CN115200786A - High-pressure floating ring sealing test equipment for heavy liquid rocket engine turbine pump - Google Patents
High-pressure floating ring sealing test equipment for heavy liquid rocket engine turbine pump Download PDFInfo
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- CN115200786A CN115200786A CN202210803769.1A CN202210803769A CN115200786A CN 115200786 A CN115200786 A CN 115200786A CN 202210803769 A CN202210803769 A CN 202210803769A CN 115200786 A CN115200786 A CN 115200786A
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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
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- 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
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- 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
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- 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 heavy liquid rocket engine turbine pump, 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 outside the floating ring assembly, and a test medium is stored in the sealing cavity; adopt dynamic seal subassembly and impeller seal subassembly to seal the chamber of revealing, adopt different structures and forms according to the difference of sealing pressure and sealed position, combine with the cooperation mode of cooperation shafting, effectively improved the sealing ability of test device leakage chamber under high operating pressure, realize the accurate measurement to letting out leakage, promote test accuracy.
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 turbo pump of a heavy-duty liquid rocket engine.
Background
The floating ring sealing structure is used as an important component in a heavy rocket engine turbopump, and a dynamic pressure film is formed by a gap between the floating ring and a rotor after the rotor is started, so that the sealing and throttling effects are realized. The working performance of the floating ring also determines the safety and reliability of the rocket engine, and when the floating ring breaks down, major accidents can be caused, and the rocket is failed to launch. In the process of developing the heavy oxyhydrogen engine, a bench simulation test must be carried out on the high-pressure floating ring, and after the working performance is verified, subsequent engine test run and aerospace launch can be carried out. The working pressure of the high-pressure floating ring is very high, usually more than 15MPa, the stress state is complex during actual working, the formation and the thickness of a dynamic pressure liquid film are influenced by various factors, the difference is generated between the theoretical design value and the theoretical design value, and the dynamic pressure liquid film is influenced by a plurality of nonlinear factors during operation, so that the cold test of the floating ring component of the heavy-duty engine turbopump has higher requirements on the aspects of the strength, the high-pressure static sealing property, the dynamic sealing property, the vibration stability property and the like of the test equipment.
The existing test device adopts a leather cup and other modes to seal a leakage cavity, and the sealing effect of the existing test device cannot meet the sealing pressure requirement of a high-pressure floating ring under high working pressure, so that the accuracy of measuring the leakage amount is influenced.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the high-pressure floating ring sealing test equipment for the heavy liquid rocket engine turbine pump is provided, the dynamic seal assembly and the impeller seal assembly are adopted to seal the test cavity, the sealing capability of the test equipment under the high-pressure test condition is improved, and the accurate measurement of the leakage amount is realized.
The technical solution of the invention is as follows:
the high-pressure floating ring sealing test equipment for the heavy liquid rocket engine turbine pump 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 the rotor assembly, a leakage cavity is formed between the other side of the floating ring assembly and the shell assembly and the rotor assembly, and a test medium is stored in the sealing cavity; the leakage cavity is sealed by adopting a dynamic sealing assembly, the dynamic sealing assembly is arranged in a first annular groove on the shell assembly and comprises a first sealing part and a second sealing part, the first sealing part is positioned at one side close to the leakage cavity, the second sealing part is positioned at one side far away from the leakage cavity, the first sealing part and the second sealing part are hollow rotary bodies and respectively provided with a first sealing lip and a second sealing lip which are of a bent structure, the first sealing 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, and is in interference fit with the rotor assembly on one side close to the leakage cavity together with the rotor assembly matching part in a line contact mode, and the side far away from the leakage cavity is in clearance fit with the rotor assembly.
Preferably, still include impeller seal assembly, impeller seal assembly is located the leakage cavity is close to the one end of dynamic seal assembly, impeller seal assembly is including setting up the impeller on the rotor part and setting up the impeller seal circle on the casing subassembly terminal surface, impeller seal circle with form radial clearance between the impeller, radially be provided with a plurality of impeller seal rings on the impeller, with set up in the installation the cooperation of a plurality of seal ring grooves that correspond on impeller seal circle's the casing subassembly terminal surface forms multistage sealed.
