LU501428B1 - Aero-engine controller sealing apparatus - Google Patents
Aero-engine controller sealing apparatus Download PDFInfo
- Publication number
- LU501428B1 LU501428B1 LU501428A LU501428A LU501428B1 LU 501428 B1 LU501428 B1 LU 501428B1 LU 501428 A LU501428 A LU 501428A LU 501428 A LU501428 A LU 501428A LU 501428 B1 LU501428 B1 LU 501428B1
- Authority
- LU
- Luxembourg
- Prior art keywords
- sealing
- jacket
- end cover
- binding post
- shell
- Prior art date
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 84
- 238000009434 installation Methods 0.000 claims abstract description 46
- 239000011521 glass Substances 0.000 claims abstract description 34
- 230000003746 surface roughness Effects 0.000 claims abstract description 4
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 claims description 13
- 239000007769 metal material Substances 0.000 claims description 10
- 239000000843 powder Substances 0.000 claims description 10
- 238000005245 sintering Methods 0.000 claims description 7
- 238000003466 welding Methods 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 6
- 238000002360 preparation method Methods 0.000 claims description 6
- KGWWEXORQXHJJQ-UHFFFAOYSA-N [Fe].[Co].[Ni] Chemical compound [Fe].[Co].[Ni] KGWWEXORQXHJJQ-UHFFFAOYSA-N 0.000 claims description 5
- 239000000956 alloy Substances 0.000 claims description 5
- 229910045601 alloy Inorganic materials 0.000 claims description 5
- 229910000833 kovar Inorganic materials 0.000 claims description 5
- 239000000446 fuel Substances 0.000 abstract description 22
- 238000002791 soaking Methods 0.000 abstract description 6
- 230000002093 peripheral effect Effects 0.000 description 5
- 239000003350 kerosene Substances 0.000 description 4
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000007654 immersion Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000035699 permeability Effects 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
- H02K5/22—Auxiliary parts of casings not covered by groups H02K5/06-H02K5/20, e.g. shaped to form connection boxes or terminal boxes
- H02K5/225—Terminal boxes or connection arrangements
-
- 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
- F02C7/22—Fuel supply systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M37/00—Apparatus or systems for feeding liquid fuel from storage containers to carburettors or fuel-injection apparatus; Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines
- F02M37/04—Feeding by means of driven pumps
- F02M37/08—Feeding by means of driven pumps electrically driven
- F02M37/10—Feeding by means of driven pumps electrically driven submerged in fuel, e.g. in reservoir
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G15/00—Cable fittings
- H02G15/013—Sealing means for cable inlets
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K11/00—Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection
- H02K11/30—Structural association with control circuits or drive circuits
- H02K11/33—Drive circuits, e.g. power electronics
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
- H02K5/10—Casings or enclosures characterised by the shape, form or construction thereof with arrangements for protection from ingress, e.g. water or fingers
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
- H02K5/12—Casings or enclosures characterised by the shape, form or construction thereof specially adapted for operating in liquid or gas
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/20—Lubricating arrangements using lubrication pumps
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B17/00—Insulators or insulating bodies characterised by their form
- H01B17/26—Lead-in insulators; Lead-through insulators
- H01B17/30—Sealing
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Aviation & Aerospace Engineering (AREA)
- Motor Or Generator Frames (AREA)
Abstract
Described is an aero-engine controller sealing apparatus, which includes a shell; an end cover is installed inside the shell in a sealing manner, a binding post assembly is installed on the end cover by threads, the binding post assembly includes a jacket, binding posts and glass bodies, and the jacket is provided with a plurality of binding posts; the surface roughness of contact positions of the shell, the end cover, the jacket and sealing rings is greater than or equal to Ra 1.6; an installation bearing platform abutted against the shell is arranged on one side, close to the shell, of the end cover; sealing installation grooves are provided respectively on the upper side and the lower side of the installation bearing platform; sealing installation grooves are provided on the side walls, close to the installation bearing platform, of the end cover; and the sealing rings are arranged in the sealing installation grooves. The present invention can block the fuel from entering inner passages of a controller, and prevent the failure of components in the controller caused by the soaking of leaked fuel, thereby ensuring the reliability of a brushless DC motor controller.
Description
AERO-ENGINE CONTROLLER SEALING APPARATUS LU501428 Technical Field The present invention belongs to the technical field of aviation fuel pumps, and particularly relates to an aero-engine controller sealing apparatus.
Background A fully-immersed brushless DC fuel pump is fully immersed in a fuel tank, and a motor body needs fuel to enter the inside to realize lubrication and circulating heat dissipation of bearings, while a controller adopts electronic components and control modules to drive a brushless motor to rotate. The fuel that enters the controller may lead to the failure of the electronic components and control modules, which may cause the product malfunction. Therefore, the controller sealing plays an important role in the reliability of the controller. The peripheral structure of connection between the motor body and the controller is all made of metal materials and is sealed by sealing rings; the sealing way is a mature technology, which can ensure the sealing; the key to the sealing of the controller lies in the sealing of lead wires between the motor body and the controller; and an external insulating layer of the lead wire is very smooth, and the aviation fuel is high in permeability, so that the reliable sealing of the lead wires cannot be realized by conventional sealing ways such as adhesives, sealing rings, etc.
The electronic components and the control modules can be completely encapsulated inside the controller through the adhesive, which can also avoid the fuel soaking. However, to completely encapsulate the electronic components and the control modules inside the controller is not conducive to the heat dissipation of the device, and may also affect the reliability of the controller; and the controller is not repairable, which may greatly increase the manufacturing cost of the product. Therefore, it is urgent to solve the problem of the controller sealing without affecting the reliability of the components in the controller.
Summary A purpose of the present invention is to provide an aero-engine controller sealing apparatus, which aims at solving the above problems.
The present invention is implemented mainly through the following technical solutions: An aero-engine controller sealing apparatus includes a shell, wherein the shell is fixedly connected with a motor body through a bolt; an end cover is installed inside the shell in a sealing manner, a binding post assembly is installed on the end cover by threads, and a sealing ring is arranged between the binding post assembly and the end cover; the binding post assembly includes a jacket, binding posts and glass bodies, a plurality of binding posts are arranged on the jacket, and the glass bodies are filled between the jacket and the binding posts, and are integrally formed by high-temperature sintering; connecting lead wires of the motor body and the controller are welded on the corresponding binding posts respectively; an installation bearing platform _ 10g abutted against the shell is arranged on one side, close to the shell, of the end cover; sealing installation grooves are provided respectively on the upper side and lower side of the installation bearing platform; sealing installation grooves are provided on the side walls, close to the installation bearing platform, of the end cover, and the sealing rings are arranged in the sealing installation grooves; and the surface roughness of contact positions of the shell, the end cover, the jacket and the sealing rings is greater than or equal to Ra 1.6.
The end cover is provided with the installation bearing platform, which increases the sealing area; and the shell is connected with the motor body through the bolt, and the contact between the installation bearing platform of the end cover and the shell is pressed at the same time. Through the installation bearing platform and the sealing installation grooves that are vertically arranged on adjacent side surfaces of the end cover, the all-round sealing connection is realized, the sealing effect is good, and the practicability is good.
In the application process of the present invention, the motor body is a brushless DC motor which may be immersed in aviation kerosene RP-3. The fuel pump is installed in an immersion manner and wholly immersed in the aviation kerosene RP-3. The controller is fixedly connected with the motor body through the bolt, and the shell and the motor body are correspondingly provided with bolt installation holes for connecting the controller and the motor body and pressing the sealing rings to realize the sealing of the peripheral structure. The shell, the end cover and the binding post assembly realize the sealing of the peripheral structure through the sealing rings; and the jacket, the binding posts and the glass bodies are integrated into the binding post assembly through the high-temperature sintering, so that the sealing of the connecting lead wires of the motor body and the controller is realized. The sealing structure can realize the sealing of the immersion-installation fuel pump controller, blocks the fuel from entering internal passages of the controller, and prevents the failure of the components inside the controller caused by the soaking of leaked fuel, thereby ensuring the reliability of the brushless DC motor controller.
To better implement the present invention, further, the end cover is provided with an installation threaded hole, the outer side of the jacket is correspondingly provided with external threads, and the outer side, close to the end cover, of the top of the jacket is circumferentially provided with the sealing installation grooves.
To better implement the present invention, further, the jacket is provided with installation filling holes for installing the binding posts and the glass bodies; and each binding post is provided with a lead wire welding hole, and two ends are provided with inclined surfaces. An aperture d of the lead wire welding hole is determined by the diameter of a metal wire of the lead wire, and two ends of the binding post are provided with the inclined surfaces to facilitate welding of the lead wire.
To better implement the present invention, further, the outer diameter D2 of the binding post is less than the outer diameter D1 of the installation filling hole by 1.5mm-2mm; and a length L of one side, extending out of the jacket, of the binding post is 3.5 mm. The length setting of he 501428 binding post ensures that the length L of two ends, extending out of a plane A and a plane B of the jacket, is generally about 3.5 mm. To better implement the present invention, further, an expansion coefficient of the glass body is the same as the expansion coefficient of the jacket and the binding post; a preparation material of the glass body is any one of DM305, DM308 and DM320 glass powder; and the jacket and the binding post are made of metal materials. To better implement the present invention, further, the preparation material of the glass body is DM308 glass powder, and the jacket and the binding post are made of 4J29 iron-nickel-cobalt Kovar alloy. The metal material generally selects 4J29 iron-nickel-cobalt Kovar alloy, and the expansion coefficient thereof is 4.7x10°/°C. Since the DM308 glass powder has higher sealing binding force than other glass powder after the sealing, DM308 is generally used, and the expansion coefficient thereof is 4.8x10%/°C. The metal material and the glass body are basically consistent in expansion coefficient, so that the tight combination of the sintering formation can be ensured to realize the sealing. The lead wires of the motor body and the controller only need to be welded on the corresponding binding posts. Since the binding post is made of the metal material, the conduction of the motor lead wire can be realized. The present invention has the beneficial effects: The sealing structure of the present invention can realize the sealing of the immersion- installation fuel pump controller, blocks the fuel from entering the internal passages of the controller, and prevents the failure of the components inside the controller caused by the soaking of leaked fuel, thereby ensuring the reliability of the brushless DC motor controller. At the same time, when the controller fails, the controller may be dismantled for repairing, thereby improving the repairability of the product.
Description of Drawings Fig. 1 is a structural schematic diagram of the present invention; and Fig. 2 is a structural schematic diagram of a binding post assembly. In the figures: 1, binding post assembly; 2, sealing ring; 3, shell; 4, controller; 5, connecting lead wire; 6, end cover; 7, motor body; 8, glass body; 9, binding post; 10, jacket; 11, external threads; 12, bolt. Detailed Description Embodiment 1: An aero-engine controller sealing apparatus comprises a shell 3. The shell 3 is fixedly connected with a motor body 7 through a bolt 12; an end cover 6 is installed inside the shell 3 in a sealing manner, a binding post assembly 1 is installed on the end cover 6 by threads, and a sealing ring 2 is arranged between the binding post assembly 1 and the end cover 6; the binding post assembly 1 comprises a jacket 10, binding posts 9 and glass bodies 8, a plurality of binding 01428 posts 9 are arranged on the jacket 10, and the glass bodies 8 are filled between the jacket 10 and the binding posts 9), and are integrally formed by high-temperature sintering; connecting lead wires 5 of the motor body 7 and the controller 4 are welded on the corresponding binding posts 9 respectively; an installation bearing platform abutted against the shell 3 is arranged on one side, close to the shell 3, of the end cover 6; sealing installation grooves are provided respectively on the upper side and the lower side of the installation bearing platform; sealing installation grooves are provided on the side walls, close to the installation bearing platform, of the end cover 6, and the sealing rings 2 are arranged in the sealing installation grooves; and the surface roughness of contact positions of the shell 3, the end cover 6, the jacket 10 and the sealing rings 2 is greater than or equal to Ra 1.6. The sealing rings 2 can be configured as O sealing rings.
In the application process of the present invention, the motor body 7 is a brushless DC motor which may be immersed in aviation kerosene RP-3. The fuel pump is installed in an immersion manner and wholly immersed in the aviation kerosene RP-3. The controller 4 is fixedly connected with the motor body 7 through the bolt 12, and the shell 3 and the motor body 7 are correspondingly provided with installation holes of the bolt 12 for connecting the controller 4 and the motor body 7 and pressing the sealing rings 2 to realize the sealing of the peripheral structure. The shell 3, the end cover 6 and the binding post assembly 1 realize the sealing of the peripheral structure through the sealing rings 2; and the jacket 10, the binding posts 9 and the glass bodies 8 are integrated into the binding post assembly 1 through the high-temperature sintering, so that the sealing of the connecting lead wires 5 of the motor body 7 and the controller 4 is realized. The sealing structure can realize the sealing of the immersion-installation fuel pump controller 4, blocks the fuel from entering internal passages of the controller 4, and prevents the failure of the components inside the controller 4 caused by the soaking of leaked fuel, thereby ensuring the reliability of the brushless DC motor controller 4.
Embodiment 2 The present embodiment is optimized on the basis of embodiment 1. The end cover 6 is provided with an installation threaded hole, the outer side of the jacket 10 is correspondingly provided with external threads 11, and the outer side, close to the end cover 6, of the top of the jacket 10 is circumferentially provided with the sealing installation grooves.
Further, the jacket 10 is provided with installation filling holes for installing the binding posts 9 and the glass bodies 8; and each binding post 9 is provided with a lead wire welding hole, and two ends are provided with inclined surfaces. An aperture d of the lead wire welding hole is determined by the diameter of a metal wire of the lead wire, and two ends of the binding post 9 are provided with the inclined surfaces to facilitate welding of the lead wire.
Further, the outer diameter D2 of the binding post 9 is less than the outer diameter D1 of the installation filling hole by 1.5mm-2mm; and a length L of one side, extending out of the jacket 10,
of the binding post 9 is 3.5 mm.
The length setting of the binding post 9 ensures that the length L 501428 of two ends, extending out of a plane A and a plane B of the jacket 10, is generally about 3.5 mm.
The sealing structure of the present invention can realize the sealing of the immersion- installation fuel pump controller 4, blocks the fuel from entering the internal passages of the 5 controller 4, and prevents the failure of the components inside the controller 4 caused by the soaking of leaked fuel, thereby ensuring the reliability of the brushless DC motor controller 4. At the same time, when the controller 4 fails, the controller may be dismantled for repairing, thereby improving the repairability of the product.
Other parts of the present embodiment are the same as those of embodiment 1, and thus will not be described.
Embodiment 3: The present embodiment is optimized on the basis of embodiment 1 or 2. An expansion coefficient of the glass body 8 is the same as the expansion coefficient of the jacket 10 and the binding post 9; a preparation material of the glass body 8 is any one of DM305, DM308 and DM320 glass powder; and the jacket 10 and the binding post 9 are made of metal materials.
Further, the preparation material of the glass body 8 is DM308 glass powder, and the jacket 10 and the binding post 9 are made of 4J29 iron-nickel-cobalt Kovar alloy.
The metal material generally selects 4J29 iron-nickel-cobalt Kovar alloy, and the expansion coefficient thereof is 4.7x10%/°C.
Since the DM308 glass powder has higher sealing binding force than other glass powder after the sealing, DM308 is generally used, and the expansion coefficient thereof is 4.8x10%/°C.
The metal material and the glass body 8 are basically consistent in expansion coefficient, so that the tight combination of the sintering formation can be ensured to realize the sealing.
The lead wires of the motor body 7 and the controller 4 only need to be welded on the corresponding binding posts 9. Since the binding post 9 is made of the metal material, the conduction of the motor lead wire can be realized.
Other parts of the present embodiment are the same as those of embodiment 1 or 2, and thus will not be described.
The above descriptions are only the preferred embodiments of the present invention and are not the limit to the present invention in any form.
Any simple modification and equivalent change made to the above embodiments according to the technical essence of the present invention shall be covered by the protection scope of the present invention.
Claims (6)
1. An aero-engine controller sealing apparatus, comprising a shell (3), wherein the shell (3) is fixedly connected with a motor body (7) through a bolt (12); an end cover (6) is installed inside the shell (3) in a sealing manner, a binding post assembly (1) is installed on the end cover (6) by threads, and a sealing ring (2) is arranged between the binding post assembly (1) and the end cover (6); the binding post assembly (1) comprises a jacket (10), binding posts (9) and glass bodies (8), a plurality of binding posts (9) are arranged on the jacket (10), and the glass bodies (8) are filled between the jacket (10) and the binding posts (9), and are integrally formed by high-temperature sintering; connecting lead wires (5) of the motor body (7) and the controller (4) are welded on the corresponding binding posts (9) respectively, an installation bearing platform abutted against the shell (3) is arranged on one side, close to the shell (3), of the end cover (6); sealing installation grooves are provided respectively on the upper side and the lower side of the installation bearing platform; sealing installation grooves are provided on the side walls, close to the installation bearing platform, of the end cover (6), and the sealing rings (2) are arranged in the sealing installation grooves; and the surface roughness of contact positions of the shell (3), the end cover (6), the jacket (10) and the sealing rings (2) is greater than or equal to Ra 1.6.
2. The aero-engine controller sealing apparatus according to claim 1, wherein the end cover (6) is provided with an installation threaded hole, the outer side of the jacket (10) is correspondingly provided with external threads (11), and the outer side, close to the end cover (6), of the top of the jacket (10) is circumferentially provided with the sealing installation grooves.
3. The aero-engine controller sealing apparatus according to claim 2, wherein the jacket (10) is provided with installation filling holes for installing the binding posts (9) and the glass bodies (8); and each binding post (9) is provided with a lead wire welding hole, and two ends are provided with inclined surfaces.
4. The aero-engine controller sealing apparatus according to claim 3, wherein the outer diameter D2 of the binding post (9) is less than the outer diameter D1 of the installation filling hole by 1.5mm-2mm; and a length L of one side, extending out of the jacket (10), of the binding post (9) is 3.5 mm.
5. The aero-engine controller sealing apparatus according to any one of claims 1-4, wherein an expansion coefficient of the glass body (8) is the same as the expansion coefficient of the jacket (10) and the binding post (9); a preparation material of the glass body (8) is any one 501428 of DM305, DM308 and DM320 glass powder; and the jacket (10) and the binding post (9) are made of metal materials.
6. The aero-engine controller sealing apparatus according to claim 5, wherein the preparation material of the glass body (8) is DM308 glass powder, and the jacket (10) and the binding post (9) are made of 4J29 iron-nickel-cobalt Kovar alloy.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110431835.2A CN113193689A (en) | 2021-04-21 | 2021-04-21 | Aeroengine control end sealing device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| LU501428A1 LU501428A1 (en) | 2022-10-21 |
| LU501428B1 true LU501428B1 (en) | 2022-11-08 |
Family
ID=76977978
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| LU501428A LU501428B1 (en) | 2021-04-21 | 2021-12-22 | Aero-engine controller sealing apparatus |
Country Status (3)
| Country | Link |
|---|---|
| CN (1) | CN113193689A (en) |
| LU (1) | LU501428B1 (en) |
| WO (1) | WO2022222525A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113193689A (en) * | 2021-04-21 | 2021-07-30 | 成都凯天电子股份有限公司 | Aeroengine control end sealing device |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10360226A1 (en) * | 2003-12-20 | 2005-07-21 | Mtu Aero Engines Gmbh | Gas turbine, in particular aircraft engine |
| CN201112865Y (en) * | 2007-10-27 | 2008-09-10 | 贵州航天电器股份有限公司 | One-way high-pressure integral air-tight electric connector |
| CN103474831B (en) * | 2013-09-23 | 2015-11-18 | 苏州华旃航天电器有限公司 | A kind of glass sintering high-temperature high-voltage sealing electric connector |
| CN105449420B (en) * | 2015-12-09 | 2018-07-31 | 西安赛尔电子材料科技有限公司 | A kind of elongated hole glass sealing spininess electric connector and preparation method thereof |
| DE102016100394A1 (en) * | 2016-01-12 | 2017-07-13 | Hanon Systems | Electric current feed-through arrangement and method for its manufacture and assembly |
| CN107257189A (en) * | 2017-08-16 | 2017-10-17 | 贵州航天林泉电机有限公司 | A kind of integrated immersion oil brshless DC motor |
| CN207691658U (en) * | 2017-11-17 | 2018-08-03 | 上海航天有线电厂有限公司 | A kind of sealing structure of aircraft oil pump brushless direct current motor |
| CN208656564U (en) * | 2018-07-24 | 2019-03-26 | 上海连成（集团）有限公司 | A kind of secondary inlet wire connection sealing structure of submersible sewage pump cable |
| CN113193689A (en) * | 2021-04-21 | 2021-07-30 | 成都凯天电子股份有限公司 | Aeroengine control end sealing device |
-
2021
- 2021-04-21 CN CN202110431835.2A patent/CN113193689A/en active Pending
- 2021-12-22 LU LU501428A patent/LU501428B1/en active IP Right Grant
- 2021-12-22 WO PCT/CN2021/140562 patent/WO2022222525A1/en active Application Filing
Also Published As
| Publication number | Publication date |
|---|---|
| WO2022222525A1 (en) | 2022-10-27 |
| CN113193689A (en) | 2021-07-30 |
| LU501428A1 (en) | 2022-10-21 |
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| Date | Code | Title | Description |
|---|---|---|---|
| FG | Patent granted |
Effective date: 20221108 |