CN217176757U - High-temperature sealing device, aircraft engine and aircraft - Google Patents
High-temperature sealing device, aircraft engine and aircraft Download PDFInfo
- Publication number
- CN217176757U CN217176757U CN202220237137.9U CN202220237137U CN217176757U CN 217176757 U CN217176757 U CN 217176757U CN 202220237137 U CN202220237137 U CN 202220237137U CN 217176757 U CN217176757 U CN 217176757U
- Authority
- CN
- China
- Prior art keywords
- groove
- backup pad
- high temperature
- expanded graphite
- support plate
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Gasket Seals (AREA)
Abstract
The utility model provides a high temperature sealing device, aeroengine and aircraft, its be arranged in the aeroengine pressure boost heat chamber sealed, high temperature sealing device includes first backup pad, second backup pad, first expanded graphite, second expanded graphite and goes up the backup pad. A first groove is formed in the inner side of the first supporting plate; the inner side of the second supporting plate is provided with a second groove, and the second groove and the first groove are oppositely arranged; the first expanded graphite is arranged in the first groove and protrudes out of the first groove; the second expanded graphite is arranged in the second groove and protrudes out of the second groove; go up the backup pad, go up the backup pad clamp and locate between first expandable graphite and the second expandable graphite, go up and be formed with first clearance between backup pad and the first backup pad, go up and be formed with the second clearance between backup pad and the second backup pad. The utility model discloses a high temperature sealing device satisfies the requirement of high temperature, sealed and flexible support completely.
Description
Technical Field
The utility model relates to an aeroengine technical field, in particular to high temperature sealing device, aeroengine and aircraft.
Background
In the design of a mechanical system tester, a rear cavity in an aircraft engine needs high-temperature sealing, but under the working condition environment of high temperature, high pressure and cold-hot alternation at 500 ℃, a middle bearing cavity cannot be rigidly supported by a rack, otherwise, the dynamic characteristic of a rotor can be influenced, and the sealing device in the prior art cannot meet the requirements of high-temperature sealing and the dynamic characteristic of the rotor.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to provide a high temperature sealing device, aeroengine and aircraft in order to overcome the defect that prior art's sealing device can't satisfy the high temperature simultaneously and seal and accord with the dynamic characteristic's of rotor demand.
The utility model discloses an above-mentioned technical problem is solved through following technical scheme:
a high temperature seal arrangement for sealing a booster warming cavity in an aircraft engine, the high temperature seal arrangement comprising:
the inner side of the first supporting plate is provided with a first groove;
a second groove is formed in the inner side of the second support plate, and the second groove is opposite to the first groove;
the first expanded graphite is arranged in the first groove and protrudes out of the first groove;
the second expanded graphite is arranged in the second groove and protrudes out of the second groove;
go up the backup pad, it locates to go up the backup pad clamp first expanded graphite with between the second expanded graphite, go up the backup pad with be formed with first clearance between the first backup pad, go up the backup pad with be formed with the second clearance between the second backup pad.
In this scheme, the utility model discloses a high temperature sealing device adopts expanded graphite as sealing material, has ensured to leak gastightly under higher temperature and pressure, and expanded graphite be elastic structure, and last backup pad between be the flexonics to furthest has allowed relative vibration and displacement between the upper and lower backup pad, does not influence the support rigidity between the structure, satisfies the requirement of high temperature, sealed and flexible support completely.
Preferably, the high temperature sealing device further comprises a connector connecting the first support plate and the second support plate.
In this embodiment, with the above structure, the first support plate and the second support plate can drive the first expanded graphite and the second expanded graphite to stably clamp the support rod.
Preferably, the connecting member is a bolt, and the connecting bolt penetrates through the first support plate and the second support plate.
In this aspect, the first expanded graphite and the second expanded graphite can more stably hold the upper support rod by using the above configuration.
Preferably, the first support plate includes:
the inner side of the supporting part is provided with the first groove;
the connecting part is arranged at the lower end of the supporting part, the length of the connecting part in the direction close to the second supporting plate is larger than that of the supporting part, and the connecting part is connected with the first supporting plate and the second supporting plate through the connecting part.
In this scheme, adopt above-mentioned structural style, can make the connection between first backup pad and the second backup pad is more stable firm.
Preferably, the first gap is formed between the first support plate and the connecting portion, and the second gap is formed between the second support plate and the connecting portion.
In this scheme, adopt above-mentioned structural style, can avoid going up the bracing piece with form rigid contact between first backup pad with the second backup pad, influence the rotordynamic characteristic.
Preferably, the first groove and the second groove have a rectangular cross-sectional shape.
In this scheme, adopt above-mentioned structural style, can guarantee that first expanded graphite and second expanded graphite locate stably in first recess and the second recess.
An aeroengine comprises the high-temperature sealing device.
Preferably, the aircraft engine further comprises:
a rotor;
the first supporting plate is arranged between the rotor and the rotor, and the first supporting plate is used for supporting the first supporting plate;
one end of the connecting structure is connected to the upper supporting plate;
and the second fulcrum is arranged between the other end of the connecting mechanism and the rotor and is used for supporting the rotor together with the first fulcrum.
In this scheme, adopt above-mentioned structural style, can solve among the aeroengine fulcrum support rigidity too big and the sealed problem of high temperature.
An aircraft comprising an aircraft engine as described above.
The utility model discloses an actively advance the effect and lie in: the utility model discloses a high temperature sealing device adopts expanded graphite as sealing material, has ensured to leak tightly under higher temperature and pressure, and expanded graphite be elastic structure, and last be the flexonics between the backup pad to furthest has allowed relative vibration and displacement between the backup pad from top to bottom, does not influence the support rigidity between the structure, satisfies the requirement of high temperature, sealed and flexible support completely.
Drawings
Fig. 1 is a schematic structural view of a high-temperature sealing device according to a preferred embodiment of the present invention.
Fig. 2 is a schematic view of the whole installation of the high-temperature sealing device according to the preferred embodiment of the present invention.
Description of reference numerals:
First expanded graphite 2
Upper supporting plate 3
Second expanded graphite 4
Connecting piece 6
Pressurizing and warming cavity 8
Detailed Description
The present invention will be more clearly and completely described below with reference to the accompanying drawings.
As shown in fig. 1-2, a high-temperature sealing device for sealing a pressurizing and warming cavity 8 in an aircraft engine comprises a first support plate 1, a second support plate 5, a first expanded graphite 2, a second expanded graphite 4 and an upper support plate 3.
A first groove is formed in the inner side of the first supporting plate 1; a second groove is formed in the inner side of the second supporting plate 5, and the second groove and the first groove are arranged oppositely; the first expanded graphite 2 is arranged in the first groove and protrudes out of the first groove; the second expanded graphite 4 is arranged in the second groove and protrudes out of the second groove; as shown in fig. 1 to 2, the first and second grooves have a rectangular cross-sectional shape, so that it is possible to ensure that the first and second expanded graphite 2 and 4 are stably disposed in the first and second grooves.
Go up backup pad 3 and press from both sides and locate between first expanded graphite 2 and second expanded graphite 4, go up and be formed with first clearance between backup pad 3 and the first backup pad 1, as shown in figure 1, in this implementation, first clearance includes the clearance between the left side wall of last backup pad 3 and the right side wall of first backup pad 1, still includes the interval that forms between the lower lateral wall of last backup pad 3 and the first backup pad to it is formed with the second clearance to go up between backup pad 3 and the second backup pad 5.
In this embodiment, the utility model discloses a high temperature sealing device adopts expanded graphite as sealing material, has ensured to leak gastightly under higher temperature and pressure, and expanded graphite be elastic structure, and last backup pad 3 between be the flexible contact to furthest has allowed relative vibration and displacement between the upper and lower backup pad, does not influence the support rigidity between the structure, satisfies the requirement of high temperature, sealed and flexible support completely.
As shown in fig. 1-2, the high temperature sealing device further comprises a connecting member 6, and the connecting member 6 connects the first support plate 1 and the second support plate 5. In this embodiment, the connecting member 6 is a bolt, and the connecting bolt penetrates through the first support plate 1 and the second support plate 5. Of course, it should be understood by those skilled in the art that the specific form of the connector is not limited to a bolt.
In this embodiment, the first support plate 1 and the second support plate 5 can be tightened by the connecting member 6, thereby bringing the first expanded graphite 2 and the second expanded graphite 4 to stably hold the upper support rods.
As shown in fig. 1-2, the first support plate 1 includes a support portion and a connection portion, and a first groove is formed on the inner side of the support portion; the connecting part is arranged at the lower end of the supporting part, the length of the connecting part in the direction close to the second supporting plate 5 is larger than that of the supporting part, and the connecting part 6 is connected with the first supporting plate 1 and the second supporting plate 5 through the connecting part.
In the present embodiment, the connection portion is provided to make the connection between the first support plate 1 and the second support plate 5 more stable and firm.
As shown in fig. 1-2, a first gap is formed between the first support plate 1 and the connection portion, and a second gap is formed between the second support plate 5 and the connection portion.
In the present embodiment, the first gap and the second gap are provided to avoid rigid contact between the upper support rod and the first support plate 1 and the second support plate 5, which affects the dynamic characteristics of the rotor 10.
As shown in fig. 2, the present embodiment also provides an aircraft engine, and the aircraft engine includes the high-temperature sealing device.
The aircraft engine further comprises a rotor 10, a first fulcrum 7, a connection mechanism and a second fulcrum 9. The first supporting point 7 is arranged between the first supporting plate 1 and the rotor 10, and the first supporting point 7 is used for supporting the first supporting plate 1; one end of the connecting structure is connected with the upper supporting plate 3; a second fulcrum 9 is provided between the other end of the connecting mechanism and the rotor 10 for supporting the rotor 10 simultaneously with the first fulcrum 7.
In the embodiment, the problems of excessive supporting rigidity of the fulcrum in the aircraft engine and high-temperature sealing can be solved by adopting the structural form.
The embodiment also provides an aircraft which comprises the aero-engine.
Although specific embodiments of the present invention have been described above, it will be understood by those skilled in the art that this is by way of example only and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and the principles of the present invention, and these changes and modifications are all within the scope of the present invention.
Claims (9)
1. A high temperature seal arrangement for sealing a booster and booster warm up cavity in an aircraft engine, the high temperature seal arrangement comprising:
the inner side of the first supporting plate is provided with a first groove;
a second groove is formed in the inner side of the second support plate, and the second groove is opposite to the first groove;
the first expanded graphite is arranged in the first groove and protrudes out of the first groove;
the second expanded graphite is arranged in the second groove and protrudes out of the second groove;
go up the backup pad, it locates to go up the backup pad clamp first expanded graphite with between the second expanded graphite, go up the backup pad with be formed with first clearance between the first backup pad, go up the backup pad with be formed with the second clearance between the second backup pad.
2. The high temperature seal of claim 1, further comprising a connector connecting the first support plate and the second support plate.
3. The high temperature seal of claim 2, wherein the connector is a bolt extending through the first and second support plates.
4. The high temperature seal of claim 2, wherein the first support plate comprises:
the inner side of the supporting part is provided with the first groove;
the connecting part is arranged at the lower end of the supporting part, the length of the connecting part in the direction close to the second supporting plate is larger than that of the supporting part, and the connecting part is connected with the first supporting plate and the second supporting plate through the connecting part.
5. The high temperature seal of claim 4, wherein the first gap is formed between the first support plate and the connection portion and the second gap is formed between the second support plate and the connection portion.
6. The high temperature seal of claim 1 wherein said first groove and said second groove are rectangular in cross-sectional shape.
7. An aircraft engine, characterized in that it comprises a high-temperature sealing device according to any one of claims 1 to 6.
8. The aircraft engine of claim 7, further comprising:
a rotor;
the first supporting plate is arranged between the rotor and the rotor, and the first supporting plate is used for supporting the first supporting plate;
one end of the connecting mechanism is connected to the upper supporting plate;
and the second fulcrum is arranged between the other end of the connecting mechanism and the rotor and is used for supporting the rotor together with the first fulcrum.
9. An aircraft, characterized in that it comprises an aircraft engine according to claim 7 or 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220237137.9U CN217176757U (en) | 2022-01-28 | 2022-01-28 | High-temperature sealing device, aircraft engine and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220237137.9U CN217176757U (en) | 2022-01-28 | 2022-01-28 | High-temperature sealing device, aircraft engine and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217176757U true CN217176757U (en) | 2022-08-12 |
Family
ID=82738208
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220237137.9U Active CN217176757U (en) | 2022-01-28 | 2022-01-28 | High-temperature sealing device, aircraft engine and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217176757U (en) |
-
2022
- 2022-01-28 CN CN202220237137.9U patent/CN217176757U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN217176757U (en) | High-temperature sealing device, aircraft engine and aircraft | |
| CN215721616U (en) | Dismantle metal compensator fast | |
| CN205478805U (en) | Sealed screw of manometer | |
| CN214222385U (en) | Direct-buried waveform expansion joint | |
| CN213871652U (en) | Double-layer expansion joint easy to install | |
| CN210441647U (en) | Heating furnace without pull rod | |
| CN203326522U (en) | Adjustable shell telescopic structure for isolated-phase bus | |
| CN215566870U (en) | Novel plug body heat preservation structure of high-temperature fan | |
| CN203656180U (en) | Wedge-shaped self-tightening type sealing part for manhole door of pressure stabilizer | |
| CN220582013U (en) | Heat insulation structure of directly buried heat supply pipeline | |
| CN111504847A (en) | Crack detection device and method for automobile casting cylinder body | |
| CN219472207U (en) | Integrated gasket structure for exhaust manifold sealing | |
| CN220892293U (en) | Bimetal thermal compensation sealing device of air preheater | |
| CN211476729U (en) | Built-in air duct structure of assembled tunnel roasting kiln | |
| CN216192530U (en) | Vacuum heat treatment furnace with long service life | |
| CN219203281U (en) | Battery cooling tube, battery module and battery pack | |
| CN221047139U (en) | Heat pipe cutting and sealing device | |
| CN210950378U (en) | Floating sealed type rotary compensator | |
| CN215258213U (en) | Heat supply insulating pipe for reducing heat loss of heat insulating pipe support | |
| CN216267646U (en) | 3D print platform and 3D printer | |
| CN201352065Y (en) | Spring flexible pressing device | |
| CN211875398U (en) | Unconstrained expansion joint | |
| CN117664775A (en) | Temperature-driven crimping IGBT tangential fretting experiment system and method | |
| CN217634514U (en) | Nonmetal expansion joint convenient to adjust installation and use | |
| CN210653320U (en) | Novel automobile integrated into one piece supporting beam |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |