CN108180149A - A kind of novel turbine pumps end face seal air-tightness detection method - Google Patents
A kind of novel turbine pumps end face seal air-tightness detection method Download PDFInfo
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- CN108180149A CN108180149A CN201711387850.1A CN201711387850A CN108180149A CN 108180149 A CN108180149 A CN 108180149A CN 201711387850 A CN201711387850 A CN 201711387850A CN 108180149 A CN108180149 A CN 108180149A
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- face seal
- turbine pump
- gas cylinder
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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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- General Engineering & Computer Science (AREA)
- Examining Or Testing Airtightness (AREA)
Abstract
A kind of novel turbine pumps end face seal air-tightness detection method, includes the following steps：Step 1: the pump fistulae of external gas cylinder and turbine pump 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: measure the change in pressure drop rate △ P of the pressure of gas in gas cylinder at any time；Step 4: establish the mathematical model of standard leak rate Y and change in pressure drop rate the △ P of turbine pump end face seal；Step 5: 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, and end face seal air-tightness is pumped more particularly to a kind of novel turbine
It can detection method.
Background technology
There is heart of the turbine pump as liquid-propellant rocket engine high temperature, high pressure, high rotating speed, Korrosionsmedium to work
Feature.Certain type liquid-propellant rocket engine turbine pump is two pump coaxial turbine offset structures, in order to ensure that engine reliable works,
Avoid two media meet in turbine pump when working generation explosion, employed between oxidant pump and petrolift two sets it is identical
Sealing structure is used to completely cut off oxidant and fuel agent.It is primary seal that the sealing structure, which mainly includes a set of spring end face seal,
Close to main pump, it is auxiliary seal that end setting is a set of, which to obturage circle sealing, releases chamber for propellant among main and auxiliary sealing structure,
The pipe passage (pump fistulae and release channel) of two Φ 7mm is symmetrical arranged for discharging because primary seal leaks in operation process
Propellant, further ensure auxiliary seal reliably working.Engine end face sealing performance can only fill at present in turbine pump component
Timing fixes air test platform to oxidant and fuel pump chamber sealing friction pair forward direction pressurising 0.6MPa pressurizes by ground, from
Pipe passage (pumping fistulae) the 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 are used to differentiate the qualified or not of end face seal.However this method is only capable of in turbine
Pump group part state is sealed air-tightness detection and differentiates, when general assembly is into 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, traditional bubble method can not be used to detect
Sealing performance simultaneously carries out qualified or not interpretation, is traditionally regarded using the bubble leak rate of turbine pump assembled state and qualification determination result
Air-tightness for 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.
Invention content
The technical problem to be solved by the present invention is to：A kind of novel turbine pump end face is overcome the deficiencies of the prior art and provide
Airtight method for testing performance is sealed, this method establishes crucial characterization parameter and counts bubble leak rate with just filling 0.6MPa based on tradition
Mathematical model, accurately drooping characteristic parameter and ground standard bubble leak rate characterization parameter are mapped, solve engine general assembly
The crucial problem of bubble characterization sealing leak rate can not be measured afterwards.
The object of the invention is achieved by the following technical programs：
A kind of novel turbine pumps end face seal air-tightness detection method, includes the following steps：
Step 1: the pump fistulae of external gas cylinder and turbine pump 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
Then the secondary pipeline in step 1 of friction measures the initial pressure of gas in gas cylinder, records initial time；
Step 3: measure the change in pressure drop rate △ P of the pressure of gas in gas cylinder at any time；
Step 4: the mathematical model for establishing standard leak rate Y and change in pressure drop rate the △ P of turbine pump end face seal is：
(1) as 0≤△ P≤0.0002, Y=415000 Δs P；
(2) as 0.0002 ＜ △ P≤0.0008, Y=700000 Δs 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 Δs 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 Δs 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: 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 calculates the standard leak rate Y of turbine pump end face seal.
Above-mentioned novel turbine pumps end face seal air-tightness detection method, and the gas cylinder in the step 1 is constant pressure constant volume
Gas cylinder.
Above-mentioned novel turbine pumps end face seal air-tightness detection method, defines the standard leak rate Y of turbine pump end face seal
The characterization parameter of characteristic is the drooping characteristic of gas cylinder.
Above-mentioned novel turbine pumps end face seal air-tightness detection method, in the step 2 in gas cylinder gas initial pressure
Power is 0.150MPa ± 0.005MPa.
Above-mentioned novel turbine pumps end face seal air-tightness detection method, novel turbine pump end face seal air-tightness detection
The detection range of method is 0 bubble/min~250000 bubbles/min.
The present invention has the advantages that 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, bubble table can not be measured 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 unwheeling movement turbine pump carry out pipeline connection, pressure regulation, 0.6MPa pressurizes, bubble leak rate measure 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 easily real
It is existing, solve traditional air seal test platform position fix (workshop), pressure resistant vessel requirement high (more than 0.6MPa), 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 automatically controlling for air-tightness detection, convenient for process control automation, data
Calculation procedure, result interpretation are intelligent；
(4) conventional method uses from GROUND VORTEX pump assemblies state and 0.6MPa compressed gas, people is filled with 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 in the range of 0~250000 bubble/min can be handled, power of test and range substantially extend.
Description of the drawings
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 collection of illustrative plates that the present invention is detected for the end face seal of different leak rates；
Fig. 4 is the second characteristic curve collection of illustrative plates that the present invention is detected for the end face seal of different leak rates；
Fig. 5 is the present invention with being compared using the accuracy of detection of conventional method.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with implementation of the attached drawing to the present invention
Mode is described in further detail.
A kind of novel turbine pumps end face seal air-tightness detection method, using by from engine oxidant pump and fuel
It pumps fistulae reversely charging constant pressure, the compressed air of constant volume, then identifies and characterize turbine pump end face seal with its drooping characteristic
The secondary leakage situation of friction；Novel drooping characteristic is given based on experimental study and mathematical analysis and tradition counts bubble characterization leak rate
Functional relation and mathematical model, solve after the completion of oxidant pump docks with petrolift the import and export pipeline general assembly, no normal direction is close
Envelope friction pair is filled with the problem that compressed gas carries out airtight test and unified quantization characterization parameter and judgement, and the present invention defines whirlpool
The characterization parameter of the standard leak rate Y characteristics of wheel pump end face seal is the drooping characteristic of gas cylinder.
Novel turbine pump end face seal air-tightness detection method by the experimental study of reversely charging pressure-bearing and to leakage quantity and
Annular seal space volume calculations determine one of key parameter of novel drooping characteristic detection turbine pump sealing air-tightness：Reversely charging pressure
For 0.150MPa (table) ± 0.005MPa.The pressure value not only can effectively characterize engine end face sealing air-tightness, but also energy
Ensure the structural reliability of auxiliary seal and turbine pump product, compared with conventional method just fills 0.6MPa, it is close to be applied not only to single set
It seals the compressed air volume of air-leakage test and substantially reduces, and air source bearing capacity standard is also reduced, realization is newly set
It counts light-weight, moveable air supply system, solves that traditional air seal test platform position is fixed, pressure resistant vessel requirement is high, volume and again
The problems such as amount is big, experimental bench system is complicated.
The novel detection method, which changes conventional method, needs mechanical connection ground air test platform and turbine pump production
Product, and the complexity such as bubble and mechanical work process are leaked by artificial pressure regulation, pressurize, connection leather hose, manual time-keeping, counting, no
It improves only efficiency and result precision is improved by high-precision sensor and intelligent distinguishing.The novel turbine pump end face is close
Envelope air-tightness detection method is directly released channel with engine pump fistulae by output pipe and is connected, design design constant volume
Under, light-weight, moveable air supply system realize liquid-propellant rocket engine general assembly after, shoot after etc. different conditions engine
The real-time detection of air-tightness is characterized in that on the one hand engine pump fistulae, which is adequately utilized, releases channel end
Structure；On the other hand it gives novel drooping characteristic based on experimental study and mathematical analysis and tradition counts bubble characterization leak rate
Drooping characteristic parameter and ground standard bubble leak rate characterization parameter are accurately mapped, solve pump by functional relation and mathematical model
Fistulae reversely charging compressed gas carries out airtight test quantization signifying parameter can not unify with conventional method leak rate inspection result parameter
The problem of standard determination.
Novel turbine pump end face seal air-tightness detection method realizes liquid-propellant rocket engine end face seal air-tightness
Can determine that in real time, general assembly state can detect can determine that, shoot after store during can determine that, ensured rocket
Engine turbine pumps the reliability of end face seal.
Fig. 1 is the step flow chart that a kind of novel turbine of the present invention pumps end face seal air-tightness detection method.
Step 101, the valve of external gas cylinder is in off state, and the pump fistulae of external gas cylinder and turbine pump is released channel leads to
Cross pipeline connection, i.e., external gas cylinder and the pump fistulae of turbine pump are released after channel connect, gas cylinder, pipeline, pump fistulae release channel,
The friction pair of turbine pump end face seal forms confined space, and the gas pressure in confined space everywhere is equal.Turbine pump 1, spring
Formula end face seal 2, auxiliary seal 3, pump fistulae release channel 4, turbine pump end face seal friction pair 5 as shown in Figure 2.
Step 102, the valve of gas cylinder is opened, the gas of gas cylinder is made to 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 channel 4, turbine pump end face seal friction
The pressure of pair 5 reaches balance；Then the initial pressure P of gas in gas cylinder is measured0, record initial time T0.Be in external gas cylinder 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, you can obtain gas in gas cylinder
Pressure change in pressure drop rate △ P at any time.
Step 104, the present invention passes through the experiment and statistical analysis of 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 calculates 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 collection of illustrative plates for being detected of end face seal of different leak rates and
Second characteristic curve collection of illustrative plates；Curve 110P represents drooping characteristic when leak rate is 110 bubbles/min in figure, and 240P represents that leak rate is
Drooping characteristic during 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, you can calculate interpretation and seal airtight results of property.
Fig. 5 is the present invention and the accuracy of detection comparison using conventional method, and stringency of test is accurate.Curve 1 is uses
The data that novel turbine pump end face seal air-tightness detection method is tested after engine general assembly is completed, curve 2 are using biography
The data that system method is tested in GROUND VORTEX pump assemblies assembled state.The registration of two curves is good as seen in Figure 5,
Demonstrate a kind of accuracy and reliability of novel turbine pump end face seal air-tightness detection method.The present invention can be accurate
The product leakage situation for being equal to ground turbine pump state air-tightness is mapped to, using the mathematical model to the figure of specific leak rate
Spectrum carries out calculating the engine product air-tightness testing result that can or must be equal to GROUND VORTEX pump assemblies status criteria, and
Carry out qualified or not judgement.
The detection range of novel turbine pump end face seal air-tightness detection method is 0 bubble/min~250000 bubbles/min,
Far beyond the test scope of conventional method.
Using a kind of novel turbine pump end face seal air-tightness detection method of invention to more general assembly delivery status
Engine turbine pump carried out air-tightness detection, through design identification and precision performance experiments have shown that：The novel turbine of invention
Pump end face seal air-tightness detection method precision it is high, it is easy to operate, engine is delivered entirely, applicability is good in storage period,
Solves the limitation of conventional method.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (5)
1. a kind of novel turbine pumps end face seal air-tightness detection method, other are characterized in that：Include the following steps：
Step 1: the pump fistulae of external gas cylinder and turbine pump 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
Then pipeline in secondary and step 1 measures the initial pressure of gas in gas cylinder, record initial time；
Step 3: measure the change in pressure drop rate △ P of the pressure of gas in gas cylinder at any time；
Step 4: the mathematical model for establishing standard leak rate Y and change in pressure drop rate the △ P of turbine pump end face seal is：
(1) as 0≤△ P≤0.0002, Y=415000 Δs P；
(2) as 0.0002 ＜ △ P≤0.0008, Y=700000 Δs 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 Δs 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 Δs 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: 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 novel turbine pump end face seal air-tightness detection method according to claim 1, other are characterized in that：
Gas cylinder in the step 1 is the gas cylinder of constant pressure constant volume.
3. a kind of novel turbine pump end face seal air-tightness detection method according to claim 1, other are characterized in that：
The characterization parameter for defining the standard leak rate Y characteristics of turbine pump end face seal is the drooping characteristic of gas cylinder.
4. a kind of novel turbine pump end face seal air-tightness detection method according to claim 1, other are characterized in that：
The initial pressure of gas is 0.150MPa ± 0.005MPa in gas cylinder in the step 2.
5. a kind of novel turbine pump end face seal air-tightness detection method according to claim 1, other are characterized in that：
The detection range of novel turbine pump 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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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 |
-
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 |
|---|
| 包超英等: ""基于渗流原理的液体润滑机械密封的泄漏率研究"", 《流体机械》 * |
| 白东安等: ""涡轮泵端面密封性能与漏气量影响研究"", 《火箭推进》 * |
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