CN205743995U - Overall guider and aero-engine - Google Patents
Overall guider and aero-engine Download PDFInfo
- Publication number
- CN205743995U CN205743995U CN201620629727.0U CN201620629727U CN205743995U CN 205743995 U CN205743995 U CN 205743995U CN 201620629727 U CN201620629727 U CN 201620629727U CN 205743995 U CN205743995 U CN 205743995U
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- Prior art keywords
- thermal stress
- stress release
- guider
- groove
- internal ring
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- 230000008646 thermal stress Effects 0.000 claims abstract description 114
- 239000000567 combustion gas Substances 0.000 claims abstract description 20
- 238000005452 bending Methods 0.000 claims abstract description 16
- 239000007789 gas Substances 0.000 claims abstract description 14
- 210000002421 cell wall Anatomy 0.000 claims abstract description 12
- 230000004260 plant-type cell wall biogenesis Effects 0.000 claims abstract description 4
- 230000008859 change Effects 0.000 claims description 2
- 230000006870 function Effects 0.000 description 9
- 230000008901 benefit Effects 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 230000008642 heat stress Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000003990 capacitor Substances 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 210000004907 gland Anatomy 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003079 width control Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a kind of overall guider and aero-engine.Overall guider, including turbine internal ring, turbine outer ring and be supported in the turbo blade between turbine internal ring and turbine outer ring, turbine internal ring is on the position between adjacent two turbo blades and offers least one set for by fluting release thermal stress the thermal stress release groove obturaging to reduce gas leakage by the cell wall formation combustion gas of bending；Thermal stress release groove is along the radial distribution of turbine internal ring and is surrounded in the outside wall surface of turbine internal ring, and the cell wall of thermal stress release groove is fold-line-shaped or curvilinear bending distribution.Thermal stress release groove by being arranged to fold-line-shaped or shaped form by cell wall, thus forms the cell wall of bending, utilizes the cell wall of bending to intercept combustion gas, forms combustion gas and obturage function.Thermal stress release groove is provided simultaneously with thermal stress release and combustion gas is obturaged dual-use function, ensures the serviceability of aero-engine while improving overall guider service life.
Description
Technical field
This utility model relates to aero-engine modular construction technical field, especially, relates to a kind of overall guider.This
Outward, this utility model further relates to a kind of aero-engine including above-mentioned overall guider.
Background technology
The middle-size and small-size auxiliary power of aero-engine or the nozzle ring of starter many employings one piece casting structure, due to whole
The typically no cooling structure of body guider and the temperature born are high, and overall guider works long hours at high temperature under high pressure, whole
The temperature that the inner and outer ring of body guider is born is inconsistent with pressure, is easily caused crackle.In order to improve making of overall guider
With the life-span, need between guider internal ring blade, to have thermal stress release groove with the temperature born between balance inner and outer ring
With pressure.
The thermal stress release groove offered at present is generally orthoscopic thermal stress release groove.Orthoscopic thermal stress release groove is deposited
Deficiency following: owing to the internal ring of guider is generally also a part for electromotor inner flow passage, opening straight line heat on runner should
Power release groove combustion gas easily leaks at fluting, owing to orthoscopic thermal stress release groove is not obturaged function, therefore for starting
Machine performance is disadvantageous.
Utility model content
This utility model provides a kind of overall guider and aero-engine, to solve existing nozzle ring by straight
Wire type thermal stress release groove balances temperature and the pressure that inner and outer ring is born, and opens straight line thermal stress release groove on runner, combustion
Air-capacitor easily leaks at fluting, and owing to orthoscopic thermal stress release groove is not obturaged function, it is unfavorable to cause for engine performance
The technical problem of impact.
According to an aspect of the present utility model, it is provided that a kind of overall guider, including turbine internal ring, turbine outer ring and
Being supported in the turbo blade between turbine internal ring and turbine outer ring, turbine internal ring is on the position between adjacent two turbo blades
Offer least one set for obturaging to reduce combustion gas and let out by fluting release thermal stress and by the cell wall formation combustion gas of bending
The thermal stress release groove of leakage；Thermal stress release groove is along the radial distribution of turbine internal ring and is surrounded in the outside wall surface of turbine internal ring,
The cell wall of thermal stress release groove is fold-line-shaped or curvilinear bending distribution.
Further, thermal stress release groove includes along the axial groove section of turbine internal ring axial distribution and along turbine inner circumference
To the circumferential slot section of distribution, axial groove section distributes alternately with circumferential slot section and end to end connects.
Further, thermal stress release groove ring outer surface in turbine curved wave distribution.
Further, thermal stress release groove ring outer surface in turbine is the distribution of broken line wave.
Further, the groove width of thermal stress release groove is 0.1mm-0.2mm.
Further, the groove width of thermal stress release groove is wide；Or the groove width of thermal stress release groove for gradually broadening or
Become narrow gradually or gradually broaden and become narrow gradually alternate.
Further, it is provided with one group of thermal stress release groove or organizes thermal stress more between same group of adjacent two turbo blades
Release groove.
Further, part turbine internal ring being between adjacent two turbo blades is equipped with thermal stress release groove.
Further, part turbine internal ring being between adjacent two turbo blades is interval with thermal stress release groove.
According to another aspect of the present utility model, additionally providing a kind of aero-engine, it includes above-mentioned overall guider.
This utility model has the advantages that
This utility model entirety guider, releases by offering thermal stress on the turbine internal ring between adjacent two turbo blades
The mode putting groove carries out the release of turbine internal ring thermal stress, in order to balance the temperature between turbine internal ring and turbine outer ring and pressure
Power, thus improve the service life of overall guider.Thermal stress release groove by cell wall being arranged to fold-line-shaped or shaped form,
Thus form the cell wall of bending, utilize the cell wall of bending to intercept combustion gas, form combustion gas and obturage function.Thermal stress release groove has simultaneously
Standby thermal stress release and combustion gas are obturaged dual-use function, ensure aero-engine while improving overall guider service life
Serviceability.
In addition to objects, features and advantages described above, this utility model also has other purpose, feature and excellent
Point.Below with reference to figure, this utility model is described in further detail.
Accompanying drawing explanation
The accompanying drawing of the part constituting the application is used for providing being further appreciated by of the present utility model, of the present utility model
Schematic description and description is used for explaining this utility model, is not intended that improper restriction of the present utility model.At accompanying drawing
In:
Fig. 1 is the structural representation of the overall guider of this utility model preferred embodiment；
Fig. 2 is the structural representation of the turbine internal ring of this utility model preferred embodiment；
Fig. 3 is one of structural representation of thermal stress release groove of this utility model preferred embodiment；
Fig. 4 is the two of the structural representation of the thermal stress release groove of this utility model preferred embodiment；
Fig. 5 is the three of the structural representation of the thermal stress release groove of this utility model preferred embodiment.
Marginal data:
1, turbine internal ring；2, turbine outer ring；3, turbo blade；4, thermal stress release groove；401, axial groove section；402, circumference
Groove section.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail, but this utility model can be by following
The multitude of different ways limiting and covering is implemented.
Fig. 1 is the structural representation of the overall guider of this utility model preferred embodiment；Fig. 2 is that this utility model is preferred
The structural representation of the turbine internal ring of embodiment；Fig. 3 is that the structure of the thermal stress release groove of this utility model preferred embodiment is shown
One of it is intended to；Fig. 4 is the two of the structural representation of the thermal stress release groove of this utility model preferred embodiment；Fig. 5 is this practicality
The three of the structural representation of the thermal stress release groove of novel preferred embodiment.
As it is shown in figure 1, the overall guider of the present embodiment, including turbine internal ring 1, turbine outer ring 2 and be supported in turbine
Turbo blade 3 between internal ring 1 and turbine outer ring 2, turbine internal ring 1 is on the position between adjacent two turbo blades 3 and offers
There is least one set for discharging thermal stress by fluting and obturaging to reduce gas leakage by the cell wall formation combustion gas of bending
Thermal stress release groove 4；Thermal stress release groove 4 is along the radial distribution of turbine internal ring 1 and is surrounded in the outside wall surface of turbine internal ring 1,
The cell wall of thermal stress release groove 4 is fold-line-shaped or curvilinear bending distribution.This utility model entirety guider, by phase
The mode offering thermal stress release groove 4 on turbine internal ring 1 between adjacent two turbo blades 3 carries out releasing of turbine internal ring 1 thermal stress
Put, in order to balance the temperature and pressure between turbine internal ring 1 and turbine outer ring 2, thus improve the service life of overall guider.
Thermal stress release groove 4 by being arranged to fold-line-shaped or shaped form by cell wall, thus forms the cell wall of bending, utilizes the groove of bending
Wall intercepts combustion gas, forms combustion gas and obturages function.Thermal stress release groove 4 is provided simultaneously with thermal stress release and combustion gas is obturaged dual merit
Can, while improving overall guider service life, ensure the serviceability of aero-engine.
As depicted in figs. 1 and 2, in the present embodiment, it is axial that thermal stress release groove 4 includes along turbine internal ring 1 axial distribution
Groove section 401 and along the circumferentially distributed circumferential slot section 402 of turbine internal ring 1.Axial groove section 401 distributes alternately with circumferential slot section 402
And end to end connection.Distributed alternately with circumferential slot section 402 by axial groove section 401 and the end to end formation thermal stress that connects is released
Put passage, to balance the temperature between turbine internal ring 1 and turbine outer ring 2 and pressure；Formed combustion gas by circumferential slot section 402
The obstruction of flowing, forms combustion gas and obturages function, it is ensured that the serviceability of aero-engine.By adjust axial groove section 401 and/or
The size of circumferential slot section 402 and quantity control the speed of gas leakage, thus drop while reducing overall guider thermal stress
The impact that low gas leakage brings.
As it is shown on figure 3, in the present embodiment, thermal stress release groove 4 is distributed at the turbine internal ring 1 curved wave of outer surface.Logical
Cross curved wave distributed heat stress relief grooves 4 and form thermal stress release channel, with balance turbine internal ring 1 and turbine outer ring 2 it
Between temperature and pressure；The thermal stress release groove 4 bending wall body being distributed by curved wave forms the resistance to fuel gas flow
Hinder, form combustion gas and obturage function, it is ensured that the serviceability of aero-engine.By adjusting size and the quantity control of arc wave
The speed of gas leakage processed, thus reduce, while reducing overall guider thermal stress, the impact that gas leakage brings.
As shown in Figure 4, in the present embodiment, thermal stress release groove 4 is the distribution of broken line wave at turbine internal ring 1 outer surface.Logical
Cross and form thermal stress release channel in broken line wave distributed heat stress relief grooves 4, with balance turbine internal ring 1 and turbine outer ring 2 it
Between temperature and pressure；The resistance to fuel gas flow is formed by the thermal stress release groove 4 bending wall body being distributed in broken line wave
Hinder, form combustion gas and obturage function, it is ensured that the serviceability of aero-engine.By adjusting size and the quantity control of broken line wave
The speed of gas leakage processed, thus reduce, while reducing overall guider thermal stress, the impact that gas leakage brings.
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4 and Fig. 5, in the present embodiment, the groove width of thermal stress release groove 4 is 0.1mm-
0.2mm.Narrow thermal stress release groove 4 cannot discharge thermal stress, thus is unable to reach balance turbine internal ring 1 and turbine outer ring 2
Between temperature and the purpose of pressure；Although wide thermal stress release groove 4 can discharge thermal stress, but cannot play combustion
The function that sealing gland is tight, causes gas leakage amount excessive, thus has influence on the service behaviour sending out aero-engine.Should by adjusting heat
The groove width of power release groove 4 controls gas leakage speed, thus reduces gas leakage band while reducing overall guider thermal stress
The impact come.
As shown in Figure 1, Figure 2, Figure 3 and Figure 4, in the present embodiment, the groove width of thermal stress release groove 4 is wide.Alternatively, heat
The groove width of stress relief grooves 4 is for gradually to broaden.Alternatively, the groove width of thermal stress release groove 4 is for becoming narrow gradually.Alternatively, heat should
The groove width of power release groove 4 is for gradually broadening and becoming narrow gradually alternate, as shown in Figure 5.Groove width by thermal stress release groove 4
Change control gas leakage speed, thus while reducing overall guider thermal stress, reduce the impact that gas leakage brings.
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4 and Fig. 5, in the present embodiment, it is provided with between same group of adjacent two turbo blades 3
One group of thermal stress release groove 4 or many group thermal stress release grooves 4.Size according to overall guider and adjacent two turbines
Spacing between blade 3 selects to arrange the thermal stress release groove 4 of varying number, thus reaches to discharge thermal stress, in balance turbine
Temperature between ring 1 and turbine outer ring 2 and the purpose of pressure.
In the present embodiment, part turbine internal ring 1 being between adjacent two turbo blades 3 is equipped with thermal stress release groove
4.Size according to overall guider selects different thermal stress release groove 4 set-up modes, thus reaches to discharge thermal stress,
Temperature between balance turbine internal ring 1 and turbine outer ring 2 and the purpose of pressure.
In the present embodiment, part turbine internal ring 1 being between adjacent two turbo blades 3 is interval with thermal stress release
Groove 4.Size according to overall guider selects different thermal stress release groove 4 set-up modes, thus reaches release heat and answer
Power, the temperature between balance turbine internal ring 1 and turbine outer ring 2 and the purpose of pressure.
The aero-engine of the present embodiment, including above-mentioned overall guider.
During enforcement, it is provided that the thermal stress release groove of a kind of sinuous formula is applied on the turbine internal ring of overall guider, such as figure
1, shown in 2,3,4,5.As depicted in figs. 1 and 2, the formula thermal stress release groove (thermal stress release groove 4) that wriggles is by multistage for architectural feature
The long straightway (axial groove section 401) turned back forms with short lines section (circumferential slot section 402), long straightway (axial groove section 401)
Joining end to end with short lines section (circumferential slot section 402) and be mutually perpendicular to, segment length's straightway (axial groove section 401) is with two sections short directly
Line segment (circumferential slot section 402) composition one " hollow " groove, whole sinuous formula thermal stress release groove (thermal stress release groove 4) have two to
Three groups of " hollow " groove compositions, the number of " hollow " groove is determined by the width of guider internal ring.Wriggling, (heat should for formula thermal stress release groove
Power release groove 4) overall width is consistent with the width of short lines section (circumferential slot section 402), the spacing of turbo blade 3 determines.Wriggle
The groove width general control of Yan formula thermal stress release groove (thermal stress release groove 4) is between 0.1mm～0.2mm.At work bar
Under part, " hollow " groove effect of obturaging to combustion gas of the formula thermal stress release groove (thermal stress release groove 4) that wriggles.Therefore, this structure
Also the impact that leakage brings is reduced while reducing guider thermal stress.
Long straightway (axial groove section 401) joins end to end with short lines section (circumferential slot section 402) and is mutually perpendicular to, a segment length
Straightway (axial groove section 401) and two sections of short lines section (circumferential slot section 402) one " hollow " grooves of composition.Formula thermal stress of wriggling is released
Put groove (thermal stress release groove 4) to be made up of two to three groups " hollow " groove.Wriggle formula thermal stress release groove (thermal stress release groove 4)
Groove width general control is between 0.1～0.2.Use and wriggle formula thermal stress release groove compared with orthoscopic thermal stress release groove
Have the advantage that the long straightway (axial groove section 401) by " hollow " groove and short lines section (circumferential slot section 402) size are with individual
Several and sinuous formula thermal stress release groove groove width controls leakage so that also reduce while reducing guider thermal stress
The impact that leakage brings.Using, on certain series auxiliary power, the formula thermal stress release groove that wriggles, empirical tests can improve to be sent out
The life-span of motivation.
The foregoing is only preferred embodiment of the present utility model, be not limited to this utility model, for this
For the technical staff in field, this utility model can have various modifications and variations.All in spirit of the present utility model and principle
Within, any modification, equivalent substitution and improvement etc. made, within should be included in protection domain of the present utility model.
Claims (10)
1. an overall guider, including turbine internal ring (1), turbine outer ring (2) and be supported in described turbine internal ring (1) and institute
State the turbo blade (3) between turbine outer ring (2),
It is characterized in that,
Described turbine internal ring (1) is in described in adjacent two on the position between turbo blade (3) and offers least one set for leading to
Cross fluting release thermal stress and obturage to reduce the thermal stress release groove (4) of gas leakage by the cell wall formation combustion gas of bending；
Described thermal stress release groove (4) is along the radial distribution of described turbine internal ring (1) and is surrounded on outside described turbine internal ring (1)
On wall,
The cell wall of described thermal stress release groove (4) is fold-line-shaped or curvilinear bending distribution.
Overall guider the most according to claim 1, it is characterised in that
Described thermal stress release groove (4) includes along the axial groove section (401) of described turbine internal ring (1) axial distribution and along described
The circumferential slot section (402) that turbine internal ring (1) is circumferentially distributed,
Described axial groove section (401) distributes alternately with described circumferential slot section (402) and end to end connects.
Overall guider the most according to claim 1, it is characterised in that
Described thermal stress release groove (4) is distributed at described turbine internal ring (1) the curved wave of outer surface.
Overall guider the most according to claim 1, it is characterised in that
Described thermal stress release groove (4) is the distribution of broken line wave at described turbine internal ring (1) outer surface.
Overall guider the most according to any one of claim 1 to 4, it is characterised in that
The groove width of described thermal stress release groove (4) is 0.1mm-0.2mm.
Overall guider the most according to claim 5, it is characterised in that
The groove width of described thermal stress release groove (4) is wide；Or
The groove width of described thermal stress release groove (4) alternately becomes with becoming narrow gradually for gradually broadening or becoming narrow gradually or gradually broaden
Change.
Overall guider the most according to any one of claim 1 to 4, it is characterised in that
It is provided with thermal stress release groove (4) described in a group described in same group between adjacent two turbo blades (3) or many groups are described
Thermal stress release groove (4).
Overall guider the most according to any one of claim 1 to 4, it is characterised in that
The part being on described turbine internal ring (1) described in adjacent two between turbo blade (3) is equipped with the release of described thermal stress
Groove (4).
Overall guider the most according to any one of claim 1 to 4, it is characterised in that
The part being on described turbine internal ring (1) described in adjacent two between turbo blade (3) is interval with described thermal stress and releases
Put groove (4).
10. an aero-engine, it is characterised in that include the overall guider according to any one of claim 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620629727.0U CN205743995U (en) | 2016-06-23 | 2016-06-23 | Overall guider and aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620629727.0U CN205743995U (en) | 2016-06-23 | 2016-06-23 | Overall guider and aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205743995U true CN205743995U (en) | 2016-11-30 |
Family
ID=57384199
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620629727.0U Active CN205743995U (en) | 2016-06-23 | 2016-06-23 | Overall guider and aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205743995U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108005792A (en) * | 2017-11-06 | 2018-05-08 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of air turbine starter turbine stage arrangement |
| CN112490844A (en) * | 2020-11-26 | 2021-03-12 | 苏州长光华芯光电技术股份有限公司 | Bar laser packaging structure and preparation method thereof |
| CN116857021A (en) * | 2023-09-04 | 2023-10-10 | 成都中科翼能科技有限公司 | Disconnect-type turbine guide vane |
-
2016
- 2016-06-23 CN CN201620629727.0U patent/CN205743995U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108005792A (en) * | 2017-11-06 | 2018-05-08 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of air turbine starter turbine stage arrangement |
| CN112490844A (en) * | 2020-11-26 | 2021-03-12 | 苏州长光华芯光电技术股份有限公司 | Bar laser packaging structure and preparation method thereof |
| CN116857021A (en) * | 2023-09-04 | 2023-10-10 | 成都中科翼能科技有限公司 | Disconnect-type turbine guide vane |
| CN116857021B (en) * | 2023-09-04 | 2023-11-14 | 成都中科翼能科技有限公司 | Disconnect-type turbine guide vane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee after: AECC HUNAN AVIATION POWERPLANT Research Institute Country or region after: China Address before: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee before: CHINA AVIATION POWER MACHINERY INSTITUTE Country or region before: China |
|
| CP03 | Change of name, title or address |