CN108180149B - A kind of turbine pump end face seal air-tightness detection method - Google Patents
A kind of turbine pump end face seal air-tightness detection method Download PDFInfo
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- CN108180149B CN108180149B CN201711387850.1A CN201711387850A CN108180149B CN 108180149 B CN108180149 B CN 108180149B CN 201711387850 A CN201711387850 A CN 201711387850A CN 108180149 B CN108180149 B CN 108180149B
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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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- Examining Or Testing Airtightness (AREA)
Abstract
A kind of novel turbine pump end face seal air-tightness detection method, includes the following steps: Step 1: the pump fistulae of external gas cylinder and turbine pump, which is released channel, passes through pipeline connection；Step 2: open the valve of gas cylinder, make the gas of gas cylinder full of pump fistulae release channel, turbine pump end face seal friction is secondary and step 1 in pipeline, then measure the initial pressure of gas in gas cylinder, record initial time；Step 3: the change in pressure drop rate △ P of the pressure of gas at any time in measurement gas cylinder；Step 4: establishing the mathematical model of standard leak rate Y and change in pressure drop rate the △ P of turbine pump end face seal；Step 5: according to the change in pressure drop rate △ P in step 3, and, the mathematical model of standard leak rate Y and change in pressure drop rate the △ P of the turbine pump end face seal in step 4 calculate the standard leak rate Y of turbine pump end face seal.
Description
Technical field
The present invention relates to a kind of air-tightness detection methods, examine more particularly to a kind of turbine pump end face seal air-tightness
Survey method.
Background technique
Heart of the turbine pump as liquid-propellant rocket engine works with high temperature, high pressure, high revolving speed, corrosive media
Feature.Certain type liquid-propellant rocket engine turbine pump is two pump coaxial turbine offset structures, in order to guarantee that engine reliable works,
It avoids two media from meeting in turbine pump when working and generates explosion, it is identical using two sets between oxidant pump and petrolift
Sealing structure is for completely cutting off oxidant and fuel agent.The sealing structure mainly includes that a set of spring end face seal is primary seal,
Close to main pump, it is that propellant releases chamber among main and auxiliary sealing structure that it is auxiliary seal that end setting is a set of, which to obturage circle sealing,
The pipe passage (i.e. pump fistulae releases channel) of two Φ 7mm is symmetrical arranged for being discharged because primary seal leaks during operation
Propellant, further ensure auxiliary seal reliably working.Engine end face sealing performance can only fill at present in turbine pump component
Timing, by the fixed air test platform in ground to oxidant and fuel pump chamber sealing friction pair forward direction pressurising 0.6MPa pressure maintaining, from
Pipe passage (i.e. pump fistulae) detection main side face of two Φ 7mm for releasing chamber between main end face seal and auxiliary end face seal
The bubble leak rate of sealing, the bubble leak rate index is for differentiating the qualified or not of end face seal.However this method is only capable of in turbine
Pump assembly state is sealed air-tightness detection and differentiates, when general assembly is at engine, due to being originally intended to detection end face seal
The structures such as the turbine pump import and export of air-tightness, pump fistulae complete general assembly docking, can not be detected using traditional bubble method
Sealing performance simultaneously carries out qualified or not interpretation, traditionally using the bubble leak rate of turbine pump assembled state and qualification determination result view
For the air-tightness in entire engine production period or even rocket production cycle.In fact, the air-tightness of end face seal is by temperature
The factors influences such as degree, environment, turnover transport, storage period, vibration can generate certain variation, its engine whirlpool for rocket
Wheel pump end face seal air-tightness stability will directly affect reliability, service life or even task success or failure.
Summary of the invention
The technical problem to be solved by the present invention is having overcome the deficiencies of the prior art and provide a kind of turbine pump end face seal
Air-tightness detection method, this method establish crucial characterization parameter and are just filling the number that 0.6MPa counts bubble leak rate with based on tradition
Model is learned, accurately drooping characteristic parameter and ground standard bubble leak rate characterization parameter are mapped, solve nothing after engine general assembly
Method measures the crucial problem of bubble characterization sealing leak rate.
The object of the invention is achieved by the following technical programs:
A kind of turbine pump end face seal air-tightness detection method, includes the following steps:
Step 1: the pump fistulae of external gas cylinder and turbine pump, which is released channel, passes through pipeline connection；
Step 2: open the valve of gas cylinder, the gas of gas cylinder is made to release channel, turbine pump end face seal full of pump fistulae
The secondary pipeline in step 1 of friction, then measures the initial pressure of gas in gas cylinder, records initial time；
Step 3: the change in pressure drop rate △ P of the pressure of gas at any time in measurement gas cylinder；
Step 4: establishing the mathematical model of standard leak rate Y and change in pressure drop rate the △ P of turbine pump end face seal are as follows:
(1) as 0≤△ P≤0.0002, Y=415000 Δ P；
(2) as 0.0002 < △ P≤0.0008, Y=700000 Δ P-60；
(3) as 0.0008 < △ P≤0.008, Y=1.0642E+06·ΔP-356.7；
(4) as 0.008 < △ P≤0.018, Y=136607 Δ P+7064；
(5) as 0.018 < △ P≤0.036, Y=-7.7592E+07·ΔP2+5.29735E+06·ΔP-59897.74；
(6) as 0.036 < △ P≤0.047, Y=753217.4 Δ P+3370.85；
(7) as 0.047 < △ P≤0.070, Y=-8.81408E+06·ΔP2+2.37918E+06·ΔP-52194.7；
(8) as 0.070 < △ P≤0.110, Y=-1.08938E+07·ΔP2+2.90696E+06·ΔP-79108.4；
(9) as 0.110 < △ P≤0.30, Y=-4.30831E+06·ΔP2+3.25921E+06·ΔP-191749.2；
(10) when 0.30 < △ P, Y >=400000；
Step 5: according to the change in pressure drop rate △ P in step 3, and, the standard of the turbine pump end face seal in step 4
The mathematical model of leak rate Y and change in pressure drop rate △ P calculate the standard leak rate Y of turbine pump end face seal.
Above-mentioned turbine pump end face seal air-tightness detection method, the gas cylinder in the step 1 are the gas of constant pressure constant volume
Bottle.
Above-mentioned turbine pump end face seal air-tightness detection method defines the standard leak rate Y characteristic of turbine pump end face seal
Characterization parameter be gas cylinder drooping characteristic.
Above-mentioned turbine pump end face seal air-tightness detection method, the initial pressure of gas is in gas cylinder in the step 2
0.150MPa±0.005MPa。
Above-mentioned turbine pump end face seal air-tightness detection method, the inspection of turbine pump end face seal air-tightness detection method
Survey range is 0 bubble/min~250000 bubbles/min.
The present invention has the following beneficial effects: compared with the prior art
(1) present invention establishes the mathematical model of standard leak rate Y and change in pressure drop rate the △ P of turbine pump end face seal, accurately
Drooping characteristic parameter and ground standard bubble leak rate characterization parameter are mapped, are unable to measure bubble table after solving engine general assembly
The critical issue of sign sealing leak rate；
(2) air test platform is in workshop fixed location in conventional method, when turbine pump is sealed airtight detection, uses
Crane or the mobile turbine pump of unwheeling carry out piping connection, pressure regulation, 0.6MPa pressure maintaining, the measurement of bubble leak rate at air test platform；
The method of the present invention determines reversely charging pressure as 0.150MPa, and under constant volume, light-weight, moveable air supply system is more easily real
It is existing, solve traditional air seal test platform position fix (workshop), pressure resistant vessel require high (0.6MPa or more), volume and weight it is big,
The problems such as experimental bench system is complicated；
(3) the method for the present invention is advantageously implemented the automatic control of air-tightness detection, is convenient for process control automation, data
Calculation procedure, result interpretation are intelligent；
(4) conventional method uses from GROUND VORTEX pump assemblies state and is filled with 0.6MPa compressed gas, people to sealing friction pair
Work releases drainage counting number of bubbles at channel (pump fistulae) from pump, as primary seal leakage rate larger (more than 120 bubbles/min),
Naked eyes will be unable to more accurately count；The method of the present invention uses mapped function relation, and automatic interpretation seals airtight results of property,
Data of the leakage rate within the scope of 0~250000 bubble/min can be handled, power of test and range substantially extend.
Detailed description of the invention
Fig. 1 is the step flow chart of the method for the present invention；
Fig. 2 is the local structural graph of turbine pump of the present invention；
Fig. 3 is the first characteristic curve map that the present invention is detected for the end face seal of different leak rates；
Fig. 4 is the second characteristic curve map that the present invention is detected for the end face seal of different leak rates；
Fig. 5 is that the present invention is compared with using the detection accuracy of conventional method.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with attached drawing to implementation of the invention
Mode is described in further detail.
A kind of turbine pump end face seal air-tightness detection method, using by being leaked from engine oxidant pump and petrolift
Pipe reversely charging constant pressure, the compressed air of constant volume, are then identified and are characterized the friction of turbine pump end face seal with its drooping characteristic
Secondary leakage situation；Novel drooping characteristic is given based on experimental study and mathematical analysis and tradition counts the letter of bubble characterization leak rate
Number relationships and mathematical model solve after the completion of oxidant pump docks with petrolift the import and export pipeline general assembly, and no normal direction is sealed and rubbed
It wipes pair and is filled with the problem that compressed gas carries out airtight test and unified quantization characterization parameter and judgement, the present invention defines turbine pump
The characterization parameter of the standard leak rate Y characteristic of end face seal is the drooping characteristic of gas cylinder.
The turbine pump end face seal air-tightness detection method is by the experimental study of reversely charging pressure-bearing and to leakage quantity and sealing
Chamber volume calculations, determine one of the key parameter of novel drooping characteristic detection turbine pump sealing air-tightness: reversely charging pressure is
0.150MPa (table) ± 0.005MPa.The pressure value not only can effectively characterize engine end face sealing air-tightness, but also can protect
The structural reliability for demonstrate,proving auxiliary seal and turbine pump product is applied not only to single cover and seals compared with conventional method just fills 0.6MPa
It the compressed air volume of air-leakage test and substantially reduces, and gas source bearing capacity standard is also reduced, realize new design
Light-weight, moveable air supply system, solution traditional air seal test platform position is fixed, pressure resistant vessel requirement is high, volume and weight
Greatly, the problems such as experimental bench system is complicated.
The detection method changes conventional method and needs mechanical connection ground air test platform and turbine pump product, and
By artificial pressure regulation, pressure maintaining, connection leather hose, manual time-keeping, the complicated and mechanical work processes such as leakage bubble are counted, not only improved
Efficiency and result precision improved by high-precision sensor and intelligent distinguishing.The turbine pump end face seal air-tightness
Detection method is directly released channel with engine pump fistulae by output pipe and is connected to, design design constant volume under, it is light-weight,
Moveable air supply system realize liquid-propellant rocket engine general assembly after, shoot after etc. the engine air-tightness of different conditions
Real-time detection is characterized in that and the structure that engine pump fistulae releases channel end is on the one hand adequately utilized；It is another
Aspect gives novel drooping characteristic based on experimental study and mathematical analysis and tradition counts the functional relation of bubble characterization leak rate
And mathematical model, accurately drooping characteristic parameter and ground standard bubble leak rate characterization parameter are mapped, solve pump fistulae reversely charging
Compressed gas, which carries out airtight test quantization signifying parameter and conventional method leak rate inspection result parameter, can not seek unity of standard judgement
Problem.
It is real that turbine pump end face seal air-tightness detection method realizes liquid-propellant rocket engine end face seal air-tightness
When can determine that, store after general assembly state can determine that, shoot during can determine that, ensured rocket motor
The reliability of machine turbine pump end face seal.
Fig. 1 is a kind of step flow chart of turbine pump end face seal air-tightness detection method of the present invention.Step 101, outside
The valve of portion's gas cylinder is in off state, and the pump fistulae of external gas cylinder and turbine pump is released channel and passes through pipeline connection, i.e. outside
Gas cylinder and the pump fistulae of turbine pump release after channel is connected to, and gas cylinder, pipeline, pump fistulae release channel, turbine pump end face seal
Rub secondary composition confined space, and the gas pressure in confined space everywhere is equal.Turbine pump 1, spring end face seal 2, auxiliary
Sealing 3, pump fistulae release channel 4, turbine pump end face seal friction pair 5 as shown in Figure 2.
Step 102, the valve for opening gas cylinder makes the gas of gas cylinder release channel, turbine pump end face seal full of pump fistulae
Friction is secondary and step 1 in pipeline 4；Even if gas cylinder, pipeline, pump fistulae release the friction in channel 4, turbine pump end face seal
The pressure of pair 5 reaches balance；Then the initial pressure P of gas in gas cylinder is measured0, record initial time T0.In external gas cylinder for for
The gas cylinder of constant pressure constant volume, when the gas pressure in confined space everywhere is equal, the initial pressure P of gas in gas cylinder0For
0.150MPa±0.005MPa。
Step 103, after T after a period of time, the pressure P of gas in gas cylinder is measured again, gas in gas cylinder can be obtained
Pressure change in pressure drop rate △ P at any time.
Step 104, test and statistical analysis of the present invention by large sample establishes the standard leakage of turbine pump end face seal
The mathematical model of rate Y and change in pressure drop rate △ P, as shown in table 1.
Table 1
Step 105, according to the change in pressure drop rate △ P in step 103, and, the mark of the turbine pump end face seal in step 104
The mathematical model of quasi- leak rate Y and change in pressure drop rate △ P calculate the standard leak rate Y of turbine pump end face seal.
Fig. 3, Fig. 4 be respectively the present invention for the first characteristic curve map for being detected of end face seal of different leak rates and
Second characteristic curve map；Curve 110P indicates that drooping characteristic when leak rate is 110 bubbles/min, 240P indicate that leak rate is in figure
Drooping characteristic when 240 bubbles/min, other curve meanings are same as described above.For the drooping characteristic of different leak rates, using new
Method mapped function relation can calculate interpretation and seal airtight results of property.
Fig. 5 is that the present invention is compared with using the detection accuracy of conventional method, and stringency of test is accurate.Curve 1 is to use
The data that turbine pump end face seal air-tightness detection method is tested after completing engine general assembly, curve 2 are to use tradition side
The data that method is tested in GROUND VORTEX pump assemblies assembled state.The registration of two curves is good as seen in Figure 5, it was demonstrated that
A kind of accuracy and reliability of turbine pump end face seal air-tightness detection method.The present invention can be accurately mapped to
It is same as the product leakage situation of ground turbine pump state air-tightness, is counted using map of the mathematical model to specific leak rate
The engine product air-tightness testing result that GROUND VORTEX pump assemblies status criteria can or must be equal to is calculated, and carries out qualification
Whether determine.
The detection range of turbine pump end face seal air-tightness detection method is 0 bubble/min~250000 bubbles/min, much
Have exceeded the test scope of conventional method.
Using a kind of turbine pump end face seal air-tightness detection method of invention to the hairs of more time general assembly delivery status
Motivation turbine pump has carried out air-tightness detection, through design identification and precision performance experiments have shown that: the turbine pump end face of invention is close
Envelope air-tightness detection method precision it is high, it is easy to operate, engine is delivered entirely, applicability is good in storage period, solve biography
The limitation of system method.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (5)
1. a kind of turbine pump end face seal air-tightness detection method, other are characterized in that: including the following steps:
Step 1: the pump fistulae of external gas cylinder and turbine pump, which is released channel, passes through pipeline connection；
Step 2: opening the valve of gas cylinder, the gas of gas cylinder is made to release the friction in channel, turbine pump end face seal full of pump fistulae
Then pipeline in secondary and step 1 measures the initial pressure of gas in gas cylinder, record initial time；
Step 3: the change in pressure drop rate △ P of the pressure of gas at any time in measurement gas cylinder；
Step 4: establishing the mathematical model of standard leak rate Y and change in pressure drop rate the △ P of turbine pump end face seal are as follows:
(1) as 0≤△ P≤0.0002, Y=415000 Δ P；
(2) as 0.0002 < △ P≤0.0008, Y=700000 Δ P-60；
(3) as 0.0008 < △ P≤0.008, Y=1.0642E+06·ΔP-356.7；
(4) as 0.008 < △ P≤0.018, Y=136607 Δ P+7064；
(5) as 0.018 < △ P≤0.036, Y=-7.7592E+07·ΔP2+5.29735E+06·ΔP-59897.74；
(6) as 0.036 < △ P≤0.047, Y=753217.4 Δ P+3370.85；
(7) as 0.047 < △ P≤0.070, Y=-8.81408E+06·ΔP2+2.37918E+06·ΔP-52194.7；
(8) as 0.070 < △ P≤0.110, Y=-1.08938E+07·ΔP2+2.90696E+06·ΔP-79108.4；
(9) as 0.110 < △ P≤0.30, Y=-4.30831E+06·ΔP2+3.25921E+06·ΔP-191749.2；
(10) when 0.30 < △ P, Y >=400000；
Step 5: according to the change in pressure drop rate △ P in step 3, and, the standard leak rate Y of the turbine pump end face seal in step 4
With the mathematical model of change in pressure drop rate △ P, the standard leak rate Y of turbine pump end face seal is calculated.
2. a kind of turbine pump end face seal air-tightness detection method according to claim 1, other are characterized in that: described
Gas cylinder in step 1 is the gas cylinder of constant pressure constant volume.
3. a kind of turbine pump end face seal air-tightness detection method according to claim 1, other are characterized in that: definition
The characterization parameter of the standard leak rate Y characteristic of turbine pump end face seal is the drooping characteristic of gas cylinder.
4. a kind of turbine pump end face seal air-tightness detection method according to claim 1, other are characterized in that: described
The initial pressure of gas is 0.150MPa ± 0.005MPa in gas cylinder in step 2.
5. a kind of turbine pump end face seal air-tightness detection method according to claim 1, other are characterized in that: turbine
The detection range for pumping end face seal air-tightness detection method is 0 bubble/min~250000 bubbles/min.
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| CN201711387850.1A CN108180149B (en) | 2017-12-20 | 2017-12-20 | A kind of turbine pump end face seal air-tightness detection method |
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| JPS5912193A (en) * | 1982-07-13 | 1984-01-21 | Toshiba Corp | Leakage detecting device for recirculating pump of reactor |
| CN104235052A (en) * | 2014-07-23 | 2014-12-24 | 中国航天科技集团公司第六研究院第十一研究所 | Novel pressure stabilization device for double-end surface sealing of turbine pump |
| JP2016070159A (en) * | 2014-09-30 | 2016-05-09 | 株式会社日立製作所 | Centrifugal type fluid machine |
| CN105890844A (en) * | 2016-06-11 | 2016-08-24 | 税爱社 | Qualitative and quantitative detection method for tiny leakage of hidden oil storage tank |
-
2017
- 2017-12-20 CN CN201711387850.1A patent/CN108180149B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5912193A (en) * | 1982-07-13 | 1984-01-21 | Toshiba Corp | Leakage detecting device for recirculating pump of reactor |
| CN104235052A (en) * | 2014-07-23 | 2014-12-24 | 中国航天科技集团公司第六研究院第十一研究所 | Novel pressure stabilization device for double-end surface sealing of turbine pump |
| JP2016070159A (en) * | 2014-09-30 | 2016-05-09 | 株式会社日立製作所 | Centrifugal type fluid machine |
| CN105890844A (en) * | 2016-06-11 | 2016-08-24 | 税爱社 | Qualitative and quantitative detection method for tiny leakage of hidden oil storage tank |
Non-Patent Citations (2)
| Title |
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| "基于渗流原理的液体润滑机械密封的泄漏率研究";包超英等;《流体机械》;20141130;第42卷(第11期);第24-28页 |
| "涡轮泵端面密封性能与漏气量影响研究";白东安等;《火箭推进》;20100228;第36卷(第1期);第38-42页 |
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