Preferably, the sealing pressure of the impeller satisfies the following expression:
in the formula: p is impeller sealing pressure, n is impeller rotating speed, D 1 Is the inner diameter of the impeller, D 2 Is the external diameter of the impeller, rho is the density of the test medium in the sealed cavity, g is the gravity acceleration, h 1 Is the impeller blade height, delta 1 Is the axial distance of the impeller from the housing assembly.
Preferably, the impeller sealing ring and the sealing ring groove matched with the impeller sealing ring are in clearance fit.
Preferably, a first impeller sealing ring, which is closest to the rotor assembly, of the plurality of impeller sealing rings is located between the inner wall of the casing assembly and the first lip, and forms clearance fit with the inner wall of the casing 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 sealing parts arranged between the first sealing part and the second sealing part, the third sealing part is a hollow revolving body with a third sealing lip of a bent structure, the third sealing lip points to the side away from the leakage cavity and is in interference fit with the rotor assembly, and the contact form is line contact.
Preferably, the interference of the interference fit part of the first sealing lip and the rotor assembly is 0.01-0.05 mm, and the clearance of the clearance fit part of the first sealing lip and the rotor assembly is 0-0.05 mm.
Preferably, the interference of the interference fit part of the second sealing lip and the rotor assembly is 0.05-0.12 mm, and the clearance of the clearance fit part of the second sealing lip and the rotor assembly is 0-0.05 mm.
Preferably, the surface roughness of the matching surface of the rotor assembly and the dynamic sealing assembly meets R a Less than or equal to 0.4, and the surface hardness of the alloy meets the HRC of more than 40.
Compared with the prior art, the invention has the advantages that:
(1) The high-pressure floating ring seal test equipment for the heavy liquid rocket engine turbo pump adopts the dynamic seal assembly to seal the leakage cavity, is designed into different structural forms according to different seal pressures and seal positions, combines the technical requirements of matched shafting surface treatment, improves the sealing capability of the leakage cavity of the test device to the maximum extent, and prolongs the service life of the seal structure;
(2) The leakage cavity is sealed by adopting an impeller sealing structure, a liquid medium is thrown out by means of centrifugal force generated by high-speed rotation of an impeller to form fluid dynamic seal, the requirement on sealing pressure is met through the design of the size of the impeller, the axial sealing gap and the radial gap between the impeller and an impeller sealing ring, and the sealing capacity of the leakage cavity of the testing device is improved;
(3) The impeller sealing structure is provided with multistage impeller sealing rings which are matched with sealing ring grooves arranged on the shell assembly to form multistage clearance sealing, so that a fluid medium is provided with larger flow resistance, and the sealing capability of a leakage cavity of the test device is further improved;
(4) The combined sealing structure of the axial dynamic sealing assembly and the impeller sealing assembly is adopted, the maximum sealing pressure which can be formed is more than 2Mpa and is more than 2 times of the sealing pressure of a common leather cup sealing structure, and the sealing performance of a leakage cavity is effectively improved, so that the accurate measurement of the leakage amount can be realized when the maximum working pressure of a testing device 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 structural view of a dynamic seal assembly and an impeller seal assembly of the present invention;
FIG. 3 is a schematic structural view of an impeller seal assembly of the present invention;
FIG. 4 is a side view of the impeller seal assembly construction of the present invention;
FIG. 5 is a schematic view of the structural parameters of the dynamic seal assembly of the present invention;
fig. 6 is a schematic view of a second embodiment of the present invention.
Detailed Description
The high-pressure floating ring seal test equipment for the heavy liquid rocket engine turbine pump comprises a rotor assembly used for transmission and a shell assembly used 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 seal cavity 11 is formed between the floating ring assembly, the shell assembly and the rotor assembly, a leakage cavity is formed outside the floating ring assembly, a test medium is stored in the seal cavity 11, the rotor assembly rotates during testing, the floating ring assembly to be tested performs action sealing on the rotor assembly, and the leakage amount between the floating ring assembly and the rotor assembly in the seal cavity 11 is measured to analyze the sealing performance of the floating ring assembly to be tested.
