CN110056397B - Gas turbine rim sealing device and gas turbine - Google Patents
Gas turbine rim sealing device and gas turbine Download PDFInfo
- Publication number
- CN110056397B CN110056397B CN201910486237.8A CN201910486237A CN110056397B CN 110056397 B CN110056397 B CN 110056397B CN 201910486237 A CN201910486237 A CN 201910486237A CN 110056397 B CN110056397 B CN 110056397B
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- China
- Prior art keywords
- gas turbine
- gas
- synthetic jet
- sealing
- driving source
- 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.)
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- 238000007789 sealing Methods 0.000 title claims abstract description 56
- 239000007789 gas Substances 0.000 claims abstract description 98
- 239000002737 fuel gas Substances 0.000 claims abstract description 14
- 238000002347 injection Methods 0.000 claims abstract description 6
- 239000007924 injection Substances 0.000 claims abstract description 6
- 230000003068 static effect Effects 0.000 claims abstract description 4
- 238000007664 blowing Methods 0.000 claims description 7
- 238000001816 cooling Methods 0.000 description 24
- 239000000567 combustion gas Substances 0.000 description 5
- 238000005507 spraying Methods 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 239000007921 spray Substances 0.000 description 4
- 238000004378 air conditioning Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000002955 isolation Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 239000000112 cooling gas Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000009545 invasion Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000737 periodic effect 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 invention provides a gas turbine rim sealing device, comprising: the air curtain sealing part is positioned at the connection part of the disk cavity between the static blade inner ring and the movable blade disk and the fuel gas channel; an air curtain generating assembly comprising a plurality of synthetic jet generators disposed on the vane inner ring, the synthetic jet generators having injection ports facing the air curtain seal; all the synthetic jet generators are connected with a driving source outside the gas turbine, and the jet ports of all the synthetic jet generators form a sealing gas curtain at the gas curtain sealing part under the driving of the driving source so as to isolate high-temperature gas in the gas channel from entering the disc cavity. The invention can prevent high-temperature fuel gas from invading the inner part of the disk cavity between the stator blade inner ring and the movable blade disk, and avoid reducing the aerodynamic efficiency of the blade.
Description
Technical Field
The invention relates to a gas turbine, in particular to a rim sealing device of a gas turbine.
Background
The main components of an industrial gas turbine include a compressor, a combustor, and a turbine. The compressor compresses air taken in from an air intake port to form high-temperature and high-pressure compressed air. The combustion chamber is configured to burn the compressed air by supplying fuel thereto, thereby obtaining a high-temperature and high-pressure combustion gas. The turbine blade is typically formed by a plurality of sets of moving blades, and the rotor is driven to rotate by passing a high-temperature and high-pressure combustion gas generated by a combustor through a plurality of stationary blades and moving blades in a combustion gas passage. A certain gap is reserved between the dynamic impeller plate and the static impeller plate in order to avoid friction. Under high speed rotation of the turbine blades, the gas interferes with the stator blades. Interference between the moving and stationary vanes may result in periodic pressure fluctuations between the moving and stationary vanes. When the gas pressure is greater than the pressure in the gap between the movable and the stationary blades, high-temperature gas can flow back into the cavity between the movable and the stationary blades, so that the metal is invalid, and the safety of the gas turbine is endangered.
In order to prevent the clearance between the combustion gas driven blade and the stationary blade from entering the chamber, a sealing device called a rim seal is provided. The rim seal is generally configured such that a cooling seal air flow, which is relatively cool with respect to the fuel gas, is led out from a compressor end, is supplied to a disk cavity formed in a gap between the rotor blades and the stator blades, and the seal air in the disk cavity is ejected toward the gap between the rotor blades and the stator blades, thereby preventing intrusion of the combustion gas. If the amount of seal cold gas is insufficient, high temperature gas still can be caused to invade the chamber. However, excessive seal cold gas can result in reduced aerodynamic efficiency of the turbine end blades after mixing with the main flow, which in turn can result in reduced gas turbine efficiency.
The utility model discloses a gas turbine rim seal structure as in CN205840921U, including the stator blade of connecting on the stator blade platform and the movable vane of connecting on the movable vane platform, the stator blade platform with form the tight air conditioning passageway between the movable vane platform, its characterized in that is followed the circumference of stator blade platform is equipped with the fumarole, the fumarole with the cooling channel of stator blade is linked together, the export of fumarole is located the downstream side of stator blade platform and with the tight air conditioning passageway is linked together, the fumarole is used for deriving cooling gas in the cooling channel and makes cooling gas in the exit of tight air conditioning passageway forms the air curtain. According to the invention, the cooling channel is arranged on the stationary blade, and the air spraying hole communicated with the cooling channel is arranged on the stationary blade platform, so that an air curtain is formed at the outlet of the sealed cold air channel, cooling air flow is required to be additionally led from the outside through the cooling channel arranged in the stationary blade platform, and the air curtain is formed by spraying through the air spraying hole, so that the structure is complex and the air curtain is not adjustable.
Accordingly, there is a need for a gas turbine rim seal that prevents high temperature gas from entering the chamber and ensures aerodynamic efficiency of the turbine end blades.
Disclosure of Invention
In view of the above-mentioned drawbacks of the prior art, an object of the present invention is to provide a rim sealing device of a gas turbine and a gas turbine, which are used for solving the problem that the efficiency of the gas turbine is easily reduced in the process of preventing high-temperature gas from invading a chamber in the prior art.
To achieve the above and other related objects, the present invention provides a gas turbine rim sealing apparatus comprising:
the air curtain sealing part is positioned at the connection part of the disk cavity between the static blade inner ring and the movable blade disk and the fuel gas channel;
an air curtain generating assembly comprising a plurality of synthetic jet generators disposed on the vane inner ring, the synthetic jet generators having injection ports facing the air curtain seal; all the synthetic jet generators are connected with a driving source outside the gas turbine, and the jet ports of all the synthetic jet generators form a sealing gas curtain at the gas curtain sealing part under the driving of the driving source so as to isolate high-temperature gas in the gas channel from entering the disc cavity.
Preferably, a sealing protrusion protruding toward the inner ring side of the stator blade is arranged on the outer wall of the movable blade wheel disc in the air curtain sealing part.
Preferably, the sealing protrusion has a groove therein, and the injection port of the synthetic jet generator is disposed opposite to the notch of the groove.
Preferably, all the synthetic jet generators are uniformly arranged along the circumferential direction of the vane inner ring.
Preferably, the sealing air curtain is formed by the following steps: and adjusting the frequency of the blowing and sucking air flow of the synthetic jet generator through the driving source according to the current working condition of the gas turbine.
Preferably, the synthetic jet generator is of piezoelectric type.
Preferably, the synthetic jet generator is a cylindrical cavity with one end open, and a piezoelectric film connected with the driving source is arranged at the other end of the cylindrical cavity; the opening of the cylindrical cavity serves as the ejection port.
Preferably, the synthetic jet generator is a cylindrical cavity with one end open and one end sealed, a piezoelectric film extending along the axial direction of the cylindrical cavity is arranged in the cylindrical cavity, the piezoelectric film divides the cylindrical cavity into two subchambers, and the opening part corresponding to each subchamber is used as the jet orifice; the piezoelectric film is connected with the driving source.
Preferably, the driving source is a power supply controller.
The invention also provides a gas turbine, wherein the gas turbine rim sealing device is arranged on the gas turbine.
As described above, the gas turbine rim sealing device and the gas turbine have the following beneficial effects: by arranging the synthetic jet generator on the inner ring of the stator blade, the synthetic jet generator uninterruptedly sucks cooling air in the disc cavity and sprays the cooling air; the sprayed synthetic jet forms an air curtain between cooling air and high-temperature fuel gas, and reduces the axial clearance between the movable vane disk and the stationary vane inner ring so as to prevent the high-temperature fuel gas from invading the disk cavity; the frequency of the blowing and sucking air flow of the synthetic jet generator can be adjusted through the driving source, so that cooling air (also called sealing cold air) can be more effectively utilized when the gas turbine runs under different working conditions, and the cooling air is prevented from entering the gas channel from the disc cavity to be mixed with high-temperature gas, so that the efficiency of the gas turbine is reduced.
