CN110550227A - Installation method of aircraft engine air inlet protective cover - Google Patents
Installation method of aircraft engine air inlet protective cover Download PDFInfo
- Publication number
- CN110550227A CN110550227A CN201910867792.5A CN201910867792A CN110550227A CN 110550227 A CN110550227 A CN 110550227A CN 201910867792 A CN201910867792 A CN 201910867792A CN 110550227 A CN110550227 A CN 110550227A
- Authority
- CN
- China
- Prior art keywords
- protective cover
- air inlet
- installation
- engine air
- aircraft engine
- 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.)
- Pending
Links
- 230000001681 protective effect Effects 0.000 title claims abstract description 55
- 238000009434 installation Methods 0.000 title claims abstract description 45
- 238000000034 method Methods 0.000 title claims abstract description 21
- 230000006835 compression Effects 0.000 claims 1
- 238000007906 compression Methods 0.000 claims 1
- 238000011900 installation process Methods 0.000 abstract description 3
- 239000004744 fabric Substances 0.000 abstract description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
Classifications
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention discloses an installation method of an aircraft engine air inlet protective cover, which comprises the following steps: a. inflating the protective cloth cover; b. the protective cover supports a certain prefabricated shape to achieve the installation strength; c. and installing a protective cover to the inside of an engine air inlet. The invention is installed by sleeving the traditional protective cover into the outer side of the air inlet, needs to be operated by multiple persons, uses the installation ladder and is improved in a mode of long time consumption in the installation, the protective cover is installed in an inflation mode, after the protective cover is installed in the engine air inlet channel, the inflation shape extrudes the inner wall of the air inlet channel so as to be expanded and fixed, and is used for preventing foreign objects from entering the engine air inlet channel, the operation in the installation process is simple, the installation ladder is not used, the operation is quickly finished by operators, the labor intensity is reduced, the labor is.
Description
Technical Field
The invention relates to the field of installation of aircraft engine inlet duct protective covers, in particular to an installation method of an aircraft engine inlet duct protective cover.
Background
The existing aircraft engine protection method generally uses a protection cloth cover to be sleeved on the outer side of an engine air inlet, the overall dimension of the aircraft engine is generally larger, the top of the engine is as high as 2.5-4m, and therefore direct installation cannot be easily realized on the ground.
Disclosure of Invention
The invention provides an installation method of an aircraft engine inlet protective cover, which aims to solve the problems that an existing engine inlet protective cover is installed by being sleeved on the outer side of an air inlet, an installation ladder is high in working strength, a large number of installation personnel are needed, and time consumption for installation is long.
The technical purpose of the invention is realized by the following technical scheme:
A method for installing an aircraft engine inlet duct shield comprises the following steps: a. inflating the protective cover; b. the protective cover supports a certain prefabricated shape to achieve the installation strength; c. and installing a protective cover to the inside of an engine air inlet. According to the installation method of the protective cover, the prefabricated shape is formed after inflation, the protective cover is installed in a blocking mode on an engine air inlet channel, and the expansion force generated by compressing the inflated shape is fixed on the air inlet channel.
The installation method of the aircraft engine air inlet protective cover comprises the following steps: a, inflating the protective cover; b. the protective cover supports a certain prefabricated shape to achieve the installation strength; c. and installing a protective cover to the inside of an engine air inlet.
In step a, the protective cover is inflatable.
In step b, the prefabricated outline dimension of the protective cover is matched with the inner outline dimension of the engine air inlet.
In step c, when the protective cover is installed, the inflation shape is expanded and fixed by pressing the inner wall of the air inlet passage.
In step c, after the protective cover is installed inside the engine air inlet, foreign objects are prevented from entering the engine air inlet.
The protection casing installation is accomplished, can open the air cock and accomodate after the gassing.
The invention is an improvement on the mode that the traditional engine protective cover is sleeved outside an air inlet, needs to be operated by a plurality of people, uses an installation ladder and consumes long time for installation, adopts an inflation mode and comprises the following steps: a. inflating the protective cover; b. the protective cover supports a certain prefabricated shape to achieve the installation strength; c. mounting a protective cover to the interior of an engine air inlet; the protection casing aerifys the back and forms prefabricated appearance and to the installation of engine intake duct jam, fixes on the intake duct through the tight power of expanding that aerifys the appearance and compressed production, and installation process easy operation does not use the installation ladder, accomplishes fast.
The invention has the beneficial effects that: 1. according to the installation method of the protective cover, the prefabricated shape of the support is installed inside the air inlet channel after inflation, the support strength is high, and the weight is light.
2. The installation method of the protective cover is used for installing and protecting the blockage of the air inlet passage of the engine after inflation, so that a ladder does not need to be installed, the installation time is shortened, and the labor intensity is reduced.
3. The installation method of the protective cover is simple and convenient to install, easy to disassemble, small in size, convenient to carry and capable of being stored after air is discharged, and the efficiency is improved.
Drawings
The invention is further illustrated with reference to the following figures and examples.