As shown in fig. 1, a first embodiment of the present invention comprises a housing assembly and rotor components, the housing comprising a first housing 1, a second housing 9 and a third housing 15;
the rotor components include a main shaft 14, a first bearing and a second bearing;
one end of the main shaft 14 is fixedly mounted on the first housing 1 through the first bearing, and the other end of the main shaft passes through the second housing 9 and is fixedly mounted on the third housing 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 a circumferential force with the main shaft 14 through a flat key; the outer ring of the bearing is arranged on the bearing pressing sleeve, the end face of the outer ring is pressed through the bearing pressing cover, the bearing pressing sleeve is arranged on the shell through a screw, and the bearing pressing cap 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 in contact with the disc spring, the disc spring is installed in the disc spring retainer, the pretightening force of the disc spring is adjusted through the thickness of a bearing adjusting gasket on the side edge of the disc spring retainer, and finally the second bearing cover and the second bearing sleeve are screwed through bolts to bring pressing force.
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, 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 matching flange surface of the floating ring and the sealing aluminum pad are simultaneously fastened by adopting high-strength bolts uniformly distributed on the circumference, and a saddle-shaped elastic pad is arranged at the head part of the bolt for preventing looseness; the main shaft 14 part for installing the floating ring assembly is provided with a shaft sleeve assembly, in the embodiment, the shaft sleeve assembly comprises three parts, wherein the first shaft sleeve and the third shaft sleeve which are positioned at two sides have the same structural size, chromium oxide is sprayed on the surface matched with the floating ring, the shaft sleeve positioned at one side is firstly installed at the middle shaft shoulder of the main shaft 14 during assembly, and then the middle shaft sleeve, an aluminum pad and the shaft sleeve positioned at the other side are sequentially installed; the shaft sleeve assembly is in clearance fit with the main shaft 14 and is compressed through a double-nut structure, after the shaft sleeve assembly is assembled, a first nut matched with the floating ring in the double-nut structure is installed, and the first nut is slightly screwed, so that the shaft sleeve assembly does not fall under the action of gravity; installing the installed main shaft 14 and the shaft sleeve assembly in a concentricity tester, respectively propping the needle heads of the dial indicator needles on the outer surfaces of the first shaft sleeve and the third shaft sleeve, and simultaneously rotating the main shaft 14; if the circular runout of the outer surfaces of the first shaft sleeve and the third shaft sleeve is larger than 0.015mm, a leather hammer is used for tapping the shaft sleeves to adjust the circular runout, the straight circular runout is smaller than or equal to 0.015mm, the first nuts are screwed and the screwing torque is checked, finally the second nuts in the double-nut structure are installed, and the screwing torque is screwed and checked.
A first leakage cavity 8 is formed between the first floating ring assembly 10 and the end surface of the first shell 1, and a second leakage cavity 13 is formed between the second floating ring assembly 12 and the end surface 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 seal assembly, the dynamic seal assembly comprises a first dynamic seal assembly and a second dynamic seal assembly, the first dynamic seal assembly is positioned in a first annular groove of the first shell 1, and the second dynamic seal 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, the first seal portion 5 is located on one side close to a seal cavity 11, and is a hollow revolving body, the cross-sectional shape of the first seal portion is similar to an "L" shape, and the first seal lip has a curved structure, the first seal lip points to one side of the leakage cavity, the matching portion of the first seal lip with the main shaft 14 is a stepped structure, one side close to the leakage cavity is in clearance fit with the main shaft 14, the clearance amount is 0 to 0.05mm, the clearance seal is formed by forming a very small clearance with the main shaft 14, the first seal lip has a throttling effect on a liquid medium, one side far away from the leakage cavity is in interference fit with the main shaft 14, the contact mode is surface contact, the interference amount is 0.01 to 0.05mm, and the first seal lip is tightly attached to the main shaft 14 through elastic deformation to form a blocking effect on a liquid medium leakage channel. The first sealing part 5 forms a one-way maximum sealing pressure larger 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 revolving body, the cross section of the second sealing part is similar to a J shape, a second sealing lip with a bending structure is arranged, the second sealing lip points to one side of the bearing cavity, the part matched with the main shaft 14 is of a stepped structure, the part near one side of the leakage cavity is in interference fit with the main shaft 14, the contact mode is line contact, the interference magnitude is 0.05-0.12 mm, the second sealing part is tightly attached to the main shaft 14 through elastic deformation, and the line contact mode is changed into surface contact, so that the blocking effect on a liquid medium leakage channel 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 gap seal is formed by a very small gap with the main shaft 14, and has a throttling effect on the liquid medium. The formed one-way maximum sealing pressure is larger than 1MPa through the combined action of clearance sealing and interference fit contact sealing.
In this embodiment, the outside of the curved portion of the second sealing lip is provided with a spring 16, and the spring 16 provides centripetal pressure to the sealing element, so as to ensure the contact pressure between the sealing lip and the shaft, so that the sealing lip and the shaft are in fit contact with each other 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, the third seal portion 4 is a hollow revolving body having a third seal lip with a curved structure, the third seal lip points to one side of the bearing cavity, and is in interference fit with the main shaft 14, the contact form is line contact, the interference amount is 0.05-0.12 mm, the third seal lip is tightly attached to the main shaft 14 through elastic deformation to form a blocking effect on a liquid medium leakage channel, and the maximum sealing pressure that can be formed is greater than 0.5MPa.
Further, a dynamic seal adjusting gasket 3 is arranged between the first sealing part, the second sealing part and the third sealing part, and is used for adjusting the axial distance between the dynamic sealing parts and also can be used for adjusting the axial distance between the dynamic sealing assembly and the shell 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 cover and the main shaft 14, so as to further seal the second bearing cavity.
The surface roughness of the matching surface of the main shaft 14 and the dynamic seal assembly meets Ra being less than or equal to 0.4, and the surface hardness meets HRC being more than 40.
Further seal the leakage cavity through impeller seal assembly, as shown in fig. 2, fig. 3, fig. 4, impeller seal assembly is located the leakage cavity is close to the one end of dynamic seal assembly, impeller seal assembly includes impeller 6 and impeller seal circle 7, impeller 6 includes wheel hub 21 and along wheel hub 21 axial evenly distributed's impeller blade 20, and in this embodiment, impeller blade 20 is the cuboid, and quantity position 10, wheel hub 21 is the round platform structure towards one side of seal cavity 11.
The impeller seal ring 7 is fastened on the shell assembly through screws, a radial gap is formed between the impeller seal ring 7 and the impeller 6, and the axial length of the impeller seal ring 7 is equal to the axial length L of the impeller hub 21 1 Impeller blade 20 height h 1 Axial clearance delta with impeller and casing assembly 1 And (4) summing.
Further, impeller 6 is along radially having set gradually a plurality of impeller seal rings on the terminal surface of bearing housing, with set up in the installation a plurality of sealed annular cooperations that correspond on impeller seal ring 7's the casing assembly terminal surface form multistage sealed, as shown in fig. 2, fig. 3, in this embodiment, be provided with three impeller seal ring, from interior to exterior is first impeller seal ring 17, second impeller seal ring 18 and third impeller seal ring 19 in proper order, second impeller seal ring 18 and third impeller seal ring 19 are located in the sealed annular on first casing 1 or the 15 terminal surfaces of third casing, its cooperation form is clearance fit, and the clearance is 0.5mm, and the complex axial clearance is the same with 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, is in clearance fit with the inner wall of the shell, is 0.5mm in clearance, and is in clearance fit with the first lip, and the clearance is 0.01mm.
In this embodiment, the axial lengths of the second impeller sealing ring 18 and the third impeller sealing ring 19 are the same, and the axial length of the first impeller sealing ring 17 is greater than the axial lengths of the second impeller sealing ring 18 and the third impeller sealing ring 19, so as to enhance the axial throttling effect.
Specifically speaking, the impeller seal subassembly is including being located the first impeller seal subassembly of first leakage chamber 8 with be located the second impeller seal subassembly of second leakage chamber 13, first impeller seal subassembly includes first impeller and first impeller seal circle, the second impeller subassembly includes second impeller and second impeller seal circle, first impeller and second impeller install in on the main shaft 14, first impeller seal circle and second impeller seal circle are fixed in respectively on first casing 1 and the third casing 15, first impeller seal subassembly sets up with second impeller seal subassembly is relative.
The sealing pressure of the impeller seal assembly satisfies the following expression:
in the formula: p is impeller sealing pressure, n is impeller rotating speed, D 1 Is the inner diameter of the impeller, D 2 Is the external diameter of the impeller, rho is the density of the test medium in the sealed cavity 11, g is the gravity acceleration, h 1 Is the height, delta, of the impeller blades 20 1 The impeller dimensional parameters are shown in fig. 5 for the axial distance of the impeller from the housing assembly.
The structure and the size parameters of the impeller sealing component are designed by adopting the following methods:
(1) Preliminarily designing the structure and the size of an impeller sealing assembly according to an expression met by the impeller sealing pressure;
(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 the inlet and outlet pressure and the fluid resistance moment M of the impeller under the working conditions of rated rotating speed and pressure, calculating the stirring power W = nM/9550 of the impeller, 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 three-dimensional impeller model and the fluid domain model, carrying out fluid-solid coupling analysis, analyzing the stress on the back of the impeller, and improving the stress condition of the impeller by changing the included angle alpha on the back of the impeller to finally obtain the included angle alpha with the best mechanical property of the impeller;
(4) Assembling the finally obtained double-impeller fluid domain model and the double impellers, assembling the combined body on the rotor, and designing and calculating the dynamic characteristics of the rotor through fluid-solid coupling analysis until the rigid rotor meets the requirement of the rotating speed.
In the present embodiment, the impeller back angle α =104.3 °.
The first impeller is in threaded connection with the main shaft 14, the rotating 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 an 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 the size chain, the required axial size of the impeller shaft sleeve is calculated, and the axial sealing gap of the impeller is ensured.
The rotating direction of the screw thread matched with the main shaft 14 of the second impeller is right-handed, and the structure size and the axial clearance adjusting method of the second impeller are the same as those of the first impeller.
The impeller can be selected to different specifications according to the pressure to be sealed during the test. When the sealing pressure is high, an impeller with a large outer diameter is selected; when the sealing pressure is lower, an impeller with a small outer diameter is selected.
The impeller sealing ring 7 determines 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 forms different radial sealing gaps and radial sealing gap lengths by being matched with the first impeller and the second impeller.
The first impeller sealing assembly and the second impeller sealing assembly are symmetrically distributed in the axial direction and are consistent in size, sealing pressures at two ends are the same, axial force existing due to impeller pressure difference in the axial direction can be balanced, additional axial force on the whole shafting can be eliminated, stability of bearing pretightening force is guaranteed, and operation stability is greatly improved.
When the impeller sealing assembly rotates at a high speed, the liquid medium is thrown to the position of the maximum outer diameter of the impeller by means of the impeller blades 20, the pressure in the radial direction 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 and the sealing ring groove at the bottom of the impeller blade 20 form clearance sealing, and meanwhile, the impeller sealing ring and the sealing ring groove at each stage form a section of flow passage with large flow resistance, and a liquid medium generates a certain pressure drop after passing through the multistage impeller sealing rings 7. The maximum pressure of the seal is related to the rotation speed, the higher the rotation 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 connecting nozzles along the circumferential direction, and the through holes and the connecting nozzles are used for communicating the inlets and the outlets of the working cavities and realizing temperature and pressure measurement of the working cavities and parts. The first shell 1 and the third shell 15 of the shell are provided with the same first filler neck for bearing temperature measurement, 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 hole and straight hole, the second filler necks lead to the space between the impeller blade 20 and the shells, are used for measuring the pressure at the bottom of the impeller blade 20 and exhausting gas, 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 necks for introducing cooling media to cool and discharge heat generated by the running of the bearing, and the number of the third filler necks is 4;
three uniformly distributed 37-degree fourth pipe connecting ports are arranged on the maximum-diameter outer circular surface of the second shell 9 and used for introducing a low-temperature test medium into the shell internal sealing cavity 11; the second shell 9 is also provided with 1 fifth filler neck for measuring the pressure of the sealed cavity 11; the number of the sixth filler necks used for measuring the pressure between the upper stage and the lower stage of the floating ring is 2; and 2 seventh filler neck nozzles for measuring the pressure of the leakage cavity. An eighth filler neck is arranged in the middle of the uppermost part of the second shell 9 and used for exhausting gasified gas in a precooling stage and accelerating the cooling rate of the floating ring, and the number of the eighth filler necks is 1.
The second shell 9 is provided with 6 ninth connecting nozzles for measuring the leakage amount of the floating rings, the number of the ninth connecting nozzles is symmetrical about the central line of the middle connecting line of the two floating rings, and in order to realize accurate measurement of the leakage amount when a low-temperature floating ring examination test is carried out, a vaporizer is connected behind the pipeline arranged on the ninth connecting nozzle, so that all low-temperature gas-liquid two-phase media can be converted into gas media, and a gas volume flowmeter is connected behind the vaporizer, thereby realizing accurate measurement of two gas-liquid flows.
The other end of the main shaft 14 penetrates out of the second end cover and is connected with the flexible coupler, and an interference ring in interference fit with the main shaft 14 is arranged on the main shaft 14 and used for axially positioning the coupler; the other end of the coupler is connected with a driving shaft, and the driving end can be driven by a motor and a gear box, an electric spindle 14 or a turbine.
The testing device is fixed on a testing bench through the second shell 9, the second shell 9 is fastened with the testing bench through a testing equipment fixing bolt and a testing equipment fixing nut, and the testing bench and a testing equipment bottom plate are connected and fastened through a testing equipment bottom plate fixing bolt and a testing equipment bottom plate fastening nut; four top-bottom bolts are arranged near four test equipment fixing nuts on the test bench, the test bench and a test equipment base plate can be jacked for a certain distance by screwing in the top-bottom bolts, a U-shaped gasket is inserted into or withdrawn from the position where the test bench is connected with the test equipment base plate bolts, the U-shaped gasket is made of stainless steel, and the thickness of the U-shaped gasket is formed by a series of 0.05mm, 0.06mm, 0.07mm, 0.08mm, 0.09mm and 0.1mm \8230 \ 8230and the size, so that the purpose of adjusting the center height is achieved; the test bench top edge fixing frame is fixed on the test equipment bottom plate through top edge fixing bolts, one of the test bench is arranged in each of four directions, namely the front direction, the rear direction, the left direction and the right direction, at least two top edge bolts are fixed on each fixing edge, and the front-back adjustment of the coaxiality can be realized by adjusting the screwing-in lengths 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 a probe of the eddy current displacement sensor 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, a plane for mounting sensors is processed corresponding to the lowest part of the first shell 1 and the third shell 15, and vibration acceleration sensors are mounted 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, the test device is a second embodiment of the invention, the embodiment is used for the working state of the normal-temperature floating ring test, and the working medium comprises air, nitrogen and other gas media. In order to realize the conversion between the two structures shown in fig. 1 and fig. 6, the device shown in fig. 1 is firstly disassembled, the normal temperature floating rings 23 and 24 shown in fig. 6 are respectively installed on the adapter sleeves 22 and 25, and then the adapter sleeves 22 and 25 are installed on the second shell 9 through high-strength bolts. The main shaft 14 and the shaft sleeve are locked by double nuts, and the installation method of the main shaft 14 is the same as that of the main shaft in the installation method shown in figure 1.
The bearing of the embodiment has two schemes: (1) lubricating a bearing by adopting grease; (2) Adopt the low temperature bearing, coolant adopts the pure water, and the pure water gets into through the third filler neck and cools off the bearing, and the water receiving is cold quick-witted before entering medium 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 spindle 14 and the shaft sleeve component are replaced to replace the minimum components, so that the examination of the normal-temperature gas floating ring at different rotating speeds and different pressures is realized.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. The high-pressure floating ring sealing test equipment for the heavy liquid rocket engine turbine pump 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 the rotor assembly, a leakage cavity is formed between the other side of the floating ring assembly and the shell assembly and the rotor assembly, and a test medium is 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 revolving bodies and respectively provided with a first seal lip and a second seal lip which are of a bent structure, 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, and is in interference fit with the rotor assembly on one side close to the leakage cavity together with the rotor assembly matching part in a line contact mode, and the side far away from the leakage cavity is in clearance fit with the rotor assembly.
2. The high-pressure floating ring seal test equipment for the heavy-duty liquid rocket engine turbo pump according to claim 1, further comprising an impeller seal assembly, wherein the impeller seal assembly is located at one end of the leakage cavity close to the dynamic seal assembly, the impeller seal assembly comprises an impeller (6) arranged on the rotor component and an impeller seal ring (7) arranged on the end face of the housing 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 the impeller seal rings are matched with a plurality of corresponding seal ring grooves arranged on the end face of the housing assembly on which the impeller seal ring is arranged to form multi-stage seal.
3. The high-pressure floating ring seal test equipment for heavy-duty liquid rocket engine turbo pumps of claim 2, wherein the sealing pressure of the impeller (6) satisfies the following expression:
in the formula: p is impeller sealing pressure, n is impeller rotating speed, D 1 Is the inner diameter of the impeller, D 2 Is the external diameter of the impeller, rho is the density of the test medium in the sealed cavity, g is the gravity acceleration, h 1 Is the impeller blade height, delta 1 Is the axial distance of the impeller from the housing assembly.
4. The high-pressure floating ring seal test equipment for the heavy-duty liquid rocket engine turbo pump according to claim 2, wherein the impeller seal ring and the seal ring groove matched with the impeller seal ring are in clearance fit.
5. The high pressure floating ring seal test apparatus for a heavy duty liquid rocket engine turbo pump according to claim 2, wherein a first impeller seal ring of the plurality of impeller seal rings, which is closest to the rotor assembly, is located between the housing assembly inner wall and the first lip, and forms a clearance fit with the housing assembly inner wall and the first lip, respectively.
6. The high-pressure floating ring seal test equipment for heavy-duty liquid rocket engine turbo pumps of claim 2, wherein the radial clearance between the impeller (6) and the impeller seal ring (7) is less than or equal to 3mm.
7. The high-pressure floating ring seal test equipment for the heavy-duty liquid rocket engine turbine pump according to claim 1, wherein the dynamic seal assembly further comprises one or more third sealing portions (4) arranged between the first sealing portion (5) and the second sealing portion (2), the third sealing portion (4) is a hollow revolving body with a bent structure third sealing lip, and the third sealing lip points to the side away from the leakage cavity and is in interference fit with the rotor assembly, and the contact form is line contact.
8. The high-pressure floating ring seal test equipment for the heavy-duty liquid rocket engine turbine pump according to one of claims 1 to 7, wherein the interference magnitude of the interference fit part of the first seal lip and the rotor assembly is 0.01-0.05 mm, and the clearance magnitude of the clearance fit part of the first seal lip and the rotor assembly is 0-0.05 mm.
9. The high-pressure floating ring seal test equipment for the heavy-duty liquid rocket engine turbine pump according to one of claims 1 to 7, wherein the interference magnitude of the interference fit part of the second seal lip and the rotor assembly is 0.05-0.12 mm, and the clearance magnitude of the clearance fit part of the second seal lip and the rotor assembly is 0-0.05 mm.
10. The high-pressure floating ring seal test equipment for heavy-duty liquid rocket engine turbo pumps of 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 Less than or equal to 0.4, and the surface hardness of the alloy meets the HRC of more than 40.
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| Application Number | Priority Date | Filing Date | Title |
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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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| 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 |
| WO2021027002A1 (en) * | 2019-08-12 | 2021-02-18 | 大连理工大学 | Ultra-low-temperature medium dynamic sealing test device |
| 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 |
| CN113405735A (en) * | 2021-04-30 | 2021-09-17 | 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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2022
- 2022-07-07 CN CN202210803769.1A patent/CN115200786B/en active Active
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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 |
| WO2021027002A1 (en) * | 2019-08-12 | 2021-02-18 | 大连理工大学 | Ultra-low-temperature medium dynamic sealing test device |
| 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 |
| CN113405735A (en) * | 2021-04-30 | 2021-09-17 | 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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| 黄智勇, 李惠敏, 胡钟兵: "液体火箭发动机超高转速泵浮动密封环研究", 火箭推进, no. 04, 30 August 2004 (2004-08-30) * |
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