodies and respectively provided with a first seal lip and a second seal lip which are of bending structures, the first seal lip points to one side of the leakage cavity, the matching part of the first seal lip and the rotor assembly is of a stepped structure, one side close to the leakage cavity is in clearance fit with the rotor assembly, and one side far away from the leakage cavity is in interference fit with the rotor assembly in a surface contact manner; the second sealing lip points to one side far away from the leakage cavity, one side close to the leakage cavity, which is matched with the rotor assembly, is in interference fit with the rotor assembly, and the contact mode is line contact, and one side far away from the leakage cavity is in clearance fit with the rotor assembly.
2. The high-pressure floating ring seal test device for a turbine pump of a heavy-duty liquid rocket engine according to claim 1, further comprising an impeller seal assembly, wherein the impeller seal assembly is positioned at one end of the leakage cavity close to the dynamic seal assembly, the impeller seal assembly comprises an impeller (6) arranged on a rotor component and an impeller seal ring (7) arranged on an end face of a shell assembly, a radial gap is formed between the impeller seal ring (7) and the impeller (6), a plurality of impeller seal rings are radially arranged on the impeller (6), and a plurality of corresponding seal ring grooves arranged on the end face of the shell assembly on which the impeller seal ring is mounted are matched to form a multi-stage seal.
3. The high-pressure floating ring seal test device for a turbopump of a heavy-duty liquid rocket engine according to claim 2, characterized in that the sealing pressure of the impeller (6) satisfies the following expression:
Wherein: p is the impeller sealing pressure, n is the impeller rotating speed, D 1 is the impeller inner diameter, D 2 is the impeller outer diameter, ρ is the sealing cavity test medium density, g is the gravitational acceleration, h 1 is the impeller blade height, and delta 1 is the axial distance between the impeller and the shell component.
4. The high-pressure floating ring seal test device for the turbine pump of the heavy-duty liquid rocket engine according to claim 2, wherein clearance fit is formed between the impeller seal ring and a seal ring groove matched with the impeller seal ring.
5. The high-pressure floating ring seal test device for a turbine pump of a heavy-duty liquid rocket engine according to claim 2, wherein a first impeller seal ring closest to the rotor assembly among the plurality of impeller seal rings is located between the inner wall of the housing assembly and the first lip, and forms clearance fit with the inner wall of the housing assembly and the first lip, respectively.
6. The high-pressure floating ring seal test device for a turbine pump of a heavy liquid rocket engine according to claim 2, wherein a radial clearance between the impeller (6) and the impeller seal ring (7) is 3mm or less.
7. The high-pressure floating ring seal test device for a turbine pump of a heavy-duty liquid rocket engine according to claim 1, wherein the dynamic seal assembly further comprises one or more third seal parts (4) arranged between the first seal parts (5) and the second seal parts (2), the third seal parts (4) are hollow revolution bodies with third seal lips of bent structures, the third seal lips point to one side far away from a leakage cavity, are in interference fit with the rotor assembly, and are in line contact.
8. The high-pressure floating ring seal test device for a turbine pump of a heavy-duty liquid rocket engine according to any one of claims 1 to 7, wherein the interference of the first seal lip with the rotor assembly interference fit portion is 0.01 to 0.05mm, and the clearance of the first seal lip with the rotor assembly clearance fit portion is 0 to 0.05mm.
9. The high-pressure floating ring seal test device for a turbine pump of a heavy-duty liquid rocket engine according to any one of claims 1 to 7, wherein the interference of the second sealing lip with the rotor assembly interference fit portion is 0.05 to 0.12mm, and the clearance with the rotor assembly clearance fit portion is 0 to 0.05mm.
10. The high-pressure floating ring seal test device for a turbine pump of a heavy-duty liquid rocket engine according to one of claims 1 to 7, wherein the surface roughness of the matching surface of the rotor assembly and the dynamic seal assembly satisfies R a to be less than or equal to 0.4, and the surface hardness satisfies HRC > 40.
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| CN202210803769.1A CN115200786B (en) | 2022-07-07 | 2022-07-07 | High-pressure floating ring seal test equipment for turbine pump of heavy liquid rocket engine |
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| CN202210803769.1A CN115200786B (en) | 2022-07-07 | 2022-07-07 | High-pressure floating ring seal test equipment for turbine pump of heavy liquid rocket engine |
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| CN112502859A (en) * | 2020-10-09 | 2021-03-16 | 蓝箭航天技术有限公司 | High-speed dynamic sealing element test device for rocket engine |
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| US20150052980A1 (en) * | 2013-08-21 | 2015-02-26 | Danny M. Sheldon | Gas turbine fuel nozzle leak detection pressure test tool and method for leak detection |
| CN110514357B (en) * | 2019-08-12 | 2020-06-16 | 大连理工大学 | Ultralow temperature medium dynamic seal test device |
| 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 |
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| CN112502859A (en) * | 2020-10-09 | 2021-03-16 | 蓝箭航天技术有限公司 | High-speed dynamic sealing element test device for rocket engine |
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| Title |
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| 液体火箭发动机超高转速泵浮动密封环研究;黄智勇, 李惠敏, 胡钟兵;火箭推进;20040830(04);全文 * |
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