CN207348905U - A kind of case structure with tip clearance control and the flowing control of leaf top - Google Patents
A kind of case structure with tip clearance control and the flowing control of leaf top Download PDFInfo
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- CN207348905U CN207348905U CN201721090471.1U CN201721090471U CN207348905U CN 207348905 U CN207348905 U CN 207348905U CN 201721090471 U CN201721090471 U CN 201721090471U CN 207348905 U CN207348905 U CN 207348905U
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- turbine
- outer ring
- leaf top
- turbulence
- turbine outer
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Abstract
A kind of case structure with tip clearance control and the flowing control of leaf top, turbine casing form first chamber with shock plate, multiple impact openings are defined on shock plate；Turbine outer ring, outer shroud form second chamber with shock plate, multiple turbulence structures, film hole structure and leakage-proof structure are defined on outer shroud；Cold air air-flow enters first chamber via air admission hole, by impacting pore structure into second chamber to impact outer shroud, again via turbulence structure to turbine outer ring carry out it is sufficiently cool, finally flow out to form cooling air film from the film hole structure of outer shroud, finally with mainstream combustion gas mixing；Boss structure on turbine outer ring is mainly used to prevent the formation and development of blade tip leakage vortex.The utility model enhances heat transfer effect of the cooling air-flow inside casing, the turbine casing surface and leaf top position that film hole structure pair is directly contacted with high-temperature fuel gas play preferable cooling effect, leakage-proof structure significantly reduces leaf top leakage loss, improves turbine efficiency.
Description
Technical field
The present invention relates to a kind of turbine casing structure, more particularly to one kind can be applied to aero-engine, gas turbine etc.
The case structure with tip clearance control and the flowing control of leaf top in machinery.
Background technology
With the continuous lifting of gas turbine performance, inlet temperature is continuously improved before turbine, and there is an urgent need to more efficient, more first
Into cooling technology ensure high-temperature component of gas turbine normal work.Turbine casing is as one of high-temperature component, outside its turbine
For ring structure directly with mainstream contacts fuel gas, operating condition is severe, only the resistance to elevated temperatures by material in itself, can not bear height for a long time
The erosion of temperature；Under high temperature action dilatancy occurs for turbine casing at the same time, causes tip clearance to become larger, has seriously affected turbine
Efficiency.In order to ensure the work efficiency of the service life of turbine outer ring and gas turbine, it is necessary to develop the turbine of comprehensive high-efficiency
Casket cooling technology.In existing issued patents, United States Patent (USP) US.5,169,287 cool down skill using the combination of impact opening and air film hole
Art, cooling structure is complicated and cooling effect is not abundant enough, fails the reasonable effective Distribution utilization of cold air.
Due to being subject to the effects such as Long-term Vibration, high temperature corrosion, the improper scraping of turbine blade-tip, turbine outer ring inside coating pole
It is easy to fall off so that turbine casing becomes one of component that repair rate is higher in gas turbine；Discovery is studied at the same time ejects mouth in leaf
Position generally has complicated fluidal texture, which causes flow losses, so as to cause due to the blending of mainstream and leakage stream
Turbine efficiency declines.In order to further improve gas turbine work efficiency, it is necessary to which developing more effective turbine outer ring obturages technology.
In existing issued patents, United States Patent (USP) US.4,213,296 use step seal structure, the tip clearance between integral shroud comb tooth
It is larger, and various turbine blade arrangements cannot be suitable for well, application range is not extensive enough.
Consider turbine casing cooling technology importantly, above-mentioned two patents are simply one-sided or obturage technology, and it is cold
But structure is relative complex, and the type of cooling is relatively easy, and cooling effect is not abundant enough, and seal structure is relatively single, touches mill problem simultaneously
Do not consider.In order to more effectively improve casing cooling effect, reduce leaf top leakage loss, it is necessary to create more preferable casing cooling knot
Structure, finds the leaf top leakage preventing technology of higher.