Fig. 1 shows a schematic representation of the post-inflation installation of the installation method of an aircraft engine air intake shroud according to the invention.
Fig. 2 shows a schematic illustration of the installation of the protective hood of the installation method of the aircraft engine air intake duct protective hood of the invention into the interior of an air intake duct.
Detailed Description
Fig. 1 shows a schematic illustration of the installation of the aircraft engine air intake shroud according to the invention. The installation method of the aircraft engine air inlet protective cover comprises the following steps: a, inflating the protective cover; b. the protective cover supports a certain prefabricated shape to achieve the installation strength; c. and installing a protective cover to the inside of an engine air inlet.
In step a, the protective cover is inflatable.
In step b, the prefabricated external dimension of the protective cover is matched with the internal dimension of the engine air inlet.
In step c, when the protective cover is installed, the inflation shape is expanded and fixed by pressing the inner wall of the air inlet passage.
in step c, the protective cover is used for blocking foreign objects from entering the engine air inlet after being installed inside the engine air inlet.
The protection casing installation forms prefabricated appearance after aerifing and to the installation of engine intake duct jam, fixes on the intake duct through the tight power of expanding that aerifys the appearance and compressed the production.
After the protective cover is installed, the protective cover serves as a plug on the air inlet channel to play a role of a barrier, so that foreign objects are prevented from entering the engine from the air inlet, and the protective cover plays a role of protecting the engine.
The protection casing installation is accomplished, can open the air cock and accomodate after the gassing.
The invention is characterized in that the traditional protective cover is installed by being sleeved outside an air inlet, the installation is improved in a mode of needing to be operated by a plurality of people, using an installation ladder and consuming long time for installation, the protective cover is installed in an inflation mode, and the method comprises the following steps: a. inflating the protective cover; b. the protective cover supports a certain prefabricated shape to achieve the installation strength; c. and installing a protective cover to the inside of an engine air inlet. The inside back of engine intake duct is installed to the protection casing, thereby it is fixed to aerify the appearance extrusion air inlet duct inner wall to expand tightly, is used for blockking that the foreign object gets into the engine intake duct, and installation process easy operation does not use the installation ladder, and operating personnel accomplishes fast, has reduced intensity of labour, uses manpower sparingly, raises the efficiency.
Claims (5)
1. A method for installing an aircraft engine inlet duct protective cover is characterized by comprising the following steps: a. inflating the protective cover; b. the protective cover supports a certain prefabricated shape to achieve the installation strength; c. and installing a protective cover to the inside of an engine air inlet.
2. The method of installing an aircraft engine inlet duct shield as claimed in claim 1, wherein in step a, the shield is inflatable.
3. The method of installing an aircraft engine intake duct shield according to claim 1, wherein in step b, the shield pre-fabricated profile dimensions match the internal dimensions of the engine intake duct.
4. The method of installing an aircraft engine intake duct shield as defined in claim 1, wherein in step c, the inflation profile is held by compression against the inner wall of the intake duct during installation of the shield.
5. The method of installing an aircraft engine intake duct shield as claimed in claim 1, wherein in step c, the shield is installed and the nozzle is opened to allow air to escape and then stowed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910867792.5A CN110550227A (en) | 2019-09-14 | 2019-09-14 | Installation method of aircraft engine air inlet protective cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910867792.5A CN110550227A (en) | 2019-09-14 | 2019-09-14 | Installation method of aircraft engine air inlet protective cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110550227A true CN110550227A (en) | 2019-12-10 |
Family
ID=68740300
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910867792.5A Pending CN110550227A (en) | 2019-09-14 | 2019-09-14 | Installation method of aircraft engine air inlet protective cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110550227A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111846251A (en) * | 2020-07-10 | 2020-10-30 | 山东太古飞机工程有限公司 | Sand prevention protection device for air inlet, exhaust and tail nozzle of engine |
| WO2021051243A1 (en) * | 2019-09-16 | 2021-03-25 | 田庆亮 | Method for installing air inlet duct protective cover of aircraft engine |
| WO2022032893A1 (en) * | 2020-08-12 | 2022-02-17 | 田庆亮 | Aircraft engine protective cover having inflating device |
-
2019
- 2019-09-14 CN CN201910867792.5A patent/CN110550227A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021051243A1 (en) * | 2019-09-16 | 2021-03-25 | 田庆亮 | Method for installing air inlet duct protective cover of aircraft engine |
| CN111846251A (en) * | 2020-07-10 | 2020-10-30 | 山东太古飞机工程有限公司 | Sand prevention protection device for air inlet, exhaust and tail nozzle of engine |
| CN111846251B (en) * | 2020-07-10 | 2024-03-19 | 山东太古飞机工程有限公司 | Sand-proof protection device for air inlet, exhaust and tail nozzle of engine |
| WO2022032893A1 (en) * | 2020-08-12 | 2022-02-17 | 田庆亮 | Aircraft engine protective cover having inflating device |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |