CN108952826B - Air pressure elastic sealing device and gas turbine engine - Google Patents
Air pressure elastic sealing device and gas turbine engine Download PDFInfo
- Publication number
- CN108952826B CN108952826B CN201810573934.2A CN201810573934A CN108952826B CN 108952826 B CN108952826 B CN 108952826B CN 201810573934 A CN201810573934 A CN 201810573934A CN 108952826 B CN108952826 B CN 108952826B
- Authority
- CN
- China
- Prior art keywords
- outer ring
- sealing
- mounting hole
- gas
- positioning
- 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.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Gasket Seals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an air pressure elastic sealing device and a gas turbine engine, wherein the air pressure elastic sealing device comprises a first outer ring, a second outer ring, a positioning component and a sealing component; the first outer ring and the second outer ring are arranged oppositely, and an accommodating space is formed between the first outer ring and the second outer ring; the first outer ring is provided with an annular boss; an annular limiting groove is formed in the second outer ring; the positioning component is arranged on the second outer ring, extends towards the first outer ring along the axial direction of the second outer ring, and is at least partially arranged in the accommodating space, and the part is called as a guide section; the sealing component is arranged on the guide section. The gas turbine engine comprises the pneumatic elastic sealing device. According to the invention, the double-layer sealing sheets are adopted for series installation, and the gaps of the fan-shaped sections of the two layers of sealing sheets are arranged in a staggered manner, so that the sealing leakage area is greatly reduced, the sealing efficiency is improved, and the installation is convenient.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to an air pressure elastic sealing device and a gas turbine engine.
Background
The advanced sealing technology has the characteristics of low investment and high return for the gas turbine engine, and compared with the approach of improving the performance of the engine by improving the structural design of the blade, the cost required by adopting the advanced sealing technology is much lower under the condition of similar effect. As the level of gas turbine engine design has increased, the impact of static seals between boundary components of the gas flow path on the overall performance and efficiency of the engine has become more and more important. The cooling air of the gas turbine engine leaks to the turbine gas flow passage through an installation gap between stator parts on the boundary of the turbine gas flow passage, and the excessive cooling air leaks to the turbine gas flow passage at an angle approximately perpendicular to the main flow gas to cause local gas flow turbulence, and the mixing loss of cold and hot air flows causes the reduction of turbine efficiency, so that the performance of the engine is reduced.
At present, the sealing of the situation is mostly applied to a bolt tight connection sealing structure, the bolt tight connection sealing structure is used for directly connecting stator components at the boundary of a turbine gas flow passage through bolts to form a closed cylinder to prevent gas from leaking outwards through the boundary, although the bolt connection structure can realize tight sealing between the stator components at the boundary of the turbine gas flow passage, radial and axial thermal deformation needs to be considered precisely, the thermal design difficulty is very high, a large amount of work needs to be carried out in the aspects of material performance matching, connection structure design and the like, otherwise, the problems of thermal fatigue, deformation, cracks and the like easily occur, the connection part is easy to adhere and decompose, because the surface of parts has roughness, the two parts connected by the bolts are difficult to realize complete sealing actually, and the gas pressure at the inner side of the gas flow passage is far higher than the outer side, gas will inevitably leak from the bolted mating face gap, causing the material to overheat and causing a series of problems.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned problems of the prior art.
Disclosure of Invention
It is an object of the present invention to provide a cooling device that overcomes or at least alleviates at least one of the above-mentioned problems of the prior art.
In order to achieve the aim, the invention provides a pneumatic elastic sealing device for sealing a flow passage boundary part of a gas turbine engine, which comprises a first outer ring, a second outer ring, a positioning part and a sealing part, wherein the first outer ring is arranged on the first outer ring; the first outer ring and the second outer ring are arranged oppositely, and an accommodating space is formed between the first outer ring and the second outer ring; the first outer ring is provided with an annular boss; an annular limiting groove is formed in the second outer ring; the positioning component is arranged on the second outer ring, extends towards the first outer ring along the axial direction of the second outer ring, and is at least partially arranged in the accommodating space, and the part is called as a guide section; the sealing component is arranged on the guide section; wherein the first outer ring is adapted to be connected to a first gas flow path boundary component; the second outer ring is used for connecting with a second fuel flow channel boundary component; the sealing part can be stressed to move on the guide section along the axial direction of the guide section, so that a closed position is formed; in the closed position, the sealing part divides the accommodating space into a first space and a second space and can prevent gas in the first space from exchanging with gas in the second space; the annular limiting groove is matched with the annular boss and used for limiting the moving distance of the sealing component in the axial direction of the guide section.
Preferably, a first mounting hole and a second mounting hole are formed in the sealing part, and the positioning part penetrates through the first mounting hole and the second mounting hole; the first mounting hole is a runway-shaped hole and is matched with the positioning part to limit the movement of the sealing part along the radial direction of the second outer ring and provide compensation for the deformation and expansion of the sealing part along the circumferential direction of the second outer ring; the second mounting hole is a circular hole and is matched with the positioning component to limit the sealing component to move along the radial direction and the circumferential direction of the second outer ring.
Preferably, the sealing component includes a first sealing sheet group and a second sealing sheet group, the first sealing sheet group is provided with the first mounting hole and the second mounting hole, the second sealing sheet group is provided with the first mounting hole and the second mounting hole, the first sealing sheet group is close to the first outer ring device, and the second sealing sheet group is far away from the first outer ring device.
Preferably, the first sealing piece group comprises at least two first sealing pieces with fan-shaped structures, the second sealing piece group comprises at least two second sealing pieces with fan-shaped structures, a first gap is formed between every two adjacent first sealing pieces, a second gap is formed between every two adjacent second sealing pieces, and the first gaps and the second gaps are distributed in a staggered manner along the circumferential direction of the first sealing pieces.
Preferably, the first sealing piece is provided with a vent hole.
Preferably, the positioning component includes a plurality of first positioning pins and a plurality of second positioning pins, each of the first positioning pins and each of the second positioning pins are disposed on the second outer ring, and the number of the first positioning pins is equal to the sum of the numbers of the first mounting holes and the second mounting holes; the number of the second positioning pins is the same as that of the second sealing sheets.
Preferably, one of the first positioning pins passes through one of the first mounting holes or one of the second mounting holes.
Preferably, the second positioning pin extends axially along the second outer ring and toward the first outer ring side.
In another aspect, the invention also provides a gas turbine engine, which is characterized by comprising the pneumatic elastic sealing device.
Preferably, the flow path boundary component is further included, and the first outer ring and the second outer ring are respectively connected with the flow path boundary component.
According to the invention, the double-layer sealing sheets are adopted for series installation, and the gaps of the fan-shaped sections of the two layers of sealing sheets are arranged in a staggered manner, so that the sealing leakage area is greatly reduced, and the sealing efficiency is improved; the sealing sheet is arranged on the fixed first positioning pin to realize radial positioning and axial guiding movement, and the second positioning pin and the annular limiting groove are used for limiting the movement amplitude of the sealing sheet, so that the sealing sheet is guaranteed to realize reliable sealing according to a preset sealing mode; gaps are reserved among the fan-shaped structural fans of the sealing sheet, and the runway-shaped first mounting holes are formed in the sealing sheet, so that thermal deformation expansion is favorably compensated, and the sealing sheet is convenient to mount.
In another aspect, the present invention also provides a gas turbine engine capable of effectively blocking mixing of low-pressure gas in a gas passage with external high-pressure cool air, compared to a gas turbine engine before improvement.
Drawings
FIG. 1 is a schematic structural diagram of a pneumatic elastic device according to an embodiment of the present invention;
FIG. 2 is a schematic view of a sealing member provided in accordance with an embodiment of the present invention in a closed position;
fig. 3 is a schematic structural diagram of a sealing component according to an embodiment of the present invention.
Reference numerals:
10. a first outer ring; 11. an annular boss; 20. a second outer ring; 21. an annular limiting groove; 30. a positioning member; 31. a guide section; 32. a first positioning pin; 33. a second positioning pin; 40. a sealing member; 41. a first mounting hole; 42. a second mounting hole; 43. a first sealing sheet; 44. a second sealing sheet; 45. a vent hole; 50. a first flow path boundary component; 60. a second flow path boundary component.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "central", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, are not to be construed as limiting the scope of the present invention and that the terms "first" and "second" are only used for descriptive purposes and are not to be construed as indicating or implying relative importance.
The embodiment of the invention provides an air pressure elastic sealing device which is used for sealing gaps at the boundary part of an engine flow passage under the action of air pressure pushing.
Referring to fig. 1 and 2, a pneumatic elastic sealing device includes a first outer ring 10, a second outer ring 20, a positioning member 30, and a sealing member 40.
The first outer ring 10 and the second outer ring 20 are arranged oppositely, an accommodating space is formed by the first outer ring 10 and the second outer ring 20, the first outer ring is provided with an annular boss 11, and the second outer ring is provided with an annular limiting groove 21. It is understood that the accommodating space is used for accommodating the annular boss 11, the annular limiting groove 21 and the like, and the accommodating space is communicated with the external space.
In some alternative embodiments, the annular boss 11 is formed by extending toward the second outer ring 20 at an edge of the first outer ring 10 away from the center of the first outer ring 10, and the annular limiting groove 21 is formed by extending toward the first outer ring 10 at an edge of the second outer ring 20 close to the center of the second outer ring 20 and bending in a direction away from the center of the second outer ring 20, so that the edges of the annular boss 11 and the annular limiting groove 21 are located in the same plane to ensure the sealing performance of the sealing device 40.
The positioning member 30 is disposed on the second outer ring 20, extends toward the first outer ring 10 in the axial direction of the second outer ring 20, and is at least partially disposed in the accommodating space, which is referred to as a guide section 31, and the sealing member 40 is disposed on the guide section 31. It is understood that the part of the positioning component 30 extending to the receiving space may be the middle part of the receiving space, or may extend to the side of the first outer ring 10 relative to the second outer ring 20, as long as it is ensured that the extending end of the guide section 31 exceeds the edge part of the annular limiting groove 21, the sealing component 40 can move on the guide section 31 along the axial direction thereof, and the sealing component 40 is partially arranged in the annular limiting groove 21, and the annular limiting groove 21 limits the moving distance of the sealing component 40 on the guide section 31.
The moving distance of the sealing component 40 is limited in a small range through the annular limiting groove 21, and the phenomenon that the moving distance of the sealing component 40 is too large, so that the sealing is invalid due to the fact that the inclination angle is too large in the moving process can be avoided.
The first outer ring 10 is used to connect with the first gas flow path boundary member 50, and the second outer ring 20 is used to connect with the second gas flow path boundary member 60, and it will be understood by those skilled in the art that the first gas flow path boundary member 50 and the second gas flow path boundary member 60 on the turbine engine are provided with gas passages inside, and a gap is formed between the first gas flow path boundary member 50 and the second gas flow path boundary member 60, and the gap is communicated with the accommodating space, during the operation of the turbine engine, low-pressure gas flows inside the gas flow path, and high-pressure cold air exists under the external condition, and due to the pressure difference between the high-pressure cold air and the low-pressure gas, the sealing member 40 is pushed to move on the guide section 31 by the pressure difference, and forms a sealing position.
When the sealing member 40 is in the closed position, the accommodating space is divided into the first space and the second space by the sealing member 40, and the gas in the first space and the gas in the second space can be prevented from exchanging, i.e., the low-pressure gas and the high-pressure cold gas are divided, so that the high-pressure cold gas is prevented from entering the gas flow channel, thereby causing local gas flow disorder and further reducing the performance of the turbine engine.
Referring to fig. 3, the sealing member 40 is provided with a first mounting hole 41 and a second mounting hole 42, and the positioning member 30 passes through the first mounting hole 41 and the second mounting hole 42; wherein the first mounting holes 41 cooperate with the positioning members 30 to limit the movement of the obturating member 40 in the radial direction of the second outer ring 20 and provide compensation for the deformation and expansion of the obturating member in the circumferential direction of the second outer ring 20, preferably, the first mounting holes 41 are racetrack-shaped holes in the circumferential direction of the second outer ring 20, the racetrack-shaped holes are curved and elongated like racetracks and are distributed along the circumferential direction of the second outer ring 20, although the first mounting holes 41 are not limited to the above-mentioned shapes, and may be other shapes, for example, the first mounting holes 41 are elliptical holes whose minor axis direction is the same as the radial direction of the first outer ring 10 or the second outer ring 20; the second mounting hole 42 cooperates with the positioning member 30 for restricting movement of the obturating member 40 in radial and circumferential directions of the second outer ring 20, for example, the second mounting hole 42 is a circular hole. In the sealing process, the first mounting holes 41 can limit the movement of the sealing part 40 along the radial direction of the second outer ring 20 and also can provide compensation for the deformation and expansion of the sealing part 40 along the circumferential direction of the second outer ring 20, the reduction of the sealing performance caused by the deformation of the sealing part 40 is avoided, and the second mounting holes 42 are matched with the first mounting holes 41 to further limit the movement of the sealing part 40 along the radial direction and the circumferential direction of the second outer ring 20.
In some optional embodiments, the sealing component 40 includes a first sealing sheet group and a second sealing sheet group, the first sealing sheet group is provided with a first mounting hole 41 and a second mounting hole 42, the second sealing sheet group is provided with a first mounting hole 41 and a second mounting hole 42, the first sealing sheet group is disposed near the first outer ring 10, and the second sealing sheet group is disposed far from the first outer ring 10. In this embodiment, the first sealing sheet group may be provided with a first mounting hole 41, and the second sealing sheet group may be provided with a second mounting hole 42; or, the first sealing sheet group may be provided with the second mounting hole 42, and the second sealing sheet group is provided with the first mounting hole 41, and the specific arrangement manner thereof may be set by a person skilled in the art in practical application according to specific needs, as long as the shape of the mounting hole is ensured to be unchanged, and the number of the first mounting hole 41 and the second mounting hole 42 is not limited herein.
The first sealing piece group comprises at least two first sealing pieces 43 with a fan-shaped structure, the second sealing piece group comprises at least two second sealing pieces 44 with a fan-shaped structure, a first gap is formed between every two adjacent first sealing pieces 43, a second gap is formed between every two adjacent second sealing pieces 44, and the first gaps and the second gaps are distributed in a staggered mode along the circumferential direction of the first sealing pieces 41. Because the staggered arrangement of first breach and second breach, can take place to compensate the inflation volume when the piece that obturages takes place circumferential deformation to prevent to lead to the performance of obturaging to descend because the piece that obturages warp.
Referring to fig. 2 and 3, the first sealing sheet 43 is provided with the vent hole 45, so that a middle pressure area is formed between the first sealing sheet 43 and the second sealing sheet 44, and thus a certain air pressure gradient is formed on both sides of the first sealing sheet 43 and the second sealing sheet 44, so that the first sealing sheet 43 and the second sealing sheet 44 have a tendency of moving towards the first outer ring 10 side, and finally, the two sealing sheets are tightly attached to realize sealing, and the vent hole 45 is arranged on the first sealing sheet 43, so that the first sealing sheet 43 cannot vibrate due to air vibration in the moving process, and the sealing performance of the sealing part 40 is further facilitated.
In some alternative embodiments, the positioning member 30 includes a plurality of first positioning pins 32 and a plurality of second positioning pins 33, each of the first positioning pins 32 and each of the second positioning pins 33 are provided on the second outer ring 20, wherein the guide section 33 belongs to a portion of the first positioning pins 32 extending toward the first outer ring 10. In order to ensure that the first positioning pins 32 can be installed in the first installation holes 41 and the second installation holes 42, the number of the first positioning pins 32 is equal to the sum of the number of the first installation holes 41 and the number of the second installation holes 42, and the positioning pins are arranged in each installation hole, so that the sealing piece can be prevented from inclining in the moving process, and the sealing effect is influenced.
