CN110056397A - Gas turbine wheel rim sealing device and gas turbine - Google Patents
Gas turbine wheel rim sealing device and gas turbine Download PDFInfo
- Publication number
- CN110056397A CN110056397A CN201910486237.8A CN201910486237A CN110056397A CN 110056397 A CN110056397 A CN 110056397A CN 201910486237 A CN201910486237 A CN 201910486237A CN 110056397 A CN110056397 A CN 110056397A
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- China
- Prior art keywords
- gas turbine
- air curtain
- wheel rim
- jet
- synthesizing jet
- Prior art date
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Links
- 238000007789 sealing Methods 0.000 title claims abstract description 50
- 239000007789 gas Substances 0.000 claims abstract description 64
- 230000002194 synthesizing effect Effects 0.000 claims abstract description 59
- 239000002737 fuel gas Substances 0.000 claims abstract description 26
- 230000015572 biosynthetic process Effects 0.000 claims abstract description 10
- 239000012528 membrane Substances 0.000 claims description 14
- 230000009545 invasion Effects 0.000 abstract description 4
- 238000001816 cooling Methods 0.000 description 21
- 238000002485 combustion reaction Methods 0.000 description 7
- 238000002955 isolation Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 239000000112 cooling gas Substances 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000003786 synthesis reaction Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000004378 air conditioning Methods 0.000 description 1
- 230000001914 calming effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention provides a kind of gas turbine wheel rim sealing device comprising: air curtain sealing, disk chamber and blast tube connecting place between stator blade inner ring and movable vane wheel disc；Air curtain formation component, including the multiple synthesizing jet-flow generators being arranged in stator blade inner ring, the jet port of the synthesizing jet-flow generator is towards the air curtain sealing；All synthesizing jet-flow generators are connected with the driving source outside gas turbine, and the jet port of all synthesizing jet-flow generators forms sealing air curtain at air curtain sealing under the driving of driving source, and it is intracavitary to enter disk with the high-temperature fuel gas completely cut off in blast tube.The present invention can prevent the intracavitary portion of disk between high-temperature fuel gas invasion stator blade inner ring and movable vane wheel disc, and avoid reducing the pneumatic efficiency of blade.
Description
Technical field
The present invention relates to gas turbines, more particularly to a kind of gas turbine wheel rim sealing device.
Background technique
The main component of industry gas turbine includes compressor, combustion chamber and turbine.Compressor to from air by taking
The air that entrance is taken into is compressed and is formed the compressed air of high temperature and pressure.Combustion chamber is by supplying fuel to the compressed air
And burning is allowed to obtain the burning gases of high temperature and pressure.Turbine end is usually to be made of multiple groups rotor and stator blade, by making by firing
The burning gases for the high temperature and pressure that burner generates pass through the multiple stator blades for being in burning gases access and movable vane piece and turn to drive
Son rotation.In order to avoid friction needs to retain certain gap between the sound impeller disk.Under turbine rotor vane high speed rotation, gas
Interference can be generated with stator blade.Interference between moving-stator blade will lead to generates periodic pressure oscillation between moving-stator blade.Work as combustion
When atmospheric pressure is greater than the pressure between moving-stator blade in gap, it will lead to high-temperature fuel gas and flow backward chamber between moving-stator blade, cause
Metal failure jeopardizes the safety of gas turbine.
In order to prevent in the gap of the burning gases passive blade and stator blade intrusion chamber, and it is close to be provided with referred to as wheel rim
The sealing device of envelope.Wheel rim sealing generally draws one by generator terminal of calming the anger and obturages air-flow relative to the colder cooling of combustion gas, to
It is formed in the disk chamber supply in the gap of movable vane piece and stator blade, and make the disk chamber obturages cold air towards movable vane piece and stator blade
Gap sprays, and thus prevents the intrusion of burning gases.If obturaging air conditioning quantity deficiency, high-temperature fuel gas invasion chamber is still resulted in
Room.However, excessive cold air of obturaging will lead to the pneumatic efficiency reduction of turbine end blade after it mix with mainstream, and then cause
Gas turbine proficiency reduces.
If CN205840921U discloses a kind of gas turbine wheel rim sealing structure, including the stator blade being connected on stator blade platform
With the movable vane being connected on movable vane platform, is formed between the stator blade platform and the movable vane platform and obturage cold air path, it is special
Sign is, along the fumarole that is circumferentially with of the stator blade platform, the fumarole is connected with the cooling duct of the stator blade, institute
The outlet for stating fumarole is located at the downstream side of the stator blade platform and is connected with the cold air path of obturaging, and the fumarole is used
In the cooling gas exported in the cooling duct and form the cooling gas in the exit for obturaging cold air path
Air curtain.The present invention sets the fumarole communicated with cooling duct, on stator blade platform by the way that cooling duct is arranged on stator blade with this
Realize that the exit for obturaging cold air path described forms air curtain, need from it is external additionally draw one from cooling air-flow pass through quiet
Cooling duct is set in leaf platform, sprays to form air curtain via fumarole, structure is complicated and air curtain is non-adjustable.
High-temperature fuel gas invasion chamber can be prevented therefore, it is necessary to one kind and ensures the combustion gas wheel of the pneumatic efficiency of turbine end blade
Wheel edge sealing device.
Summary of the invention
In view of the foregoing deficiencies of prior art, the purpose of the present invention is to provide a kind of sealings of gas turbine wheel rim to fill
It sets and gas turbine, easily reduces gas turbine proficiency during preventing high-temperature fuel gas from invading chamber in the prior art for solving
The problem of.
In order to achieve the above objects and other related objects, the present invention provides a kind of gas turbine wheel rim sealing device, packet
It includes:
Air curtain sealing, disk chamber and blast tube connecting place between stator blade inner ring and movable vane wheel disc；
Air curtain formation component, including the multiple synthesizing jet-flow generators being arranged in stator blade inner ring, the synthesizing jet-flow hair
The jet port of raw device is towards the air curtain sealing；All synthesizing jet-flow generators with the driving source outside the gas turbine
It is connected, the jet port of all synthesizing jet-flow generators forms sealing air curtain at air curtain sealing under the driving of driving source, with
It is intracavitary that high-temperature fuel gas in isolation blast tube enters disk.
Preferably, the movable vane wheel disc is in the outer wall in the air curtain sealing equipped with convex to stator blade inner ring side
Seal convexity out.
Preferably, there is groove, and recessed described in the jet port face of the synthesizing jet-flow generator in the seal convexity
The notch of slot is arranged.
Preferably, all synthesizing jet-flow generators are uniformly arranged along the circumferential direction of the stator blade inner ring.
Preferably, meet when sealing air curtain formation: according to the current working of gas turbine, by the driving source come
Adjust the frequency of the synthesizing jet-flow generator Push-pull Flow.
Preferably, the synthesizing jet-flow generator is piezoelectric type.
Preferably, the synthesizing jet-flow generator is cylindrical cavity open at one end, is equipped at the other end of cylindrical cavity
The piezoelectric membrane being connected with the driving source；The opening of cylindrical cavity is as the jet port.
Preferably, the synthesizing jet-flow generator is the cylindrical cavity of one end open at one end sealing, is set in cylindrical cavity
There is the axially extending piezoelectric membrane along cylindrical cavity, and piezoelectric membrane will be divided into two sub- chambers, every height in cylindrical cavity
The corresponding opening portion of chamber is as the jet port；The piezoelectric membrane is connected with the driving source.
Preferably, the driving source is power-supply controller of electric.
The present invention also provides a kind of gas turbine, the gas turbine is sealed equipped with gas turbine wheel rim as described above
Device.
As described above, gas turbine wheel rim sealing device of the invention and gas turbine, have the advantages that and pass through
Synthesizing jet-flow generator is set in stator blade inner ring, cooling air and is sprayed in the continual sucking disk chamber of synthesizing jet-flow generator
It is shot out；The synthesizing jet-flow ejected forms an air curtain between cooling air and high-temperature fuel gas, reduces movable vane
Axial gap between disk and stator blade inner ring, to prevent high-temperature fuel gas from invading the intracavitary portion of disk；Synthesis can be adjusted by driving source to penetrate
The frequency of flow-generator Push-pull Flow can make gas turbine when different operating conditions are run, utilization cooling air more efficiently
(also become and obturage cold air) avoids cooling air from mixing from the intracavitary entrance blast tube of disk with high-temperature fuel gas, thus reduces combustion
The efficiency of gas-turbine.
Detailed description of the invention
Fig. 1 is shown as gas turbine wheel rim sealing device schematic diagram of the invention.
Fig. 2 is shown as air curtain formation component schematic diagram of the invention.
Fig. 3 is shown as an implementation example figure of synthesizing jet-flow generator.
Fig. 4 is shown as another implementation example figure of synthesizing jet-flow generator.
Component label instructions
1 turbine rotor blade
2 movable vane wheel discs
3 driving sources
4 electric wires
5 Turbomachineries
6 stator blade inner ring
7 synthesizing jet-flow generators
8 jet ports
9 seal convexities
10 cavity walls
11 piezoelectric membranes
12 synthesizing jet-flows
13 cylindrical cavities
100 blast tubes
200 disk chambers
300 air curtain sealings
Specific embodiment
Embodiments of the present invention are illustrated by particular specific embodiment below, those skilled in the art can be by this explanation
Content disclosed by book is understood other advantages and efficacy of the present invention easily.
It please refers to Fig.1 to Fig.4.It should be clear that structure, ratio, size etc. depicted in this specification institute attached drawing, only to
Cooperate the revealed content of specification, so that those skilled in the art understands and reads, being not intended to limit the invention can be real
The qualifications applied, therefore do not have technical essential meaning, the tune of the modification of any structure, the change of proportionate relationship or size
It is whole, in the case where not influencing the effect of present invention can be generated and the purpose that can reach, it should all still fall in disclosed skill
In the range of art content can cover.Meanwhile in this specification it is cited as "upper", "lower", "left", "right", " centre " and
The term of " one " etc. is merely convenient to being illustrated for narration, rather than to limit the scope of the invention, relativeness
It is altered or modified, under the content of no substantial changes in technology, when being also considered as the enforceable scope of the present invention.
As shown in Figures 1 to 4, the present invention provides a kind of gas turbine, relates generally to gas turbine wheel rim sealing device,
The main component of gas turbine includes compressor, combustion chamber and turbine, in general, compressor includes gas compressor moving blade and calms the anger
Machine stator blade；Turbine includes turbine rotor blade 1 and Turbomachinery 5；Air is turned back after being entered by compressor air inlet machine mouth as Radial Flow, pressure
The rotation of mechanism of qi movable vane, under the action of gas compressor moving blade and compressor stator, the air deceleration diffusion of Radial Flow, into burning
Room and fuel, which are mixed and burned, generates high-temperature fuel gas, in high-temperature fuel gas channel 100, flows through Turbomachinery in high-temperature fuel gas and turbine is dynamic
The acting of leaf speedup, pushes turbine rotor blade to rotate and is discharged by turbine gas outlet；Mainly the sealing of description gas turbine wheel rim fills below
It sets, the compressor, combustion chamber and other structures in gas turbine are not described in detail here.
For ease of description, the axial direction in this specification refers to the axis direction of armature spindle in gas turbine, radially refer to armature spindle
Radially extend direction.
The present invention provides a kind of gas turbine wheel rim sealing device, as shown in Figure 1 comprising:
Air curtain sealing 300, what the disk chamber 200 between stator blade inner ring 6 and movable vane wheel disc 2 was connected with blast tube 100
Upstream end；
Air curtain formation component, including the multiple synthesizing jet-flow generators 7 being arranged in stator blade inner ring 6, the synthesizing jet-flow
The jet port 8 of generator 7 is towards the air curtain sealing 300；All synthesizing jet-flow generators 7 are and outside gas turbine
Driving source 3 be connected, the jet port 8 of all synthesizing jet-flow generators 7 is at air curtain sealing 300 under the driving of driving source 3
Sealing air curtain is formed, is entered in disk chamber 200 with the high-temperature fuel gas completely cut off in blast tube 100.
The present invention in stator blade inner ring 6 by being arranged synthesizing jet-flow generator 7, the continual suction of synthesizing jet-flow generator 7
Enter cooling air in disk chamber 200 and ejects；The synthesizing jet-flow 12 ejected form one in cooling air and
Air curtain between high-temperature fuel gas reduces the axial gap between movable vane disk 2 and stator blade inner ring 6, to prevent high-temperature fuel gas from invading disk
Intracavitary portion；The frequency that 7 Push-pull Flow of synthesizing jet-flow generator can be adjusted by driving source 3, can make gas turbine in different works
When condition is run, (also becoming using cooling air and obturaging cold air) more efficiently avoids cooling air from entering combustion out of disk chamber 200
It is mixed in gas channel 100 with high-temperature fuel gas, thus reduces the efficiency of gas turbine；Preferably to play isolation function, this implementation
The air curtain that the injection of synthesizing jet-flow generator 7 is formed in example is located at disk chamber 200 and 100 connecting place of blast tube, that is, is located at high temperature and fires
Gas enters upstream end when disk chamber.
Enter the intracavitary portion of disk preferably to completely cut off high-temperature fuel gas, it is close in movable vane wheel disc 2 to be in the air curtain in the present embodiment
Outer wall in envelope portion 300 is equipped with the seal convexity 9 protruded to 6 side of stator blade inner ring, and the setting of seal convexity 9 can be shortened dynamic
Axial gap between the impeller disk 2 and stator blade inner ring 6.The present embodiment shortens movable vane wheel disc 2 and stator blade inner ring 6 by seal convexity 9
Between axial gap, the air curtain that the injection of above-mentioned synthesizing jet-flow generator 7 need to only formed will be between seal convexity 9 and stator blade inner ring 6
Clearance seal isolation.
Completely cut off for better seal, there is in seal convexity 9 groove, and the synthesizing jet-flow generator 7 in the present embodiment
8 face of jet port described in groove notch setting.It is overhanging that two circles are circumferentially in the present embodiment on the outer wall of movable vane wheel disc 2
Cantilever, two cantilevers constitute above-mentioned seal convexity 9, and the gap between two cantilevers constitutes above-mentioned groove, passes through the setting of two cantilevers
The aisle spare of high-temperature fuel gas invasion disk chamber is reduced, and is acted on air curtain caused by synthesizing jet-flow 12 of the generation between cantilever
Afterwards, it can largely reduce needed for flowing through axial gap and obturage cold air, to hinder high-temperature fuel gas to invade.
For better seal isolation, as shown in Figure 2, all synthesizing jet-flow generators 7 are along the stator blade in the present embodiment
The circumferential direction of ring 6 is uniformly arranged.Multiple synthesis are uniformly arranged along its circumferential direction and are penetrated towards the side of movable vane wheel disc 2 in stator blade inner ring 6
Flow-generator 7.Synthesizing jet-flow generator 7 can be embedded in stator blade inner ring 6 in the present embodiment, can by welding, clamping or
It the modes such as is bolted to fix with 6 phase of stator blade inner ring.
Enter in blast tube 100 to avoid the cooling air in disk chamber 200 from being mixed into high-temperature fuel gas, gas turbine is caused to imitate
Rate reduces, and meets in the present embodiment when the formation of sealing air curtain: according to the current working of gas turbine, by above-mentioned driving source 3 come
Adjust the frequency of 7 Push-pull Flow of synthesizing jet-flow generator；High-temperature fuel gas pressure even in current working blast tube 100
It reduces, then the frequency of 7 Push-pull Flow of synthesizing jet-flow generator is also decreased, cooling air is avoided to enter blast tube 100
It is interior.
Above-mentioned synthesizing jet-flow generator 7 can be there are many form.For example, piston type, piezoelectric type namely piezoelectric diaphragm type with
And plasma formula.Two kinds of piezoelectric diaphragm type synthesizing jet-flow embodiments are described below:
As shown in Figure 3, synthesizing jet-flow generator 7 is cylindrical cavity 13 open at one end, at the other end of cylindrical cavity 13
Equipped with the piezoelectric membrane 11 being connected with the driving source 3 by electric wire 4；The opening of cylindrical cavity 13 is as the jet port 8.Pressure
Conductive film 11 generates vibration after being powered and squeezes the cylindrical cavity 13 surrounded by the cavity wall 10 of synthesizing jet-flow generator 7, after compression
Gas sprayed in the form of synthesizing jet-flow 12 the spray-hole 8 of synthesizing jet-flow generator 7.Driving source 3 is power-supply controller of electric.
See that Fig. 4, another embodiment of synthesizing jet-flow generator, the present embodiment are the cylindrical cavity of one end open at one end sealing
13, the axially extending piezoelectric membrane 11 along cylindrical cavity 13 is equipped in cylindrical cavity 13, and piezoelectric membrane 11 is empty by cylinder
Intracavitary to be divided into two sub- chambers, the corresponding opening portion of every sub- chamber is as the jet port 8；The piezoelectric membrane 11 with it is described
Driving source 3 is connected by electric wire 4.Driving source 3 is power-supply controller of electric.This structure guarantees to squeeze when the energization vibration of piezoelectric membrane 11
One of them sub- chamber injection, another sub- chamber are in suction condition.To guarantee synthesizing jet-flow generator 7 always in spurting
State.
In conclusion gas turbine wheel rim sealing device of the invention, is sent out by the way that synthesizing jet-flow is arranged in stator blade inner ring
Raw device cooling air and ejects in the continual sucking disk chamber of synthesizing jet-flow generator；The synthesizing jet-flow ejected
An air curtain between cooling air and high-temperature fuel gas is formd, is reduced between the axial direction between movable vane disk and stator blade inner ring
Gap, to prevent high-temperature fuel gas from invading the intracavitary portion of disk；The frequency that synthesizing jet-flow generator Push-pull Flow can be adjusted by driving source, can
So that gas turbine, when different operating conditions are run, (also becoming using cooling air and obturaging cold air) more efficiently avoids cooling down
Air enters in blast tube the efficiency for mixing with high-temperature fuel gas, thus reducing gas turbine from disk is intracavitary.So the present invention has
Effect overcomes various shortcoming in the prior art and has high industrial utilization value.
The above-described embodiments merely illustrate the principles and effects of the present invention, and is not intended to limit the present invention.It is any ripe
The personage for knowing this technology all without departing from the spirit and scope of the present invention, carries out modifications and changes to above-described embodiment.Cause
This, institute is complete without departing from the spirit and technical ideas disclosed in the present invention by those of ordinary skill in the art such as
At all equivalent modifications or change, should be covered by the claims of the present invention.
Claims (10)
1. a kind of gas turbine wheel rim sealing device characterized by comprising
Air curtain sealing, disk chamber and blast tube connecting place between stator blade inner ring and movable vane wheel disc；
Air curtain formation component, including the multiple synthesizing jet-flow generators being arranged in stator blade inner ring, the synthesizing jet-flow generator
Jet port towards the air curtain sealing；All synthesizing jet-flow generators with the driving source phase outside the gas turbine
Even, under the driving of driving source the jet port of all synthesizing jet-flow generators is formed at air curtain sealing seals air curtain, with every
It is intracavitary that high-temperature fuel gas in exhausted blast tube enters disk.
2. gas turbine wheel rim sealing device according to claim 1, it is characterised in that: the movable vane wheel disc is in described
Outer wall in air curtain sealing is equipped with the seal convexity protruded to stator blade inner ring side.
3. gas turbine wheel rim sealing device according to claim 2, it is characterised in that: have in the seal convexity recessed
Slot, and the notch setting of groove described in the jet port face of the synthesizing jet-flow generator.
4. gas turbine wheel rim sealing device according to claim 1, it is characterised in that: all synthesizing jet-flows occur
Device is uniformly arranged along the circumferential direction of the stator blade inner ring.
5. gas turbine wheel rim sealing device according to claim 1, it is characterised in that: full when sealing air curtain formation
Foot: according to the current working of gas turbine, the frequency of the synthesizing jet-flow generator Push-pull Flow is adjusted by the driving source
Rate.
6. gas turbine wheel rim sealing device according to claim 1, it is characterised in that: the synthesizing jet-flow generator is
Piezoelectric type.
7. gas turbine wheel rim sealing device according to claim 1, it is characterised in that: the synthesizing jet-flow generator is
Cylindrical cavity open at one end is equipped with the piezoelectric membrane being connected with the driving source at the other end of cylindrical cavity；Cylindrical cavity
Opening as the jet port.
8. gas turbine wheel rim sealing device according to claim 1, it is characterised in that: the synthesizing jet-flow generator is
The cylindrical cavity of one end sealing open at one end is equipped with the axially extending piezoelectric membrane along cylindrical cavity in cylindrical cavity, and
Piezoelectric membrane will be divided into two sub- chambers in cylindrical cavity, the corresponding opening portion of every sub- chamber is as the jet port；It is described
Piezoelectric membrane is connected with the driving source.
9. gas turbine wheel rim sealing device according to claim 7 or 8, it is characterised in that: the driving source is power supply
Controller.
10. a kind of gas turbine, it is characterised in that: the gas turbine is equipped with such as any one of claim 1 to claim 8
The gas turbine wheel rim sealing device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910486237.8A CN110056397B (en) | 2019-06-05 | 2019-06-05 | Gas turbine rim sealing device and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910486237.8A CN110056397B (en) | 2019-06-05 | 2019-06-05 | Gas turbine rim sealing device and gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110056397A true CN110056397A (en) | 2019-07-26 |
| CN110056397B CN110056397B (en) | 2023-11-10 |
Family
ID=67325507
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910486237.8A Active CN110056397B (en) | 2019-06-05 | 2019-06-05 | Gas turbine rim sealing device and gas turbine |
Country Status (1)
| Country | Link |
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| CN (1) | CN110056397B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112282864A (en) * | 2020-11-16 | 2021-01-29 | 兰州长城机械工程有限公司 | Blade root protection technology for long-handle moving blade of flue gas turbine rotor |
| CN114320489A (en) * | 2022-01-11 | 2022-04-12 | 永旭腾风新能源动力科技（北京）有限公司 | Gas turbine with gas seal component |
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| 张玫宝，余锐，杨玉骏: "Ｆ级重型燃气轮机中冷却空气对透平气动性能的影响研究", 上海电气技术, vol. 11, no. 3 * |
| 李金波: "叶轮机械中基于蜂窝密封和合成射流技术的流场控制方法研究", 中国优秀硕士学位论文全文数据库工程科技Ⅱ辑 * |
| 罗振兵，夏智勋: "合成射流技术及其在流动控制中应用的进展", 力学进展, vol. 35, no. 2 * |
| 郑新前，张扬军，周盛: "合成射流控制压气机分离流动及工程应用探索", 中国科技论文在线, vol. 3, no. 8 * |
| 郭咏雪;何立东: "反旋流密封技术研究综述", 化学工程与装备, no. 10 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112282864A (en) * | 2020-11-16 | 2021-01-29 | 兰州长城机械工程有限公司 | Blade root protection technology for long-handle moving blade of flue gas turbine rotor |
| CN114320489A (en) * | 2022-01-11 | 2022-04-12 | 永旭腾风新能源动力科技（北京）有限公司 | Gas turbine with gas seal component |
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| Publication number | Publication date |
|---|---|
| CN110056397B (en) | 2023-11-10 |
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