The content of the invention
Present invention solves the technical problem that it is：It is an object of the invention to propose that a kind of tip clearance that is used for controls and leaf top
The case structure of control is flowed, to solve the problems, such as that existing turbine casing expanded by heating deformation is big and leaf top leakage loss is serious.
The technical scheme is that：A kind of case structure with tip clearance control and the flowing control of leaf top, it is special
Sign is, including turbine casing 1, shock plate 4 and turbine outer ring 6；The turbine casing 1 is integral with shock plate 4, defines two
The chamber formed between person is first chamber 3；Turbine outer ring 6 is couple on turbine casing 1, and turbine outer ring 6 is formed with shock plate 4
Second chamber 7；The shock plate 4 is equipped with some through holes as impact opening 5；Turbine outer ring 6 is equipped with some through holes as gas
Fenestra 9, and turbine outer ring 6 is equipped with some protrusions, as turbulence structure；Turbine outer ring inner surface 10 is equipped with some raised works
For seal structure 12.
The present invention further technical solution be：Some impact openings 5 are into multiple rows of distribution, and multiple rows of impact opening 5 is mutual
It is arranged in parallel or is staggered in arrangement.
The present invention further technical solution be：The angle of plane where 5 axis of impact opening and shock plate is 30 °-
90°。
The present invention further technical solution be：The turbulence structure is turbulence columns or flow-disturbing rib, and wherein turbulence columns are column
Shape is raised, and flow-disturbing rib is strip projected parts.
The present invention further technical solution be：When turbulence structure is turbulence columns, some turbulence columns are in a row distributed,
And be spaced apart with air film hole 9 in a row, and multiple rows of turbulence columns are arranged parallel to or are staggered in arrangement.
The present invention further technical solution be：When turbulence structure is flow-disturbing rib, some flow-disturbing ribs with into exhaust
Fenestra 9 is spaced apart.
The present invention further technical solution be：On the turbine outer ring inner surface 10, part corresponding with blade is equipped with
Material coating 11 can be ground.
Invention effect
The technical effects of the invention are that：1. the cooling structure in turbine casing is simple, handling ease；2. internal cooling side
Formula is various, and turbulence structure considerably increases heat exchange area, improves surface film thermal conductance, so as to strengthen cooling effect；3. whirlpool
Take turns outer shroud film hole structure and form air film in turbine outer ring inner surface, play the role of obstructing high-temperature fuel gas, reach reduction turbine
The effect of outer shroud temperature；4. turbine outer ring seal structure prevents the development of leakage stream, leaf top leakage loss is effectively reduced；⑤
Improved turbine casing structure reduces apart from the center radius of rotation axis, and then reduces the radial deformation of turbine casing；⑥
Cooling effect increase, can reduce cold air dosage, more gases is used for expansion work, improve gas utilization rate；7. outside turbine
Ring inner surface can grind the use of material, prevent the abrasion of leaf top and turbine outer ring, extend the working life of turbine part, at the same time
Tip clearance is reduced, further increases turbine efficiency.
Brief description of the drawings
Fig. 1 is the turbine casing structure radial cross-section of the present invention；
Fig. 2 is the turbine casing three-dimensional structure view of the present invention；
Fig. 3 (a) and Fig. 3 (b) is A-A profile directions shock plate and impact opening structure diagram；
Fig. 4 (a) and Fig. 4 (b) is B-B profile direction turbine outer ring structure diagrams；
Fig. 5 is turbine outer ring inner surface structure schematic diagram.
In figure：
1. 5. impact opening of turbine casing 2. cold air inlet, 3. first chamber, 4. shock plate, 6. turbine outer ring 7. second
8. flow-disturbing rib of chamber, 9. air film hole, 10. turbine outer ring inner surface (directly contacting surface with mainstream combustion gas) 11. can grind material
15. turbine rotor blade of coating 12. seal structure, 13. integral shroud, 14. comb tooth, 16. rotation axis, 17. main 18. flow-disturbing of blast tube
Column
Embodiment
Referring to Fig. 1-Fig. 5, the present invention proposes a kind of new turbine casing structure, its technical solution is as follows：It is of the invention public
A kind of case structure with tip clearance control and the flowing control of leaf top is opened, mainly including turbine casing, casing internal cooling
Structure and turbine outer ring seal structure；Casing internal cooling ceiling structure has cold air air admission hole, impact opening and impacts hardened surely
Structure, shock plate form first chamber with turbine casing, multiple impact openings are defined on shock plate；Turbine outer ring passes through coupling mode
It is connected in turbine casing structure, it forms second chamber with shock plate, and multiple turbulence structures, air film hole knot are defined on outer shroud
Structure and leakage-proof structure；Cold air air-flow enters first chamber via air admission hole, by impact pore structure into second chamber with
Impulse turbine outer shroud, then it is sufficiently cool to turbine outer ring progress via turbulence structure, finally from the film hole structure of turbine outer ring
Outflow formed cooling air film, finally with mainstream combustion gas mixing；Flowing of the boss structure to leaf top fluid on turbine outer ring produces
Influence, prevent the formation and development of blade tip leakage vortex.
Specifically, the impact harden structure on turbine casing, is mainly used for the separation of casing chamber and the arrangement of impact opening.
Specifically, impact pore structure is multiple rows of parallel or is staggered in arrangement on shock plate.
Preferably, a diameter of 0.5mm-2mm of impact opening.
Preferably, hole row's spacing and be 1.5-4 times of bore dia with round spacing during the arrangement of multiple impact openings.
Preferably, the angle of impact opening and shock plate is 30 ° -90 °.
Preferably, it can be the forms such as circular, oval, square, diamond shape to impact hole shape.
Specifically, turbulence structure can be turbulence columns or flow-disturbing rib, and wherein turbulence columns are columnar projections, and flow-disturbing rib is convex for strip
Rise, and turbulence structure is spaced apart with film hole structure.
Specifically, flow-disturbing rod structure is multiple rows of parallel or is staggered in arrangement on turbine outer ring.
Preferably, pin-fin diameter 0.5mm-1.5mm.
Preferably, column row's spacing and be 2-3 times of column diameter with organ timbering spacing during the arrangement of multiple turbulence columns.
More specifically, flow-disturbing rod structure corresponding with upper impingement hole can be arranged or be staggered in arrangement.
Preferably, flow-disturbing post shapes can be the forms such as circular, oval, square, diamond shape.
Specifically, film hole structure is arranged on turbine outer ring, it leads to the second chamber of turbine casing and mainstream combustion gas
Road connects；More specifically, film hole structure is put or is staggered in arrangement with arrangement with flow-disturbing rod structure.
Preferably, a diameter of 0.5mm-1.5mm of air film hole.
Specifically, the shape of turbine outer ring boss structure can be the forms such as plane, honeycomb, sawtooth.
Specifically, outer ring portion use corresponding with turbo blade can grind material.
The above-mentioned cooling structure main working process of the present invention is as follows：Can be as the gas main source of cooling turbine part
In high-pressure compressor, cold air enters turbine casing first chamber through primary air inlet, then passes through the impact pore structure on shock plate
Cold air is introduced into second chamber, the gas into second chamber is in contact with turbulence structure first, and turbulence structure changes gas
The original liquid form of body so that gas is more fully contacted with turbine casing and turbine outer ring structure, strengthens convection current
Heat transfer effect, reaches the film hole structure of turbine outer ring by the gas of turbulence structure, passes through the pore structure (i.e. air film passage)
The air-flow of outflow forms air film in the turbine outer ring inner surface directly with mainstream contacts fuel gas, so that the air film plays isolation high temperature
The effect of combustion gas, and cooling is achieveed the purpose that to turbine outer ring.
The main working process of the above-mentioned leakage-proof structure of the present invention is as follows：According to the structure type on turbo blade leaf top,
Different turbine outer ring seal structures can be designed, turbine outer ring seal structure can be designed as blade flat-tope structure convex
Bench-type formula or honeycomb pattern；Consider from turbo blade rigidity, and in order to avoid due to turbo blade breakage problem caused by vibration,
Turbine leaf top usually needs to increase crown structure, and turbine outer ring structure can use saw-tooth pattern at this time.Mainstream combustion gas is in pressure differential
Under the action of reached and export by tip clearance from import, the generation that influences each other of leakage stream and leaf grating mainstream is multiple in flow process
Vortex, the development of leakage stream necessarily weakens the flowing of mainstream combustion gas, and the seal structure of turbine outer ring can not only prevent to leak
The development in whirlpool, reduces leakage loss, can also reduce tip clearance；Turbine outer ring structure table with leaf top corresponding position at the same time
Face, can grind material with large area use, it is allowed to which leaf top produces certain friction with turbine outer ring.
As shown in Figure 1 and Figure 2, the present invention is a kind of control of tip clearance and the flowing control of leaf top applied to gas turbine
Turbine casing component, according to the design feature of the component, by it, circumferentially 360 ° are divided into several pieces, every part of structure type
It is identical.In the following, the embodiment of the present invention is illustrated referring to the drawings.
Fig. 1 is the turbine casing structure radial cross-section of the present invention, i.e. two dimension view.As seen from the figure, 1 He of turbine casing
Turbine outer ring 6 is the arc-shaped structure being rotarily formed centered on rotation axis 16, it is whole circle turbine casing component by 60 it is identical and
Circumferentially-adjacent matrix turbine casing 1 and turbine outer ring 6 forms.Cooling gas enters first chamber 3 by cold air inlet 2, then
Cold air cools down turbine casing 1, and subsequent cold air reaches shock plate 4, the pore structure 5 of arranged in rows impact thereon；Cold air passes through
Impinging cooling can be carried out into second chamber 7 to turbine outer ring structure 6 by impacting pore structure 5, and turbine outer ring structure 6 be coupled to turbine
Case structure 1, coupling mode weaken influence of the turbine outer ring deformation to turbine casing, flow-disturbing are disposed with turbine outer ring structure
The structures such as turbulence structure, air film hole 9 and the seal structure 12 of 8 form of rib, under the action of turbulence structure, add cold air and whirlpool
Take turns the contact area of outer shroud 6；Cold air enters main blast tube 17 by multiple rows of film hole structure 9 on turbine outer ring 6 at the same time, and one
Aspect cold air can form air film in turbine outer ring inner surface 10, and on the other hand position at the top of the leaf of turbine rotor blade 15 can be carried out
Cooling；The turbine rotor blade 15 with crown structure 13 is directed to, is gone out in order to prevent because comb toothing 14 touches mill with turbine outer ring 6
The phenomenon of existing blade damage, part-structure on turbine outer ring inner surface 10 is with can grind material coating 11.In order to more clear
The architectural feature of the present invention is observed clearly, and Fig. 2 gives the turbine casing three-dimensional structure view of the invention.
For shock plate and impact pore structure, Fig. 3 a and Fig. 3 b give corresponding structure diagram, its view direction is
A-A sections in Fig. 1.It can be seen that impact opening 5 is regularly arranged on shock plate 4, Fig. 3 a arrange parallel cloth for impact opening
Put, Fig. 3 b are staggered in arrangement for impact opening row, and parallel arrangement causes processing to be more prone to, and is staggered in arrangement primarily to cooling down
It is more uniform；Contrast is it can be found that be staggered in arrangement in main fuel gas inlet part (i.e. the left side of Fig. 3 (a) and Fig. 3 (b) views) increase
The arrangement of impact opening, so can preferably cool down the high temperature position of structure, reduce the temperature gradient of structure.The above two
Kind arrangement adds the selection of technical staff, while impact opening arrangement mode can also be set according to actual conditions
Meter.
Shock plate 4 is integral with turbine casing 1, and turbine casing 1 can be divided into two chambers, i.e., first by shock plate 4
Chamber 3 and second chamber 7, on the one hand can be sufficiently cooled turbine casing structure 1, on the other hand can design impact
5 structure of hole, makes cold air be cooled down in a manner of impacting to turbine outer ring 6.Impact opening 5 is multiple rows of parallel in the present invention or stagger arrangement
It is arranged on shock plate 4, a diameter of 0.5mm-2mm of impact opening, hole arranges spacing and is the 1.5-4 of bore dia with round spacing
Times, the angle of impact opening 5 and shock plate 4 is 30 ° -90 °, the shape of impact opening 5 may be designed as it is circular, oval, square and
The forms such as diamond shape.
