CN108150227A - Labyrinth gas seals system - Google Patents
Labyrinth gas seals system Download PDFInfo
- Publication number
- CN108150227A CN108150227A CN201611094833.4A CN201611094833A CN108150227A CN 108150227 A CN108150227 A CN 108150227A CN 201611094833 A CN201611094833 A CN 201611094833A CN 108150227 A CN108150227 A CN 108150227A
- Authority
- CN
- China
- Prior art keywords
- stator
- inner ring
- gas seals
- labyrinth gas
- pressure side
- 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
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
-
- 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
- F04D29/083—Sealings especially adapted for elastic fluid pumps
Abstract
The purpose of the present invention is to provide a kind of labyrinth gas seals systems, advantageously reduce and turn adverse effect of the stator gap to engine efficiency in aero-engine runner.Labyrinth gas seals system according to the present invention, it is suitable for adjacent in aero-engine runner turning obturaging for stator in stator, the stator includes stator inner ring and the multiple stator blades for being arranged on the stator inner ring peripheral side, the labyrinth gas seals system includes the labyrinth comb tooth being oppositely arranged with the inner circumferential side of the stator inner ring, wherein, multiple cross sections which is additionally included in the high pressure side setting of the stator inner ring are in the torus of dentation.
Description
Technical field
The present invention relates to obturage system in aero-engine runner.
Background technology
With the development of science and technology, requirement of the modern aeroengine to economy and reliability is higher and higher, aeroplane engine
The performance of each component of machine encounters unprecedented challenge.One of main path for improving aero-engine performance is to improve development
Technology is obturaged, runner internal leakage is reduced, and then improve the efficiency of aero-engine, reduces rate of fuel consumption.Labyrinth gas seals are a kind of
Common densification device, using the sudden expansion and sudden contraction of runner, consuming the kinetic energy of fluid increases flow resistance to limit the non-of fluid leakage
Contact, which is moved, obturages.When fluid passes through comb backlash, upstream fluid pressure is converted into speed energy by throttling action, then in tooth
Intracavitary speed is dissipated by turbulence vortex as thermal energy.Due to its dependable performance, it is simple in structure the features such as, be widely used in the military, people
With in aero-engine.
However, with the continuous improvement of aero-engine performance index, the temperature and pressure ratio of engine interior gradually rise,
The leakage problem of interior streaming system is on the rise, and the requirement to seal performance is also increasingly harsh.Traditional labyrinth gas seals structure leakage rate
It is larger so that engine loss is big, and oil consumption rate is high.
Invention content
The purpose of the present invention is to provide a kind of labyrinth gas seals systems, advantageously reduce and turn quiet in aero-engine runner
Sub- gap is to the adverse effect of engine efficiency.
The optimization of traditional labyrinth gas seals system focuses on shape optimum of comb tooth itself and reduces crown and the diameter of stator inner ring
To the radial clearance of the coating of inner circumferential side, but effect of optimization is limited, and optimizes position and be located on rotating member, to structure design, peace
Full property and reliability propose higher requirement, increase cost.And the thinking of the present invention is, between guarantee turns stator axial direction
Under conditions of gap, with redundant space original below the listrium of blade both sides, increase feature structure in the stator inner ring of stator,
While reducing leakage rate, leakage stream is guided, reduces the influence to mainstream.
Labyrinth gas seals system according to the present invention is suitable for the envelope for turning stator in stator adjacent in aero-engine runner
Sternly, the stator includes stator inner ring and the multiple stator blades for being arranged on the stator inner ring peripheral side, the labyrinth gas seals
System includes the labyrinth comb tooth being oppositely arranged with the inner circumferential side of the stator inner ring, wherein, which further includes
In the high pressure side of the stator inner ring, multiple cross sections of setting are in the torus of dentation.
In one embodiment, which is additionally included in the low-pressure side of the stator inner ring along entire circumferential direction point
Multiple deflectors of cloth, the deflector are used for from the fluid leaked between the inner circumferential side of the comb tooth and the stator inner ring
It is oriented to, so that the flow direction of the fluid of the leakage is intended to the main flow direction that the stator blade limits.
In one embodiment, the height that the torus is protruded from the high-pressure side is not more than the listrium of the stator blade
The distance that relatively described high-pressure side protrudes.
In one embodiment, the cross section of the torus is isosceles trapezoid, radially inner side is the right-angled trapezium at right angle, diameter
Round back helical teeth with circular arc or radially-inwardly inclined parallelogram tooth outward.
In one embodiment, the deflector is aerofoil profile.
In one embodiment, the deflector is the blade profile of compressor guide vane.
In one embodiment, it is arranged in the low-pressure side of the stator inner ring along entire circumferentially distributed multiple deflectors
Deng height, and the listrium from the height that the low-pressure side of the stator inner ring is protruded no more than the stator blade is relative to described
The distance that low-pressure side protrudes.
In one embodiment, the inclination angle on the radially-inwardly inclined side of the round back helical teeth or parallelogram tooth
It is 30 degree to 45 degree.
Increase torus in stator inner ring high pressure side, therefore increase gas leakage on the edge of the radial direction in import stage
Journey resistance flow acts on reference to the axial choked flow of labyrinth comb tooth, is further reduced vent flow.
In addition, increasing multiple deflectors in stator inner ring low-pressure side, change the flow direction of final leakage stream and to the greatest extent may be used
Can be consistent with mainstream, reduce the mixing loss to mainstream.
High pressure side ring body can be limited according to practical structures with low-pressure side deflector and individually be used, and can also be generated and be better than
The root health flow effect of traditional labyrinth gas seals system.
The structure of labyrinth gas seals system according to the present invention is simple, easy to process, under a small amount of structure optimization, reduces leakage
Effectively with leakage stream while stream, various aspects, which reduce, turns quiet leakage loss, promotes engine performance.
Description of the drawings
The above and other features of the present invention, property and advantage will pass through retouching with reference to the accompanying drawings and examples
It states and becomes readily apparent from, wherein：
Fig. 1 is the local main view diagrammatic cross-section according to the labyrinth gas seals system of the present invention.
Fig. 2 is the close-up schematic view of Fig. 1 mesohighs side.
Fig. 3 is the schematic diagram of a modification of embodiment illustrated in fig. 2.
Fig. 4 is the schematic diagram of another modification of embodiment illustrated in fig. 2.
Fig. 5 is the schematic diagram of another modification of embodiment illustrated in fig. 2.
Fig. 6 is not increase the schematic diagram of the streamline of deflector in low-pressure side.
Fig. 7 is the streamline schematic diagram of the low-pressure side with deflector.
Fig. 8 is the side view of the low-pressure side of stator inner ring in Fig. 1.
Fig. 9 is the on high-tension side side view of stator inner ring in Fig. 1.
The low-pressure side of stator inner ring, on high-tension side streamline schematic diagram when Figure 10 is work.
Figure 11 is the local main view diagrammatic cross-section of existing labyrinth gas seals system.
Specific embodiment
With reference to specific embodiments and the drawings, the invention will be further described, elaborates in the following description more
Details to facilitate a thorough understanding of the present invention, still the present invention obviously can be come with a variety of other manners different from this description it is real
It applies, those skilled in the art can make similar popularization according to practical situations without violating the connotation of the present invention, drill
It unravels silk, therefore should not be limited the scope of the invention with the content of this specific embodiment.
It should be noted that attached drawing is only as an example, it is drawn according to the condition of equal proportion, and should not
This is construed as limiting in this, as the protection domain to actual requirement of the present invention.
Stator inner ring, comb ring gear do not show its hatching in such as Fig. 1,11, and entire comb can more be well understood in this way
Tooth obturages system.
With initial reference to Figure 11, existing labyrinth gas seals system that Figure 11 is shown.Comb tooth envelope according to the present invention is shown in Fig. 1
Tight system.Embodiment shown in FIG. 1 can be considered as the improvement carried out on the basis of the labyrinth gas seals system shown in Figure 11.Scheming
In 11, labyrinth gas seals system is illustrated by taking the quiet rotor of compressor as an example.As shown in figure 11, labyrinth gas seals system is suitable for pair
Stator 1 is obturaged, and stator 1 includes stator inner ring 12 and multiple stator blades in the setting of the peripheral side of stator inner ring 12
11, comb ring gear 13 corresponding thereto is additionally provided in the radially inner circumference side of stator inner ring 12, air-flow is made in the suction that rotor 2 generates
Rotor 2 is reached again across stator 1 with lower.There are axial gap 16 between rotor 2 and stator 1, due to the side gas close to rotor 2
Pressure is higher than the air pressure of the opposite side of stator, even if obturaging there are comb ring gear 13, but it is limited to the structure of comb ring gear 13, exist
Leakage rate, the leakage rate are enough to bring loss to engine, cause the problem of oil consumption rate is high, air-flow is readily along shown in figure
Flow path leakage shown in dotted line.
Fig. 1 is also to be illustrated by taking the stator of compressor as an example, but the present invention is not limited to be suitable for compressor.Such as Fig. 1 institutes
Show, labyrinth gas seals system according to the present invention is suitable for a stator, and the stator includes stator inner ring 32 and is arranged on stator
Multiple stator blades 312 of 32 peripheral side of inner ring, the labyrinth gas seals system include being oppositely arranged with the inner circumferential side of stator inner ring 32
Labyrinth comb tooth 33, be additionally included in stator inner ring high pressure side 32a setting multiple cross sections be in dentation torus
321.Three torus 321 are shown in Fig. 1, the horizontal section of labyrinth gas seals system are shown in Fig. 1, therefore illustrate only
The cross face shape of torus 321.Fig. 9 show stator inner ring 32 high-pressure side 32a and three torus 321 thereon it is complete
Looks.Meanwhile the labyrinth gas seals system is additionally included in multiple deflectors 322 of the low-pressure side 32b settings of stator inner ring 32, deflector
322 can also be referred to as guide vane, be used for from the fluid leaked between the inner circumferential side of comb tooth 33 and stator inner ring 32 into
Row is oriented to, so that the flow direction of the fluid of leakage is intended to the main flow direction of the restriction of stator blade 31.
Although the labyrinth gas seals system of Fig. 1 show stator inner ring 32 low-pressure side 32b set deflector 322 and
High-pressure side 32a sets torus 321, it is worth mentioning at this point that, even if torus 321, deflector 322 select a setting, can also produce
The flow effect of the raw labyrinth gas seals system better than shown in Figure 11.
As shown in Fig. 2, the cross section of torus 321 is isosceles trapezoid, the height H1 of high-pressure side 32a is protruded from generally not
Listrium 310 more than stator blade 31 protrudes from the distance L1 of high-pressure side 32a, that is, increase torus 321 after, after still ensure original
There is the axial gap turned between stator, reduce torus 321 and touch mill risk with adjacent rotor tongue-and-groove, ensure safety of structure.Tooth
Intercuspal space is defined as L1-H1, typically no less than 0, and smaller effect of obturaging is better, usually 0.2mm-0.5mm.Torus 321
The facewidth B in cross section is generally equal with the high H1 of tooth, with specific reference to actually can the situation of processing determine.The quantity of torus 321 according to
Practical structures limit, generally 2-4.
The cross section tooth-shape structure of torus 321 is not limited to a kind of comb tooth type, as shown in figure 3, oblique type tooth can be used
321a is to the inclined parallelogram of radially inner side.As shown in figure 4, it can also use right-angled trapezium helical teeth 321b, directly
The radially inner side of the trapezoidal helical teeth 321b in angle is right angle, and the angle [alpha] of bevel edge is usually 30 ° -45 °.As shown in figure 5, for Fig. 3 or
Person's modification shown in Fig. 4 can increase fillet meeting air-flow side, form round back helical teeth or round back straight-tooth.
It returns to Fig. 2 and referring concurrently to Figure 10, several torus 321 is set in the high pressure side 32a of stator inner ring 32, it can
To increase the on-way resistance of the radial direction of leak fluid, each torus 321 can be that contour degree designs.
Fig. 1 is returned to, the low-pressure side 32b i.e. left side of stator inner ring 32 is schemed along multiple deflectors 322 are entirely circumferentially provided with
8 show whole low-pressure side 32b and multiple deflectors 322.Deflector 322 for guide by comb tooth 33 will be with
The leakage stream of mainstream blending.The quantity of deflector 322, such as the domain according to structure limited case, can be set to be evenly distributed with 20-30
It is a.Each deflector 322 can be that contour degree designs.
In addition, touching mill risk to reduce, ensure safety of structure, deflector 322 protrudes from the height H2 of low-pressure side 32b not
It is more than or the distance L2, i.e. H2 ＜ or=L2 of low-pressure side 32b is protruded from not less than 31 edge of listrium, ensures between original axial direction
Gap ensures safety of structure.Deflector 322 may be configured as aerofoil profile, reduce windage loss, and compressor guide vane leaf can be used
Type.
As shown in fig. 6, being not provided in the case of deflector, leakage stream flowing is mixed and disorderly unordered, and blending damage will be generated into mainstream
It loses.
Fig. 7 shows the flow direction of the leak fluid by water conservancy diversion, is shown by dotted line with the arrow, reality with the arrow
Line shows that mainstream is circumferentially tangential, and the two reaches unanimity.It can be seen that after addition deflector, leakage stream flow direction obtains effectively
Control, produces similar to mainstream circumferential tangential, effectively reduces mixing loss, reducing leakage stream influences mainstream, water conservancy diversion
The angle of plate 322 is according to being calculated.
Although the present invention is disclosed as above with preferred embodiment, it is not for limiting the present invention, any this field skill
Art personnel without departing from the spirit and scope of the present invention, can make possible variation and modification.Therefore, it is every without departing from
The content of technical solution of the present invention, any modification that technical spirit according to the present invention makees above example, equivalent variations
And modification, it each falls within the protection domain that the claims in the present invention are defined.
Claims (8)
1. labyrinth gas seals system, it is suitable for adjacent in aero-engine runner turning obturaging for stator in stator, the stator packet
Include stator inner ring and the multiple stator blades for being arranged on the stator inner ring peripheral side, the labyrinth gas seals system include with it is described
The labyrinth comb tooth that the inner circumferential side of stator inner ring is oppositely arranged, which is characterized in that the labyrinth gas seals system is additionally included in described quiet
Multiple cross sections of the high pressure side setting of sub- inner ring are in the torus of dentation.
2. labyrinth gas seals system as described in claim 1, which is characterized in that be additionally included in the low-pressure side of the stator inner ring
Along entire circumferentially distributed multiple deflectors, the deflector be used for from the inner circumferential side of the comb tooth and the stator inner ring it
Between the fluid that leaks be oriented to so that the flow direction of the fluid of the leakage is intended to the mainstream that the stator blade limits
Direction.
3. labyrinth gas seals system as described in claim 1, which is characterized in that the height that the torus is protruded from the high-pressure side
Degree is no more than the distance that the relatively described high-pressure side of the listrium of the stator blade protrudes.
4. labyrinth gas seals system as described in claim 1, which is characterized in that the cross section of the torus for isosceles trapezoid,
Radially inner side is the round back helical teeth of right-angled trapezium, radial outside with circular arc at right angle or radially-inwardly inclined parallel four
Side shape tooth.
5. labyrinth gas seals system as claimed in claim 2, which is characterized in that the deflector is aerofoil profile.
6. labyrinth gas seals system as claimed in claim 2, which is characterized in that the deflector is the leaf of compressor guide vane
Type.
7. labyrinth gas seals system as claimed in claim 2, which is characterized in that in the low-pressure side of the stator inner ring along entire
Circumferentially distributed multiple deflectors are arranged to wait height, and the height protruded from the low-pressure side of the stator inner ring is not more than institute
State the distance that the listrium of stator blade is protruded relative to the low-pressure side.
8. labyrinth gas seals system as claimed in claim 4, which is characterized in that the circle back helical teeth or parallelogram
The inclination angle on the radially-inwardly inclined side of tooth is 30 degree to 45 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611094833.4A CN108150227A (en) | 2016-12-02 | 2016-12-02 | Labyrinth gas seals system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611094833.4A CN108150227A (en) | 2016-12-02 | 2016-12-02 | Labyrinth gas seals system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108150227A true CN108150227A (en) | 2018-06-12 |
Family
ID=62469640
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611094833.4A Pending CN108150227A (en) | 2016-12-02 | 2016-12-02 | Labyrinth gas seals system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108150227A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2931714A1 (en) * | 1979-07-05 | 1981-01-15 | Bbc Brown Boveri & Cie | Contactless labyrinth seal assembly - has S=shaped sealing strips and comb-pieces with edges inclined to each other |
| US20070224035A1 (en) * | 2005-09-16 | 2007-09-27 | General Electric Company | Angel wing seals for turbine blades and methods for selecting stator, rotor and wing seal profiles |
| US20100074734A1 (en) * | 2008-09-25 | 2010-03-25 | Siemens Energy, Inc. | Turbine Seal Assembly |
| CN106460538A (en) * | 2014-04-08 | 2017-02-22 | 赛峰直升机发动机公司 | Turbine engine compressor with variable-pitch blades |
-
2016
- 2016-12-02 CN CN201611094833.4A patent/CN108150227A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2931714A1 (en) * | 1979-07-05 | 1981-01-15 | Bbc Brown Boveri & Cie | Contactless labyrinth seal assembly - has S=shaped sealing strips and comb-pieces with edges inclined to each other |
| US20070224035A1 (en) * | 2005-09-16 | 2007-09-27 | General Electric Company | Angel wing seals for turbine blades and methods for selecting stator, rotor and wing seal profiles |
| US20100074734A1 (en) * | 2008-09-25 | 2010-03-25 | Siemens Energy, Inc. | Turbine Seal Assembly |
| CN106460538A (en) * | 2014-04-08 | 2017-02-22 | 赛峰直升机发动机公司 | Turbine engine compressor with variable-pitch blades |
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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 |
Application publication date: 20180612 |
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| RJ01 | Rejection of invention patent application after publication |