Drawings
FIG. 1 shows a schematic view of a gas turbine rim seal arrangement of the present invention.
FIG. 2 is a schematic diagram of an air curtain generating assembly according to the present invention.
Fig. 3 shows a diagram of an embodiment of a synthetic jet generator.
Fig. 4 shows a diagram of another embodiment of a synthetic jet generator.
Description of element reference numerals
1. Turbine bucket
2. Movable vane wheel disc
3. Driving source
4. Electric wire
5. Turbine stator blade
6. Inner ring of stationary blade
7. Synthetic jet generator
8. Jet orifice
9. Sealing protrusion
10. Cavity wall
11. Piezoelectric film
12. Synthetic jet
13. Cylindrical cavity
100. Gas channel
200. Disc cavity
300. Air curtain sealing part
Detailed Description
Further advantages and effects of the present invention will become apparent to those skilled in the art from the disclosure of the present invention, which is described by the following specific examples.
Please refer to fig. 1 to 4. It should be understood that the structures, proportions, sizes, etc. shown in the drawings are for the purpose of understanding and reading the disclosure, and are not intended to limit the scope of the invention, which is defined by the appended claims, but rather by the claims, unless otherwise indicated, and unless otherwise indicated, all changes in structure, proportions, or otherwise, used by those skilled in the art, are included in the spirit and scope of the invention. Also, the terms such as "upper," "lower," "left," "right," "middle," and "a" and the like recited in the present specification are merely for descriptive purposes and are not intended to limit the scope of the invention, but are intended to provide relative positional changes or modifications without materially altering the technical context in which the invention may be practiced.
As shown in fig. 1 to 4, the present invention provides a gas turbine, which mainly relates to a rim sealing device of the gas turbine, wherein main components of the gas turbine comprise a compressor, a combustion chamber and a turbine, and generally, the compressor comprises a compressor movable blade and a compressor stationary blade; the turbine comprises a turbine movable blade 1 and a turbine stationary blade 5; the air enters from the air inlet of the air compressor and is folded into radial flow, the movable blades of the air compressor rotate, the radial flow air is decelerated and diffused under the action of the movable blades of the air compressor and the stationary blades of the air compressor, the radial flow air enters into a combustion chamber to be mixed with fuel for combustion so as to generate high-temperature gas, and the high-temperature gas flows through the stationary blades of the turbine and the movable blades of the turbine to do work at a speed increasing speed, so that the movable blades of the turbine are pushed to rotate and are discharged from the air outlet of the turbine; the following mainly describes a gas turbine rim seal arrangement, and the compressor, combustor and other structures in the gas turbine are not described in detail herein.
For convenience of description, axial in this specification refers to an axial direction of a rotor shaft in a gas turbine, and radial refers to a radial extending direction of the rotor shaft.
The present invention provides a gas turbine rim sealing apparatus, as shown in FIG. 1, comprising:
an air curtain seal 300 located upstream of the connection between the disk chamber 200 between the stator blade inner ring 6 and the movable blade disk 2 and the gas passage 100;
an air curtain generating assembly including a plurality of synthetic jet generators 7 provided on the vane inner ring 6, the injection ports 8 of the synthetic jet generators 7 being directed toward the air curtain sealing part 300; all the synthetic jet generators 7 are connected with a driving source 3 outside the gas turbine, and the jet ports 8 of all the synthetic jet generators 7 form a sealed gas curtain at the gas curtain sealing part 300 under the driving of the driving source 3 so as to isolate the high-temperature gas in the gas channel 100 from entering the disc cavity 200.
The synthetic jet generator 7 is arranged on the stator blade inner ring 6, and the synthetic jet generator 7 continuously sucks cooling air into the disc cavity 200 and sprays the cooling air; the sprayed synthetic jet 12 forms an air curtain between the cooling air and the high-temperature fuel gas, and reduces the axial clearance between the movable vane disk 2 and the stationary vane inner ring 6 so as to prevent the high-temperature fuel gas from invading into the disk cavity; the frequency of the blowing and sucking air flow of the synthetic jet generator 7 can be adjusted through the driving source 3, so that cooling air (also called sealing cold air) can be more effectively utilized when the gas turbine runs under different working conditions, and the cooling air is prevented from entering the gas channel 100 from the disc cavity 200 to be mixed with high-temperature gas, so that the efficiency of the gas turbine is reduced; in order to better perform the isolation function, the air curtain formed by spraying the synthetic jet generator 7 in this embodiment is located at the connection between the disc cavity 200 and the fuel gas channel 100, that is, at the upstream of the high-temperature fuel gas entering the disc cavity.
