CN106932157A - Pressure measuring device is compared in a kind of mechanical end face seal for high velocity liquid oxygen turbopump - Google Patents
Pressure measuring device is compared in a kind of mechanical end face seal for high velocity liquid oxygen turbopump Download PDFInfo
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- CN106932157A CN106932157A CN201710178523.9A CN201710178523A CN106932157A CN 106932157 A CN106932157 A CN 106932157A CN 201710178523 A CN201710178523 A CN 201710178523A CN 106932157 A CN106932157 A CN 106932157A
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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
- G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
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Abstract
A kind of mechanical end face seal for high velocity liquid oxygen turbopump measures end face seal pressure data than pressure measuring device for accurate.The device includes stationary seal ring component, rotating ring, the first axle sleeve, housing, axle, pressurising ozzle, sealing gasket, the second axle sleeve, pressure sensor, the device can not accurately measure the problem than pressing data when overcoming original Seal Design, piston shaft stress balance can be kept, improve certainty of measurement, suitable for rotating speed oxygen turbopump mechanical seal high, various liquids and gases media can be met, it is easy to operate, processing is simple, and adapt to engine condition, the seal face of product testing can be met simultaneously to be tested than pressure, can range of application it is wider.
Description
Technical field
It is that one kind is used for high speed liquid oxygen whirlpool the present invention relates to liquid-propellant rocket engine turbine mechanical seal for pump application field
The mechanical end face seal of wheel pump is mainly used in the rocket engine end face seal of liquid hydrogen liquid oxygen propellant than pressure measuring device
Than pressure measurement experiment.
Background technology
Since 21 century, each spacefaring nation in the world is proposed respective new generation's carrier rocket, hydrogen-oxygen expansion one after another
Circulation rocket engine because its simple system, reliability is high, performance is high, strong adaptability, can repeatedly start the advantages of and abroad
New generation's carrier rocket Upper Stage is widely used.
Hydrogen-oxygen turbine pump is one of core component of hydrogen-oxygen expansion cycles rocket engine, its frequently with seal form have
The forms such as end face seal, labyrinth seal, wherein end face seal leakage rate is small, but has that complex structure, frictional heat amount be big, film
The shortcomings of box deformation is big.Particularly in lox-hydrogen engine turbine pump, to ensure trouble free service, hydrogen-oxygen medium needs helium
Play isolation hydrogen, oxygen medium, but helium lubricity is poor, and it is limited to engine condition, helium end face seal
Without coolant during work, often occur the rising of helium cavity pressure, the larger phenomenon of caloric value in the normal test run of engine.
Helium annular seal space temperature and pressure raises the operating mode substantial deviation design conditions for not only resulting in helium sealing, causes sealing
Performance change, while also there is certain potential safety hazard, temperature is too high to cause helium sealed graphite ring with the stationary seat magnitude of interference not
Foot, makes graphite annulus deviate from fracture from stationary seat, and rotating ring coating produces heavy wear even decrepitation, and hypertonia can be caused
Bellows stress is excessive, is deformed even rupture, can cause helium seal failure, it is impossible to play a part of to completely cut off hydrogen-oxygen medium,
Influence oxygen turbopump functional reliability, and helium consumption can be caused excessive, engine control unsaturated vapor, valve cannot be acted and led
Causing engine cannot shut down or reignition.
It is to use the seal pressure under theoretical formula method not pressurising state that current helium seal pressure is calculated, and chooses warp
Test formula and calculate influence of the sealing cavity pressure to seal pressure, it is impossible to the number of seal pressure under the actual real pressurising state of measurement
Value, therefore seal pressure under operating pressure calculates and there is larger error.When actually used, due to the ratio to helium end face seal
The support without real data is pressed, causes that for annular seal space pressure rise problem accurate quantitative analysis and positioning cannot be carried out,
Effective control measure thus cannot be taken, the phenomenon of annular seal space pressure rise is fundamentally prevented effectively from, cannot also be slapped in detail
Hold the design of end face seal and use.
The content of the invention
Present invention solves the technical problem that being：Cannot actually be measured under real pressurising state for traditional helium end face seal
The numerical value of seal pressure leads to not effectively control the problem of annular seal space pressure rise, it is proposed that one kind is used for high speed liquid oxygen turbine
The mechanical end face seal of pump is capable of the rocket engine end face seal of accurate measurement liquid hydrogen liquid oxygen propellant than pressure measuring device
Than pressure numerical value.
The present invention solves above-mentioned technical problem and is achieved by following technical solution：
A kind of mechanical end face seal for high velocity liquid oxygen turbopump than pressure measuring device, including stationary seal ring component,
Rotating ring, the first axle sleeve, housing, axle, pressurising ozzle, sealing gasket, the second axle sleeve, pressure sensor, its axis are two-part structure,
The piston portion of axis body part including thin segment and thick section, the first axle sleeve and the second axle sleeve are socketed in institute from upper and lower part respectively
State on axis body part, the junction of the first axle sleeve and the second axle sleeve is fixedly connected by sealing gasket with rotating ring, stationary seal ring component
It is fixed on first axle to put, the upper end of housing is fixedly connected with stationary seal ring component, the upper end of rotating ring is tight with stationary seal ring component
Patch, the lower end of housing is connected with piston portion, and housing, stationary seal ring component, the first axle sleeve, the second axle sleeve and piston portion are common
A closed pressurising chamber is surrounded, pressure sensor is located at the bottom of the piston portion, and pressurising ozzle is fixed on hull outside
And connected with the pressurising chamber.
Preferably, with housing for gap coordinates, piston portion diameter should be with stone in end face seal static components for piston portion
The internal diameter of Mo Huan is consistent.
Further, the stationary seal ring component includes stationary ring housing, metal bellows, graphite annulus, and metal bellows is loaded on quiet
In toroidal shell body, graphite annulus is loaded on stationary ring housing lower end, and wherein graphite annulus lower end is connected with rotating ring, and stationary ring housing is connected with housing,
Stationary seal ring component decrement is adjusted by gasket seal.
Present invention advantage compared with prior art is：
(1) present invention solves the problems, such as that existing end face seal cannot be measured than pressure, in traditional theory analysis, end
Face seal pressure is considered as invariable, but the numerical value can be continually changing in actually measurement, with traditional theory analysis
Compare, the present apparatus is made up of pressurising ozzle to by stationary seal ring component, the first axle sleeve, the second axle sleeve, housing and piston portion
Pressurising chamber in inflate, in the case where metallic beUows gauge is continually changing, by axis body part and piston portion to pressure
The numerical value detection of transmission and pressure sensor, realizes the monitor in real time to the pressure being continually changing, and overcomes original sealing and sets
The problem of the seal pressure data that timing can not be measured accurately, compensate for the missing of original data deficiencies.
(2) present invention is coordinated using piston shaft piston portion and housing small―gap suture and ensures that annular seal space builds pressure, it is to avoid O-ring
The friction effects of sealing, the degree of accuracy of measurement is greatly improved.
(3) present invention considers the finished product helium end face seal used in liquid-propellant rocket engine in design.For
Finished product helium is sealed, in order that piston shaft stress balance under high pressure, sealing gasket is selected by calculating default decrement in advance,
Piston diameter is consistent with rotating ring external diameter, has gas to be filled with the case of pressurising, and graphite part is identical with piston portion stress, so disappears
Except the imbalance of piston shaft stress.
(4) the seal pressure measurement apparatus simple structure of present invention design, easy processing, part is generally hardware, can be led to
Excess pressure detects that, compared to O-ring plugging meter method, what the present apparatus can be complete effectively measures in the environment of lower temperature
Device seal pressure, can adapt to subzero 196 degree to all temperature environments in the range of normal temperature, and calculate seal pressure change
Curve, it is adaptable to high velocity liquid oxygen turbopump mechanical end face seal, while the detection of various liquids and gases media can be met.
Brief description of the drawings
Fig. 1 is the helium end face seal that provides of invention than pressure measuring device installation diagram；
The stationary seal ring component drawings that Fig. 2 is provided for invention；
The movable ring structure figure that Fig. 3 is provided for invention；
The main axle structure figure that Fig. 4 is provided for invention；
Specific embodiment
As shown in Figure 1 the present invention include stationary seal ring component 2, rotating ring 3, the first axle sleeve 1, housing 4, axle 5, pressurising ozzle 6,
Sealing gasket 7, the second axle sleeve 8, pressure sensor 9, its axis 5 be two-part structure, including thin segment axis body part and thick section
Piston portion, the first axle sleeve 1 and the second axle sleeve 8 are socketed on the axis body part respectively from upper and lower part, the He of the first axle sleeve 1
The junction of the second axle sleeve 8 is fixedly connected by sealing gasket 7 with rotating ring 3, and the component of stationary seal ring 2 is fixed on the first axle sleeve 1, is moved
The upper end of ring 3 is close to stationary seal ring component 2, and the upper end of housing 4 is fixedly connected with stationary seal ring component 2, the lower end of housing 4 with
The piston portion is connected, and housing 4, stationary seal ring component 2, the first axle sleeve 1, the second axle sleeve 8 and the piston portion enclose jointly
Into a closed pressurising chamber 10, pressurising ozzle 6 is fixed on the outside of housing 4 and is connected with the pressurising chamber 10, pressure sensor 9
Positioned at the bottom of piston portion, piston portion is that gap coordinates with housing, as shown in figure 4, piston portion diameter should with rotating ring 3 outside
Footpath is consistent, and stationary seal ring component 2 as shown in Figure 2 includes stationary ring housing 201, metal bellows 202, the part of graphite annulus 203 3, metal
Loaded in stationary ring housing 201, graphite annulus 203 is loaded on the lower end of stationary ring housing 201, the wherein lower end of graphite annulus 203 and rotating ring to bellows 202
3 are connected, and are illustrated in figure 3 the concrete structure diagram of rotating ring, and stationary ring housing 201 is connected with housing 4, and the decrement of static components 2 passes through
Sealing gasket 7 is adjusted.
The workflow of the present apparatus is as follows：
After the completion of device assembling, by pressurising ozzle 6 to insufflation gas in pressurising chamber 10, in confined space interior sealing stationary ring
Component 2 is acted on by external pressure, and metal bellows 202 can produce axial thrust, thrust to be passed by rotating ring to rotating ring 3 under external pressure
Axis body part is passed, then piston portion is passed to by axis body part, be ultimately transferred to pressure sensor 9, by pressure sensor 9
The pressure data measured of reading, it is close by being calculated by reading the data of different pressurising pressure and pressure sensor 9
Envelope is than line of buckling.
End face seal than press computing formula be
Pb=Psp+ (K- λ) Ps
Wherein Pb is the pressure data that pressure sensor 9 is measured, and Psp is that the ratio pressure that the compression of metal bellows 202 is produced is：
Fm/S；Fm is the compression stress of metal bellows 202, i.e., compress the spring force for causing by metal bellows 202, pre- according to metal bellows 202
First given decrement can be in the hope of arriving, and S is the area of graphite annulus 203 in sealing surface area, i.e. stationary seal ring component 2；Ps is sealing
Absolute value | P1-P2 | of exocoel medium differential pressure in static components 2, i.e. pressurising pressure P1 and atmospheric pressure P2 differences；K- λ are carried for sealing
Lotus coefficient, for characterizing the parameter of different sealing characteristic, different metal bellows 202 has different loading coefficients, and system of load
Number is the characteristic of sealing with change in pressure, therefore can obtain：
K- λ=(Pb-Psp)/Ps
Loading coefficient according to being tried to achieve under different pressurising pressure conditions can obtain seal pressure curve.
The seal pressure curve embodies the relation of stationary seal ring component and operating pressure in the operation of liquid oxygen turbine pump,
Basis is used for the mechanical end face seal of liquid oxygen turbine pump uses to provide than pressure.
Claims (5)
1. pressure measuring device is compared in a kind of mechanical end face seal for high velocity liquid oxygen turbopump, it is characterised in that：Including sealing
Static components (2), rotating ring (3), the first axle sleeve (1), housing (4), axle (5), pressurising ozzle (6), sealing gasket (7), the second axle sleeve
(8), pressure sensor (9), its axis (5) is two-part structure, including axis body part and the thick section of thin segment piston portion,
One axle sleeve (1) and the second axle sleeve (8) are socketed on the axis body part respectively from upper and lower part, the first axle sleeve (1) and second
The junction of axle sleeve (8) is fixedly connected by sealing gasket (7) with rotating ring (3), and stationary seal ring component (2) is fixed on first axle and puts
(1), the upper end of rotating ring (3) is close to stationary seal ring component (2), and the upper end of housing (4) is fixed with stationary seal ring component (2) to be connected
Connect, the lower end of housing (4) is connected with piston portion, housing (4), stationary seal ring component (2), the first axle sleeve (1), the second axle sleeve
(8) and piston portion surrounds a closed pressurising chamber (10) jointly, pressurising ozzle (6) be fixed on housing (4) it is outside and with institute
Pressurising chamber (10) connection is stated, pressure sensor (9) is positioned at the bottom of piston portion.
2. a kind of mechanical end face seal for high velocity liquid oxygen turbopump according to claim 1 is than pressure measuring device,
It is characterized in that：Stationary seal ring component (2) includes stationary ring housing (201), metal bellows (202), graphite annulus (203), metal film
Box (202) loaded in stationary ring housing (201), graphite annulus (203) loaded on stationary ring housing (201) lower end, wherein under graphite annulus (203)
End is connected with rotating ring (3), and stationary ring housing (201) is connected with housing (4).
3. a kind of mechanical end face seal for high velocity liquid oxygen turbopump according to claim 1 and 2 is than pressure measurement dress
Put, it is characterised in that：The piston portion is with housing (4) for gap coordinates.
4. a kind of mechanical end face seal for high velocity liquid oxygen turbopump according to claim 1 and 2 is than pressure measurement dress
Put, it is characterised in that：Described piston portion diameter is consistent with the internal diameter of graphite annulus (203) in end face seal static components (2).
5. a kind of mechanical end face seal for high velocity liquid oxygen turbopump according to claim 1 and 2 is than pressure measurement dress
Put, it is characterised in that：Stationary seal ring component (2) decrement is adjusted by gasket seal (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710178523.9A CN106932157B (en) | 2017-03-23 | 2017-03-23 | Mechanical end face seal specific pressure measuring device for high-speed liquid oxygen turbine pump |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710178523.9A CN106932157B (en) | 2017-03-23 | 2017-03-23 | Mechanical end face seal specific pressure measuring device for high-speed liquid oxygen turbine pump |
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| CN106932157A true CN106932157A (en) | 2017-07-07 |
| CN106932157B CN106932157B (en) | 2023-08-11 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107505216A (en) * | 2017-10-12 | 2017-12-22 | 中国船舶重工集团公司第七0三研究所 | A kind of measure device of seal shaft segment table surface hardness reasonable value |
| CN107939722A (en) * | 2017-11-30 | 2018-04-20 | 北京航天动力研究所 | A kind of oxyhydrogen engine turbine pump is spring-loaded automatic disengaging dynamic sealing device |
| CN110821879A (en) * | 2019-09-30 | 2020-02-21 | 北京航天动力研究所 | Helium flame-retardant sealing structure of turbopump of liquid rocket engine |
| CN112798200A (en) * | 2021-02-01 | 2021-05-14 | 北京航空航天大学 | Micro-leakage graphite sealing leakage measuring method and device |
| 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 |
| CN113970408A (en) * | 2021-04-30 | 2022-01-25 | 北京航天动力研究所 | Mechanical seal end face specific pressure measuring device and method for high-speed turbine pump |
| CN114279610A (en) * | 2021-12-06 | 2022-04-05 | 北京航天动力研究所 | Device and method for measuring specific pressure of mechanical seal end face of turbopump of liquid rocket engine |
| US11333571B2 (en) * | 2019-08-12 | 2022-05-17 | Dalian University Of Technology | Dynamic seal test device for cryogenic fluid medium |
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| CN206683829U (en) * | 2017-03-23 | 2017-11-28 | 北京航天动力研究所 | Pressure measuring device is compared in a kind of mechanical end face seal for high velocity liquid oxygen turbopump |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107505216A (en) * | 2017-10-12 | 2017-12-22 | 中国船舶重工集团公司第七0三研究所 | A kind of measure device of seal shaft segment table surface hardness reasonable value |
| CN107939722A (en) * | 2017-11-30 | 2018-04-20 | 北京航天动力研究所 | A kind of oxyhydrogen engine turbine pump is spring-loaded automatic disengaging dynamic sealing device |
| CN107939722B (en) * | 2017-11-30 | 2024-02-09 | 北京航天动力研究所 | Spring-loaded automatic release type dynamic sealing device for oxyhydrogen engine turbopump |
| US11333571B2 (en) * | 2019-08-12 | 2022-05-17 | Dalian University Of Technology | Dynamic seal test device for cryogenic fluid medium |
| CN110821879A (en) * | 2019-09-30 | 2020-02-21 | 北京航天动力研究所 | Helium flame-retardant sealing structure of turbopump of liquid rocket engine |
| CN112798200A (en) * | 2021-02-01 | 2021-05-14 | 北京航空航天大学 | Micro-leakage graphite sealing leakage measuring method and device |
| 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 |
| CN113970408A (en) * | 2021-04-30 | 2022-01-25 | 北京航天动力研究所 | Mechanical seal end face specific pressure measuring device and method for high-speed turbine pump |
| CN113970408B (en) * | 2021-04-30 | 2024-05-03 | 北京航天动力研究所 | Mechanical seal end face specific pressure measuring device and method for high-speed turbine pump |
| CN114279610A (en) * | 2021-12-06 | 2022-04-05 | 北京航天动力研究所 | Device and method for measuring specific pressure of mechanical seal end face of turbopump of liquid rocket engine |
| CN114279610B (en) * | 2021-12-06 | 2023-07-14 | 北京航天动力研究所 | Device and method for measuring specific pressure of mechanical seal end face of turbopump of liquid rocket engine |
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Inventor after: Wu Lin Inventor after: Yu Binkai Inventor after: Jiang Xuqiang Inventor after: Chu Baoxin Inventor after: Dou Wei Inventor after: Xu Cun Inventor after: Liu Yang Inventor after: Liu Hongjie Inventor after: Li Ming Inventor after: Ye Xiaoming Inventor before: Wu Lin Inventor before: Yu Binkai Inventor before: Jiang Xuqiang Inventor before: Chu Baoxin Inventor before: Dou Wei Inventor before: Xu Cun Inventor before: Liu Yang Inventor before: Liu Hongjie Inventor before: Li Ming Inventor before: Ye Xiaoming |
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