CN109611374A - A kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structure - Google Patents
A kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structure Download PDFInfo
- Publication number
- CN109611374A CN109611374A CN201910031661.3A CN201910031661A CN109611374A CN 109611374 A CN109611374 A CN 109611374A CN 201910031661 A CN201910031661 A CN 201910031661A CN 109611374 A CN109611374 A CN 109611374A
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- China
- Prior art keywords
- inner core
- type
- metallic matrix
- notch
- labyrinth seal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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- 239000007788 liquid Substances 0.000 title claims abstract description 12
- 239000011159 matrix material Substances 0.000 claims abstract description 24
- 239000002184 metal Substances 0.000 claims abstract description 22
- 229910052751 metal Inorganic materials 0.000 claims abstract description 22
- 238000004826 seaming Methods 0.000 claims abstract description 7
- 238000007789 sealing Methods 0.000 abstract description 22
- 238000009826 distribution Methods 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 description 7
- 230000013011 mating Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 239000003380 propellant Substances 0.000 description 4
- 238000003466 welding Methods 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 238000010894 electron beam technology Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005530 etching Methods 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/165—Sealings between pressure and suction sides especially adapted for liquid pumps
- F04D29/167—Sealings between pressure and suction sides especially adapted for liquid pumps of a centrifugal flow wheel
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of labyrinth seal structure more particularly to a kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structures.In the gap that the structure setting is formed between impeller and the pump case of fixation, the structure includes metallic matrix, the metallic matrix side is connected with pump case, the metallic matrix other side setting L-type places notch, the L-type, which is placed, is arranged nonmetallic inner core on notch, and L-type places notch one end setting lock seaming structure, the other end is placed its nonmetallic inner core detachable L-type that is locked in notch by setting metal platen, and the nonmetallic inner core is arranged multiple seal grooves with impeller contact jaw and matches sealing pair with its impeller convex shoulder.Metallic matrix of the present invention provides overall stiffness, and cooperates with metal platen, pressure- distribution ring border needed for realizing nonmetallic inner core maintenance high stiffness；After sealing pair failure, it is only necessary to nonmetallic inner core is replaced, it is easy to operate, economical.
Description
Technical field
The present invention relates to a kind of labyrinth seal structure more particularly to a kind of cryogenic liquid rocket engine turbopump sandwiches
Formula labyrinth seal structure.
Background technique
In centrifugal pump structure, the high-pressure medium of impeller outlet outflow can be by between the impeller of rotation and the pump case of fixation
The gap of formation is returned to impeller eye, to cause certain internal leakage loss.Rationally to control this partial loss, pump case
It needs to be arranged convex shoulder sealing between impeller and implements current limliting.Convex shoulder sealing structure type can be generally divided into flat ring formula, right-angle type,
Labyrinth type and four kinds of floating ring formula, current limitation effect successively enhances, but the complexity of structure and manufacturing cost are consequently increased.Liquid
In body rocket engine turbopump, for the strict control requirement to loss, it is widely used labyrinth type convex shoulder sealing structure.Together
When, the propellant of liquid-propellant rocket engine is often more special (such as low temperature, Strong oxdiative, deep-etching), the sealing of labyrinth type convex shoulder
Sealing surface material therefor except should it is compatible with propellant in addition to, also needing to cooperatively form rubbing with impeller material, secondary (i.e. abrasion is only
Occur in convex shoulder sealed sides).So far, the way of realization point of the implementation secondary according to friction, the sealing of labyrinth type convex shoulder is non-
Metallic monolith and dissimilar metal combined-type two schemes.
Nonmetallic integrated labyrinth seal scheme is added using the nonmetallic materials integrated machine compatible with propellant, cost
It is low, easy to process, but due to the feature that nonmetallic materials intensity is low, rigidity is weak, constriction coefficient is big, exist during specifically used
Following disadvantage: 1) nonmetallic 2 constriction coefficient is big, and seal clearance substantially reduces under low temperature, and occurs to divide with the positioning surface of pump case 1
From the high pressure zone of action increases, and under the above composite factor effect, easily with impeller 3 locking occurs for sealing ring, and turbine pump is caused to turn
Speed, which reduces, even to be stalled；2) strict control need to be carried out with the screw-down torque of fastener 4 with 1 connection of pump case, it is too big to make to seal
Ring generates severely deformed, and the failure of sealing surface Fast Wearing also easily leads to locking failure when serious, when too small fastener in low temperature and
It is easily loosened under vibration environment, is easy to cause secondary failure；3) in order to realize the higher rigidity of structure, need nonmetallic integrated convex
Shoulder seal uses biggish macro-size, but sealing surface position, once failing, sealing ring is integrally scrapped, and economy is poor；4) it ties
Structure size is bigger, and the rigidity of nonmetallic integrated convex shoulder sealing is smaller, and shrinkage also can be bigger under low temperature, the reliability control of sealing
Difficulty processed increases, therefore is generally only applicable in mesolow power and small structures turbine pump.
Dissimilar metal combined-type labyrinth seal scheme, inner ring use the soft metal (such as copper, silver) with pump media compatibility, outside
Ring use with pump media compatibility, the stronger metal of rigidity similar in constriction coefficient, the two by be welded and fused (as soldering,
Electron beam welding etc.).Compared to nonmetallic integrated scheme, the intensity of dissimilar metal combined-type scheme is higher, rigidity is more preferable and impeller
Contraction matching it is more preferable, can be adapted for the turbine pump of higher pressure and more big structure size.But due to introducing xenogenesis gold
Belong to welding procedure, specifically used there is also some disadvantages in the process: 1) different-metal material welding difficulty is high, and developing early period need to be longer
Technique is known the real situation research, and process stabilizing is also required to the longer period；2) soft metal itself price is high, and production technology is complicated, the period is long,
Whole manufacturing cost is higher；3) weld seam stress is complicated, harsh, and weldquality is more demanding, testing cost height, low efficiency；4) close
Cover can not be repaired after abrasion, can only integral replacing, economy is also poor.
Summary of the invention
To solve the above-mentioned problems, originally practical to provide a kind of cryogenic liquid rocket engine turbopump folder using novel
Core type labyrinth seal structure.
This is practical to use the novel technical solution taken to achieve the above object are as follows:
A kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structure, the structure setting is in impeller and admittedly
In the gap formed between fixed pump case, which includes metallic matrix, and the metallic matrix side is connected with pump case, institute
It states metallic matrix other side setting L-type and places notch, the L-type, which is placed, is arranged nonmetallic inner core on notch, and L-type places notch
One end setting lock seaming structure, the other end by setting metal platen by its nonmetallic inner core it is detachable be locked to L-type placing groove
In mouthful, the nonmetallic inner core is arranged multiple seal grooves with impeller contact jaw and matches sealing pair with its impeller convex shoulder.
It is connected as a further improvement, multiple low-pressure balance holes are arranged on the metallic matrix and place notch with L-type.
As a further improvement, being connected between the metal platen and nonmetallic inner core by flange.
As a further improvement, 4 low-pressure balance holes are arranged on the metallic matrix.
The invention has the following advantages that
1) repertoire is cooperated by metallic matrix, metal platen and nonmetallic inner core three parts and is realized；
2) metallic matrix provides overall stiffness, and cooperates with metal platen, realizes that nonmetallic inner core maintains high stiffness institute
The pressure- distribution ring border needed；
3) nonmetallic inner core realizes sealing pair and friction slave function；
4) constriction coefficient with metallic matrix similar in impeller constriction coefficient and metal platen by determining, seal clearance is convenient for essence
Really control；
5) after sealing pair failure, it is only necessary to nonmetallic inner core is replaced, it is easy to operate, economical；
6) simple production process, controllable without complicated special process.
Detailed description of the invention
Fig. 1 is the structural schematic diagram that convex shoulder seals four kinds.
Fig. 2 is the structural schematic diagram of nonmetallic integrated labyrinth seal.
Fig. 3 is the structural schematic diagram of dissimilar metal combined-type labyrinth seal.
Fig. 4 is structural schematic diagram of the invention.
Specific embodiment
A specific embodiment of the invention is made a detailed explanation with reference to the accompanying drawing.
As shown in figure 4, a kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structure, the structure setting
In the gap that impeller 3 is formed between fixed pump case 1, which includes metallic matrix 6,6 side of metallic matrix
It is connected with pump case 1,6 other side of the metallic matrix setting L-type places notch, is arranged on the L-type placement notch nonmetallic
Inner core 9, and L-type places notch one end setting lock seaming structure 8, the other end is by being arranged metal platen 10 for its nonmetallic inner core 9
The detachable L-type that is locked to is placed in notch, and multiple seal grooves and its leaf is arranged in the nonmetallic inner core 9 and impeller contact jaw
Wheel convex shoulder matches sealing pair.
Metal Substrate 6 external circular diameter φ 150mm, inner circle diameter phi 100mm, thickness 30mm；With the cooperation of nonmetallic inner core 9
Face is evenly distributed the low-pressure balance hole 7 for making a call to four φ 1mm, mating surface diameter phi 116mm, length 18mm；With nonmetallic inner core
Flange fitting surface the diameter phi 140mm, depth 8mm that 9+ metal platen 10 cooperates.Nonmetallic inner core flange excircle diameter phi
140mm, flange thickness 4mm；φ 106mm is taken with metal platen lock seaming mating surface diameter, depth takes 4.5mm；With metallic matrix
Mating surface diameter takes φ 116mm, length 18mm；φ 106mm is taken with the mating surface diameter of metallic matrix lock seaming, depth takes 4.5mm；
φ 99mm, length 13mm are taken with impeller convex shoulder mating surface diameter, opens up 3 road sealing grooves along axial direction.Metal platen outside diameter φ
140mm, inner circle diameter phi 100mm, integral thickness 8mm, lock seaming length take 4mm.Impeller convex shoulder outside diameter takes φ 98mm, axial
Length 32mm.
In the course of work, the strong constraint that nonmetallic inner core is lockstitched a border by both ends is limited to contract；Meanwhile it is flat to open up low pressure
Weighing apparatus hole causes the mating surface of nonmetallic inner core and metallic matrix to form low-pressure area, and nonmetallic inner core is relatively high in sealing surface
It under pressure effect, integrally expands outwardly, can effectively avoid the risk being inwardly crushed, and pressure is higher before sealing, rigid amplification is got over
Obviously, it therefore is more suitable for high pressure, uses in large scale turbine pump.The rigidity of nonmetallic inner core is weaker, temperature and pressure effect
Under, deflection is determined by rigidity compared with strong and close with impeller line expansion factor metallic matrix and metal platen completely, convex with impeller
Shoulder at seal clearance and room temperature fit-up gap it is almost the same, it is stronger to the control force of seal clearance.Nonmetallic inner core constraint
In a relatively closed space, it is unlikely to deform under big fastener axial pre tightening force, biggish screwing force can be taken to mend
Repay the axial deformation under low temperature.Work long hours or abnormal conditions cause sealing surface fail after, only replace nonmetallic inner core i.e.
Can, the period is short and relatively inexpensive.
Claims (4)
1. a kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structure, the structure setting is in impeller and fixation
Pump case between in the gap that is formed, it is characterised in that: the structure includes metallic matrix, the metallic matrix side and pump case
Body is connected, and the metallic matrix other side setting L-type places notch, and the L-type, which is placed, is arranged nonmetallic inner core, and L on notch
Type places notch one end setting lock seaming structure, and the other end is locked to by setting metal platen by its nonmetallic inner core is detachable
L-type is placed in notch, and the nonmetallic inner core matches close with the multiple seal grooves of impeller contact jaw setting with its impeller convex shoulder
Envelope is secondary.
2. a kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structure according to claim 1,
It is characterized in that: multiple low-pressure balance holes being set on the metallic matrix and are connected with L-type placement notch.
3. a kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structure according to claim 1,
It is characterized in that: being connected between the metal platen and nonmetallic inner core by flange.
4. a kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structure according to claim 2,
It is characterized in that: 4 low-pressure balance holes is set on the metallic matrix.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910031661.3A CN109611374A (en) | 2019-01-14 | 2019-01-14 | A kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910031661.3A CN109611374A (en) | 2019-01-14 | 2019-01-14 | A kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109611374A true CN109611374A (en) | 2019-04-12 |
Family
ID=66016766
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910031661.3A Pending CN109611374A (en) | 2019-01-14 | 2019-01-14 | A kind of cryogenic liquid rocket engine turbopump sandwich type labyrinth seal structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109611374A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3798449A1 (en) * | 2019-09-24 | 2021-03-31 | Sulzer Management AG | Pump for conveying a fluid |
| CN112983881A (en) * | 2021-05-21 | 2021-06-18 | 星河动力(北京)空间科技有限公司 | Sealing opening ring, liquid rocket engine centrifugal pump and liquid rocket engine |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1535678A (en) * | 1976-04-10 | 1978-12-13 | Wernert Pumpen Gmbh | Ring seals for the shafts of centrifugal machines |
| CA2264996A1 (en) * | 1998-03-06 | 1999-09-06 | Minoru Matsuda | Sealing device for axial flow turbine |
| CN101776152A (en) * | 2010-03-05 | 2010-07-14 | 北京化工大学 | Outside pressurized type dynamic and static pressure gas lubricating and sealing device |
| CN102518819A (en) * | 2011-12-22 | 2012-06-27 | 中国航天科技集团公司第六研究院第十一研究所 | Composite split type high-pressure sealing pair |
| CN202992209U (en) * | 2012-12-08 | 2013-06-12 | 中国航天科技集团公司第六研究院第十一研究所 | Valve core structure of high-pressure sealing pair |
| CN203532314U (en) * | 2013-11-20 | 2014-04-09 | 浙江佳力科技股份有限公司 | Labyrinth impeller ring clearance structure |
| CN206957970U (en) * | 2017-07-17 | 2018-02-02 | 四川三台剑门泵业有限公司 | A kind of centrifugal pump impeller seal structure |
| CN209838757U (en) * | 2019-01-14 | 2019-12-24 | 北京星际荣耀空间科技有限公司 | Sandwich type labyrinth seal structure for low-temperature liquid rocket engine turbine pump |
-
2019
- 2019-01-14 CN CN201910031661.3A patent/CN109611374A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1535678A (en) * | 1976-04-10 | 1978-12-13 | Wernert Pumpen Gmbh | Ring seals for the shafts of centrifugal machines |
| CA2264996A1 (en) * | 1998-03-06 | 1999-09-06 | Minoru Matsuda | Sealing device for axial flow turbine |
| CN1228505A (en) * | 1998-03-06 | 1999-09-15 | 东芝株式会社 | Sealing device for axial flow turbine |
| CN101776152A (en) * | 2010-03-05 | 2010-07-14 | 北京化工大学 | Outside pressurized type dynamic and static pressure gas lubricating and sealing device |
| CN102518819A (en) * | 2011-12-22 | 2012-06-27 | 中国航天科技集团公司第六研究院第十一研究所 | Composite split type high-pressure sealing pair |
| CN202992209U (en) * | 2012-12-08 | 2013-06-12 | 中国航天科技集团公司第六研究院第十一研究所 | Valve core structure of high-pressure sealing pair |
| CN203532314U (en) * | 2013-11-20 | 2014-04-09 | 浙江佳力科技股份有限公司 | Labyrinth impeller ring clearance structure |
| CN206957970U (en) * | 2017-07-17 | 2018-02-02 | 四川三台剑门泵业有限公司 | A kind of centrifugal pump impeller seal structure |
| CN209838757U (en) * | 2019-01-14 | 2019-12-24 | 北京星际荣耀空间科技有限公司 | Sandwich type labyrinth seal structure for low-temperature liquid rocket engine turbine pump |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3798449A1 (en) * | 2019-09-24 | 2021-03-31 | Sulzer Management AG | Pump for conveying a fluid |
| CN112628152A (en) * | 2019-09-24 | 2021-04-09 | 苏尔寿管理有限公司 | Pump for conveying fluids |
| US11493053B2 (en) | 2019-09-24 | 2022-11-08 | Sulzer Management Ag | Pump for conveying a fluid |
| CN112983881A (en) * | 2021-05-21 | 2021-06-18 | 星河动力(北京)空间科技有限公司 | Sealing opening ring, liquid rocket engine centrifugal pump and liquid rocket engine |
| CN112983881B (en) * | 2021-05-21 | 2021-09-17 | 星河动力(北京)空间科技有限公司 | Sealing opening ring, liquid rocket engine centrifugal pump and liquid rocket engine |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190412 |