In order to better isolate high-temperature fuel gas from entering the disc cavity, in this embodiment, a sealing protrusion 9 protruding towards the stationary blade inner ring 6 is provided on the outer wall of the movable blade wheel disc 2 in the air curtain sealing portion 300, and the axial gap between the movable blade wheel disc 2 and the stationary blade inner ring 6 can be shortened due to the arrangement of the sealing protrusion 9. In this embodiment, the axial gap between the movable vane disk 2 and the stationary vane inner ring 6 is shortened by the sealing protrusion 9, and only the air curtain formed by spraying the synthetic jet generator 7 is required to seal and isolate the gap between the sealing protrusion 9 and the stationary vane inner ring 6.
For better sealing isolation, the sealing bulge 9 is provided with a groove in the embodiment, and the jet orifice 8 of the synthetic jet generator 7 is arranged opposite to the notch of the groove. In this embodiment, two rings of overhanging cantilevers are circumferentially arranged on the outer wall of the movable vane disk 2, the two cantilevers form the sealing protrusion 9, the gap between the two cantilevers forms the groove, the channel area of the high-temperature gas invading the disk cavity is reduced by the arrangement of the two cantilevers, and after the gas curtain generated by the synthetic jet 12 between the cantilevers acts, the sealing cold air required by flowing through the axial gap can be greatly reduced to prevent the invasion of the high-temperature gas.
For better sealing isolation, all synthetic jet generators 7 in this embodiment are uniformly arranged along the circumference of the vane inner ring 6, as shown in fig. 2. That is, a plurality of synthetic jet generators 7 are uniformly provided along the circumferential direction of the vane inner ring 6 on the side facing the movable vane disk 2. In this embodiment, the synthetic jet generator 7 may be embedded in the vane inner ring 6, and may be fixed to the vane inner ring 6 by welding, clamping, or bolting.
To avoid mixing cooling air in the disk cavity 200 into the high temperature gas into the gas passage 100, the efficiency of the gas turbine is reduced, and the sealing gas curtain in this embodiment is formed by: according to the current working condition of the gas turbine, the frequency of the blowing and sucking air flow of the synthetic jet generator 7 is adjusted through the driving source 3; if the pressure of the high-temperature gas in the gas channel 100 in the current working condition is reduced, the frequency of the blowing and sucking air flow of the synthetic jet generator 7 is reduced, and cooling air is prevented from entering the gas channel 100.
The synthetic jet generator 7 described above can take many forms. For example, piston type, piezoelectric type, i.e., piezoelectric diaphragm type, and plasma type. Two piezoelectric diaphragm type synthetic jet embodiments are described below:
as shown in fig. 3, the synthetic jet generator 7 is a cylindrical cavity 13 with one end open, and a piezoelectric film 11 connected with the driving source 3 through an electric wire 4 is arranged at the other end of the cylindrical cavity 13; the opening of the cylindrical cavity 13 serves as the injection port 8. The piezoelectric film 11 is energized to produce vibration which squeezes a cylindrical cavity 13 surrounded by the cavity wall 10 of the synthetic jet generator 7, and the compressed gas is ejected in the form of a synthetic jet 12 through the ejection orifice 8 of the synthetic jet generator 7. The driving source 3 is a power supply controller.
Referring to fig. 4, in another embodiment of the synthetic jet generator, a cylindrical cavity 13 with one end open and one end sealed is provided, a piezoelectric film 11 extending along the axial direction of the cylindrical cavity 13 is arranged in the cylindrical cavity 13, and the piezoelectric film 11 divides the cylindrical cavity into two subchambers, and an opening part corresponding to each subchamber is used as the jet orifice 8; the piezoelectric film 11 is connected to the driving source 3 via an electric wire 4. The driving source 3 is a power supply controller. This structure ensures that one of the subchambers is extruded to spray when the piezoelectric film 11 is energized and vibrated, and the other subchamber is in an air suction state. Thereby ensuring that the synthetic jet generator 7 is always in the jet state.
In summary, according to the rim sealing device of the gas turbine, the synthetic jet generator is arranged on the inner ring of the stationary blade, and the synthetic jet generator continuously sucks cooling air into the disc cavity and sprays the cooling air; the sprayed synthetic jet forms an air curtain between cooling air and high-temperature fuel gas, and reduces the axial clearance between the movable vane disk and the stationary vane inner ring so as to prevent the high-temperature fuel gas from invading the disk cavity; the frequency of the blowing and sucking air flow of the synthetic jet generator can be adjusted through the driving source, so that cooling air (also called sealing cold air) can be more effectively utilized when the gas turbine runs under different working conditions, and the cooling air is prevented from entering the gas channel from the disc cavity to be mixed with high-temperature gas, so that the efficiency of the gas turbine is reduced. Therefore, the invention effectively overcomes various defects in the prior art and has high industrial utilization value.
The above embodiments are merely illustrative of the principles of the present invention and its effectiveness, and are not intended to limit the invention. Modifications and variations may be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the invention. Accordingly, it is intended that all equivalent modifications and variations of the invention be covered by the claims, which are within the ordinary skill of the art, be within the spirit and scope of the present disclosure.
Claims (10)
1. A gas turbine rim seal assembly, comprising:
the air curtain sealing part is positioned at the connection part of the disk cavity between the static blade inner ring and the movable blade disk and the fuel gas channel;
an air curtain generating assembly comprising a plurality of synthetic jet generators disposed on the vane inner ring, the synthetic jet generators having injection ports facing the air curtain seal; all the synthetic jet generators are connected with a driving source outside the gas turbine, and the jet ports of all the synthetic jet generators form a sealing gas curtain at the gas curtain sealing part under the driving of the driving source so as to isolate high-temperature gas in the gas channel from entering the disc cavity.
2. The gas turbine rim sealing apparatus of claim 1 wherein: and a sealing bulge protruding towards the inner ring side of the stationary blade is arranged on the outer wall of the movable blade wheel disc in the air curtain sealing part.
3. The gas turbine rim sealing apparatus of claim 2 wherein: the sealing bulge is provided with a groove, and the jet orifice of the synthetic jet generator is arranged opposite to the notch of the groove.
4. The gas turbine rim sealing apparatus of claim 1 wherein: all the synthetic jet generators are uniformly arranged along the circumferential direction of the stator blade inner ring.
5. The gas turbine rim sealing apparatus of claim 1 wherein: the sealing air curtain is formed by the following steps: and adjusting the frequency of the blowing and sucking air flow of the synthetic jet generator through the driving source according to the current working condition of the gas turbine.
6. The gas turbine rim sealing apparatus of claim 1 wherein: the synthetic jet generator is piezoelectric.
7. The gas turbine rim sealing apparatus of claim 1 wherein: the synthetic jet generator is a cylindrical cavity with one end open, and a piezoelectric film connected with the driving source is arranged at the other end of the cylindrical cavity; the opening of the cylindrical cavity serves as the ejection port.
8. The gas turbine rim sealing apparatus of claim 1 wherein: the synthetic jet flow generator is a cylindrical cavity with one end open and one end sealed, a piezoelectric film extending along the axial direction of the cylindrical cavity is arranged in the cylindrical cavity, the piezoelectric film divides the cylindrical cavity into two subchambers, and the opening part corresponding to each subchamber is used as the jet orifice; the piezoelectric film is connected with the driving source.
9. The gas turbine rim sealing apparatus of claim 7 or 8 wherein: the driving source is a power supply controller.
10. A gas turbine, characterized by: the gas turbine is provided with a gas turbine rim sealing device according to any one of claims 1 to 8.
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 CN110056397A (en) | 2019-07-26 |
| CN110056397B true CN110056397B (en) | 2023-11-10 |
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Family Applications (1)
| 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 |
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| Country | Link |
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| CN (1) | CN110056397B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
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| CN110056397A (en) | 2019-07-26 |
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