Fig. 4 a and Fig. 4 b are B-B profile direction turbine outer ring structure diagrams, it mainly gives the gas on turbine outer ring 6
Fenestra is distributed and different turbulence structure forms.Film hole structure and turbulence structure are spaced on turbine outer ring, close
Main fuel gas inlet part (i.e. the left side of Fig. 4 (a) and Fig. 4 (b) views) arrangement two row or multi-row film hole structure 9, its main mesh
Be the high temperature position that more cold air are incorporated into turbine outer ring, stronger air film is formed to turbine outer ring inner surface 10 and is protected
Shield, makes turbine outer ring inner surface preferably be isolated with high-temperature fuel gas.The present invention provides two kinds of turbulence structures, i.e. flow-disturbing rib
Structure 8 and flow-disturbing rod structure 18, effect mainly increase heat exchange area, improve heat convection effect；With 8 phase of flow-disturbing rib structure
Than 18 form of flow-disturbing rod structure reduces materials to a certain extent, reduces cost, alleviates turbine casing weight.
Flow-disturbing rib structure 8 on turbine outer ring 6 circumferentially circles round what is formed with rotation axis 16 for rotation axis.Flow-disturbing rod structure 18
It can be arranged in parallel or be staggered in arrangement with film hole structure 9,18 a diameter of 1mm-2mm of turbulence columns, its column arranges spacing and same organ timbering
Spacing is 2-3 times of column diameter；In order to increase by 9 numbers of air film hole, increase film overcast scope, 9 diameter of air film hole is opposite can
Can be 0.5mm-1.5mm, its spacing also can suitably shorten to reduce a bit.18 shape of turbulence columns can be circular, ellipse,
The forms such as square, diamond shape, its diameter is set and arrangement mode can be identical with upper impingement hole 5, can be corresponding with upper impingement hole 5
Arrangement or interlaced arrangement.
Except cooling structure is distributed with turbine outer ring 6, there is seal structure 12 and can on turbine outer ring inner surface 10
Grind material coating 11.Fig. 5 is turbine outer ring inner surface structure schematic diagram, can substantially observe the envelope on turbine outer ring inner surface 10
Tight structure 12, the structure are mainly designed according to the crown structure 13 of turbine rotor blade 15, have on different integral shrouds 13 different
14 numbers of comb tooth.With leaf top corresponding position with that can grind material coating 11 on turbine outer ring inner surface 10, it mainly allows whirlpool
Wheel movable vane 15 touches mill with turbine outer ring 6, certain protective effect is played to turbine rotor blade 15 and turbine outer ring 6, in this feelings
Under condition, the tip clearance value of smaller can be designed, further improves turbine efficiency.
So far, specific description has been carried out to embodiments of the present invention with reference to attached drawing.According to described above, ability
Field technique personnel a kind of to the present invention should flow the case structure controlled with tip clearance control and leaf top to be had clearly
Understanding.
In conclusion the present invention provides a kind of case structure with tip clearance control and the flowing control of leaf top.The machine
Box structure is mainly to employ the type of cooling of impact opening, turbulence structure and air film hole, and turbine outer ring seal structure and can
Grind material coating.Cooling structure not only further cools down structure, also so that cooling is more uniform, reduces structure
Temperature gradient, reduces the temperature loading being subject in structure；Seal structure then fundamentally weakens the formation of blade tip leakage vortex,
Reduce the mixing loss of leakage stream and leaf grating mainstream.The present invention has extensive in fields such as aero-engine, gas turbines
Using and higher use value.
In addition, the present invention is not in any way limited to the illustrative embodiments presented in explanation and attached drawing.More than
Definition to each element and method is not limited in various concrete structures, mode or the shape mentioned in example, will in such as right
The scope of the present invention and above-described embodiment, those skilled in the art for asking book summary can be in actual applications
In it is modified as the case may be.All any modifications on the basis of the spirit and principles in the present invention, made, be equal
Replace, improve etc., it should all be included in the protection scope of the present invention.
Claims (7)
1. a kind of case structure with tip clearance control and the flowing control of leaf top, it is characterised in that including turbine casing
(1), shock plate (4) and turbine outer ring (6)；The turbine casing (1) is integral with shock plate (4), defines shape between the two
Into chamber be first chamber (3)；Turbine outer ring (6) is couple on turbine casing (1), turbine outer ring (6) and shock plate (4) shape
Into second chamber (7)；The shock plate (4) is equipped with some through holes as impact opening (5)；Turbine outer ring (6) is equipped with some
Through hole is as air film hole (9), and turbine outer ring (6) is equipped with some protrusions, as turbulence structure；Turbine outer ring inner surface (10)
Seal structure (12) is used as equipped with some protrusions.
2. a kind of case structure with tip clearance control and the flowing control of leaf top as claimed in claim 1, its feature exist
In some impact openings (5) are into multiple rows of distribution, and multiple rows of impact opening (5) is arranged parallel to or is staggered in arrangement.
3. a kind of case structure with tip clearance control and the flowing control of leaf top as claimed in claim 1, its feature exist
In impact opening (5) axis and the angle of plane where shock plate are 30 ° -90 °.
4. a kind of case structure with tip clearance control and the flowing control of leaf top as claimed in claim 1, its feature exist
In the turbulence structure is turbulence columns or flow-disturbing rib, and wherein turbulence columns are columnar projections, and flow-disturbing rib is strip projected parts.
5. a kind of case structure with tip clearance control and the flowing control of leaf top as described in claim 2 or 4, its feature
It is, when turbulence structure is turbulence columns, some turbulence columns are in a row distributed, and are spaced apart with air film hole in a row (9), and
Multiple rows of turbulence columns are arranged parallel to or are staggered in arrangement.
6. a kind of case structure with tip clearance control and the flowing control of leaf top as described in claim 2 or 4, its feature
It is, when turbulence structure is flow-disturbing rib, some flow-disturbing ribs are spaced apart with air film hole in a row (9).
7. a kind of case structure with tip clearance control and the flowing control of leaf top as claimed in claim 1, its feature exist
In on the turbine outer ring inner surface (10), part corresponding with blade, which is equipped with, can grind material coating (11).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2017204901078 | 2017-05-05 | ||
| CN201720490107 | 2017-05-05 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207348905U true CN207348905U (en) | 2018-05-11 |
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ID=62412055
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721090471.1U Expired - Fee Related CN207348905U (en) | 2017-05-05 | 2017-08-29 | A kind of case structure with tip clearance control and the flowing control of leaf top |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207348905U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020151578A1 (en) * | 2019-01-22 | 2020-07-30 | 北京南方斯奈克玛涡轮技术有限公司 | Turbine housing integrated with active clearance control apparatus and turbine |
| CN111594275A (en) * | 2019-02-20 | 2020-08-28 | 通用电气公司 | Turbomachine having an airflow management assembly |
| CN113027817A (en) * | 2021-03-12 | 2021-06-25 | 西北工业大学 | Processing method and structure of self-circulation casing of axial flow compressor |
-
2017
- 2017-08-29 CN CN201721090471.1U patent/CN207348905U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020151578A1 (en) * | 2019-01-22 | 2020-07-30 | 北京南方斯奈克玛涡轮技术有限公司 | Turbine housing integrated with active clearance control apparatus and turbine |
| CN111594275A (en) * | 2019-02-20 | 2020-08-28 | 通用电气公司 | Turbomachine having an airflow management assembly |
| CN113027817A (en) * | 2021-03-12 | 2021-06-25 | 西北工业大学 | Processing method and structure of self-circulation casing of axial flow compressor |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
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Granted publication date: 20180511 Termination date: 20200829 |