The number of the second positioning pins 33 is the same as that of the second sealing sheets 44, the second positioning pins 33 extend along the axial direction of the second outer ring 20 and toward the first outer ring 10 side for limiting the movement of the sealing sheets toward the second outer ring 20, and the movement distance of the sealing member 40 in the axial direction of the guide section 31 can be limited within a small range by the cooperation between the second positioning pins 33 and the annular limiting grooves 21, so that the sealing member 40 is prevented from being inclined due to an excessively large movement distance.
In another aspect, the present invention further provides a gas turbine engine, including the above-mentioned gas pressure elastic sealing device, and further including a first flow path boundary member 50 and a second flow path boundary member 60, wherein the first outer ring 10 is connected to the first flow path boundary member 50, and the second outer ring 20 is connected to the second flow path boundary member 60, for sealing a gas passage of the gas turbine engine, and blocking mixing of low-pressure gas in the gas passage and external high-pressure cold gas.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. A pneumatic elastic sealing device is used for sealing a flow passage boundary part of a gas turbine engine and is characterized by comprising a first outer ring, a second outer ring, a positioning part and a sealing part;
the first outer ring and the second outer ring are arranged oppositely, and an accommodating space is formed between the first outer ring and the second outer ring; the first outer ring is provided with an annular boss; an annular limiting groove is formed in the second outer ring;
the positioning component is arranged on the second outer ring, extends towards the first outer ring along the axial direction of the second outer ring, and is at least partially arranged in the accommodating space, and the part is called as a guide section; the sealing component is arranged on the guide section; wherein the content of the first and second substances,
the first outer ring is used for being connected with a first gas flow passage boundary component;
the second outer ring is used for connecting with a second fuel flow channel boundary component;
the sealing part can be stressed to move on the guide section along the axial direction of the guide section, so that a closed position is formed;
in the closed position, the sealing part divides the accommodating space into a first space and a second space and can prevent gas in the first space from exchanging with gas in the second space;
the annular limiting groove is matched with the annular boss and used for limiting the moving distance of the sealing component in the axial direction of the guide section.
2. The pneumatic elastic sealing device of claim 1, wherein the sealing member is provided with a first mounting hole and a second mounting hole, and the positioning member passes through the first mounting hole and the second mounting hole;
the first mounting hole is a runway-shaped hole and is matched with the positioning part to limit the movement of the sealing part along the radial direction of the second outer ring and provide compensation for the deformation and expansion of the sealing part along the circumferential direction of the second outer ring;
the second mounting hole is a circular hole and is matched with the positioning component to limit the sealing component to move along the radial direction and the circumferential direction of the second outer ring.
3. The gas-pressure elastic sealing device according to claim 2, wherein the sealing component comprises a first sealing sheet group and a second sealing sheet group, the first sealing sheet group is provided with the first mounting hole and the second mounting hole, the second sealing sheet group is provided with the first mounting hole and the second mounting hole, the first sealing sheet group is close to the first outer ring device, and the second sealing sheet group is far away from the first outer ring device.
4. The pneumatic elastic sealing device according to claim 3, wherein the first sealing sheet group comprises at least two first sealing sheets with a fan-shaped structure, the second sealing sheet group comprises at least two second sealing sheets with a fan-shaped structure, a first gap is formed between every two adjacent first sealing sheets, a second gap is formed between every two adjacent second sealing sheets, and the first gaps and the second gaps are distributed in a staggered manner along the circumferential direction of the first sealing sheets.
5. The gas pressure spring seal of claim 4 wherein the first seal piece has a vent hole.
6. The pneumatic elastic sealing device according to any one of claims 4 to 5, wherein the positioning member includes a plurality of first positioning pins and a plurality of second positioning pins, each of the first positioning pins and each of the second positioning pins are provided on the second outer ring, and the number of the first positioning pins is equal to the sum of the number of the first mounting holes and the number of the second mounting holes; the number of the second positioning pins is the same as that of the second sealing sheets.
7. The gas spring seal of claim 6 wherein one of said first alignment pins passes through one of said first mounting holes or through one of said second mounting holes.
8. The gas spring seal of claim 6 wherein said second pin extends axially along said second outer ring and toward said first outer ring side.
9. A gas turbine engine comprising a gas pressure elastic sealing device according to any one of claims 1 to 8.
10. The gas turbine engine of claim 9, further comprising a flow path boundary member to which the first and second outer rings are connected, respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810573934.2A CN108952826B (en) | 2018-06-06 | 2018-06-06 | Air pressure elastic sealing device and gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810573934.2A CN108952826B (en) | 2018-06-06 | 2018-06-06 | Air pressure elastic sealing device and gas turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108952826A CN108952826A (en) | 2018-12-07 |
| CN108952826B true CN108952826B (en) | 2020-12-18 |
Family
ID=64493033
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810573934.2A Active CN108952826B (en) | 2018-06-06 | 2018-06-06 | Air pressure elastic sealing device and gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108952826B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110318829A (en) * | 2019-07-19 | 2019-10-11 | 中国航发沈阳发动机研究所 | A kind of elastic piece seal structure |
| CN116399526B (en) * | 2023-06-05 | 2023-09-01 | 中国航发四川燃气涡轮研究院 | Circumferential sealing effect verification device for guide vane of aero-engine |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3486329B2 (en) * | 1997-09-11 | 2004-01-13 | 三菱重工業株式会社 | Sealing device between bolt holes and bolts in gas turbine disks |
| JP5118552B2 (en) * | 2008-05-20 | 2013-01-16 | 三菱重工業株式会社 | Shaft seal device for rotating machinery |
| CN204511526U (en) * | 2015-01-07 | 2015-07-29 | 中国航空动力机械研究所 | Seal arrangement |
| CN104929779B (en) * | 2015-04-30 | 2016-06-22 | 中国科学院工程热物理研究所 | Wheel disc attachment structure and the gas-turbine unit with it |
| CN205000997U (en) * | 2015-09-29 | 2016-01-27 | 中航商用航空发动机有限责任公司 | Seal device , turbine and aeroengine between turbine stator and outer loop support |
| CN206647140U (en) * | 2017-04-07 | 2017-11-17 | 中国航发沈阳发动机研究所 | Turborotor bullet formula seal structure |
-
2018
- 2018-06-06 CN CN201810573934.2A patent/CN108952826B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108952826A (en) | 2018-12-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7744096B2 (en) | Seal device | |
| CN101435346B (en) | Sealing a rotor ring in a turbine stage | |
| JP5110646B2 (en) | Casing between turbines provided with cooling circuit and turbofan provided with the same | |
| CA2803342C (en) | Vane assemblies for gas turbine engines | |
| US7581924B2 (en) | Turbine vanes with airfoil-proximate cooling seam | |
| CN102278147A (en) | Spring loaded seal assembly for turbines | |
| CN101684736B (en) | Shroud for a turbomachine | |
| CN108952826B (en) | Air pressure elastic sealing device and gas turbine engine | |
| CN101943032A (en) | Relate to turbogenerator and be used for the system and the device of the sealed department of turbogenerator | |
| US8353672B2 (en) | Turbine blade damper arrangement | |
| US11629609B2 (en) | Sealing arrangements in gas turbines | |
| BRPI0920178B1 (en) | turbomachine and axial sealing ring gasket for such a turbomachine | |
| US9951638B2 (en) | Shaped rim cavity wing surface | |
| US9677669B2 (en) | Shaft seal device and rotary machine | |
| CN103354859B (en) | Blade profile and platform assembly for supersonic flow | |
| US8684673B2 (en) | Static seal for turbine engine | |
| KR20170018956A (en) | Stator blade, gas turbine, split ring, method for modifying stator blade, and method for modifying split ring | |
| CN102913289A (en) | Outward bristle brush seal design for gas turbine application | |
| CN103485951A (en) | Nozzle mounting and sealing assembly and method of mounting and sealing a nozzle assembly | |
| US9234433B2 (en) | Flap seal spring and sealing apparatus | |
| EP2813762B1 (en) | Combustion equipment | |
| US9829007B2 (en) | Turbine sealing system | |
| JPH0610708A (en) | Packing mechanism of member of turbine engine | |
| US11795876B2 (en) | Outlet seal, outlet seal set, and gas turbine | |
| CN101052833B (en) | Free floating bellows |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |