CN101885383A - Aircraft engine protective cover - Google Patents
Aircraft engine protective cover Download PDFInfo
- Publication number
- CN101885383A CN101885383A CN2009101072523A CN200910107252A CN101885383A CN 101885383 A CN101885383 A CN 101885383A CN 2009101072523 A CN2009101072523 A CN 2009101072523A CN 200910107252 A CN200910107252 A CN 200910107252A CN 101885383 A CN101885383 A CN 101885383A
- Authority
- CN
- China
- Prior art keywords
- air inlet
- aeroengine
- protective cover
- aircraft engine
- inlet storehouse
- 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 18
- 230000004888 barrier function Effects 0.000 claims description 3
- 230000001154 acute effect Effects 0.000 claims 1
- 230000000717 retained effect Effects 0.000 claims 1
- 238000012216 screening Methods 0.000 claims 1
- 230000000903 blocking effect Effects 0.000 abstract 1
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005266 casting Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- LENZDBCJOHFCAS-UHFFFAOYSA-N tris Chemical compound OCC(N)(CO)CO LENZDBCJOHFCAS-UHFFFAOYSA-N 0.000 description 1
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- Emergency Lowering Means (AREA)
Abstract
An aircraft engine shield for preventing a bird from striking or being sucked into an aircraft engine. The aircraft engine air inlet is arranged at the front end of an aircraft engine air inlet and consists of a cylindrical (or elliptic cylindrical) air inlet bin assembly and a conical fairing. The protective cover air inlet bin assembly consists of a plurality of independent air inlet bins and is arranged at the front end of an air inlet of an aircraft engine. The area of the opening of the fairing is larger than that of the air inlet of the aircraft engine, and the fairing is arranged at the front end of the air inlet bin assembly of the protective cover. When a bird collides or is sucked to an aircraft engine, the bird cannot enter the aircraft engine due to the protection of the fairing and can only enter the aircraft engine together with air from the air inlet bin of the protective cover, and the bird moves around the air inlet of the aircraft engine and is thrown away from the aircraft engine after colliding with one or more fragile wind blocking pieces of the independent air inlet bin of the protective cover under the action of huge impact force generated by high-speed relative motion of the bird and the aircraft, so that the aircraft engine is prevented from being damaged. The other independent intake compartments of the hood continue to provide sufficient air to the aircraft engine.
Description
Affiliated technical field
The present invention relates to a kind ofly can prevent that flying bird from banging into or being inhaled into and lead the aeroengine protective cover device that has an accident of system aircraft in the aeroengine.
Background technology
At present, outside the admission port of known aeroengine was directly exposed to, aeroengine was easy to suck or is banged into the system led in the engine by flying bird and has an accident.Each airport is generally adopted the mode of warn birds but can't be stopped this type of accident and takes place at present.
Summary of the invention
Can not prevent automatically that in order to overcome existing aeroengine flying bird from banging into or being inhaled into this deficiency in the aeroengine, the invention provides a kind of aeroengine protective cover, this protective cover can prevent that flying bird from banging into or being inhaled in the aeroengine, do not influence the normal operation of aeroengine again.
The technical solution adopted for the present invention to solve the technical problems is: at the protective cover of a strong shock resistance of aeroengine admission port front end installation, it is made up of cylindrical (or elliptical cylinder-shape) air inlet storehouse assembly and a conical fairing.Air inlet storehouse assembly is installed in aeroengine admission port front end, combine by a plurality of relatively independent air inlet storehouses, the square section gross area of the free air diffuser of air inlet storehouse assembly admission port assembly is not less than the area of aeroengine admission port, and fixed support was beneficial to air flows to the horizontal throw between the fixed support of back before the longitudinal length of air inlet storehouse assembly housing was smaller than air inlet storehouse assembly.At column type air inlet storehouse assembly front end a conical fairing is installed, the bore of fairing opening part is a bit larger tham the bore of aeroengine admission port, to play the effect of protection aeroengine.The concrete division of labor is that fairing is responsible for preventing that flying bird from directly entering in the aeroengine, and air inlet storehouse assembly is responsible for enough air and separation being provided and casting flying bird aside to aeroengine.
The invention has the beneficial effects as follows: when flying bird hits or be attracted to aeroengine, can avoid flying bird to bang into automatically or be inhaled in the aeroengine.The present invention only is made up of several groups of mechanical components, installs and maintain simple and convenient.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples
Fig. 1 is a fundamental diagram of the present invention,
1. fairings among the figure, 2. before fixed support, 3. air inlet storehouse assembly, 4. frangible windscreen sheet, 5. dish out track, 6. back fixed support, 7. air running orbit of flying bird.
Fig. 2 is a longitudinal diagram of the present invention,
1. fairings among the figure, 2. before fixed support, 3. air inlet storehouse housing, 4. back fixed support, 5. air inlet storehouse barrier.
Fig. 3 is a drawing in side sectional elevation of the present invention,
1. air inlet storehouse housings among the figure, 2. air inlet storehouse, 3. air inlet storehouse barrier, 4. back fixed support.
Fig. 4 is an exploded drawings of the present invention,
1. fairings among the figure, 2. air inlet storehouse assembly, 3. frangible windscreen sheet, 4. windscreen sheet platen.
The specific embodiment
In Fig. 1, air inlet storehouse assembly (3) through after fixed support (6) be installed in the front end of aeroengine admission port, fairing (1) is installed in the front end of air inlet storehouse assembly (3).
Under normal circumstances, because of each independent admission port of air inlet storehouse assembly (3) in the outside of fairing (1) and be in the windward side, the square section gross area of the free air diffuser of the admission port assembly of air inlet storehouse assembly (3) is not less than the area of aeroengine admission port, fixed support was to the horizontal throw between the fixed support of back before the longitudinal length of air inlet storehouse assembly housing was smaller than air inlet storehouse assembly, the bore of back fixed support (6) equates that with the bore of aeroengine admission port totally four groups of members have been formed a free air diffuser smoothly, the impulsive force of adding the generation of air high-speed motion is little, be not enough to crash through frangible windscreen sheet (4), under the high-speed combined action during operation of the characteristic of air malleable running orbit and aeroengine strong suction and aircraft, air enters in the aeroengine through each independent admission port of air inlet storehouse assembly (3) and uses for aeroengine.
When flying bird hits or be attracted to aeroengine; because of the bore of fairing (1) bore greater than the aeroengine admission port; under the protection of fairing (1); stoped flying bird directly to enter in the aeroengine; flying bird can only enter from the admission port of air inlet storehouse assembly (3) together with air, and moves at the peripheral space of aeroengine admission port.Because flying bird and air produce very big inertia together during rapid movement, the depth of adding the high speed relative motion of flying bird and aircraft and air inlet storehouse is shorter, flying bird can be dished out from air inlet storehouse assembly (3) having little time to change running orbit in a flash and directly crash through frangible windscreen sheet (4), avoids being inhaled in the aeroengine.Crashed through the independent air inlet storehouse forfeiture part gas supply capacity of frangible windscreen sheet (4), other independent air inlet storehouse of air inlet storehouse assembly (3) continues to supply enough air to the aeroengine dike, ensures that aeroengine can continue normal operation.Even the frangible windscreen sheet (4) in all air inlet storehouses is all crashed through, aeroengine still can suck the part air from the air-flow that runs through air inlet storehouse assembly (3), ensures that aircraft safety lands.Can recover normal condition after treating only to need to change the damage parts after aircraft safety lands.
Claims (8)
1. an aeroengine protective cover is made up of cylindrical air inlet storehouse assembly and conical fairing, it is characterized in that: cylindrical air inlet storehouse assembly is installed in the front end of aeroengine admission port, and conical fairing is installed in the front end of air inlet storehouse assembly.
2. aeroengine protective cover according to claim 1 is characterized in that: the bore of conical fairing opening part is greater than the bore of aeroengine admission port.
3. aeroengine protective cover according to claim 1 is characterized in that: air inlet storehouse assembly is made up of a plurality of relatively independent air inlet storehouses and frangible windscreen sheet and windscreen sheet platen, is shaped as cylindrically, and the member of each windward side is the acute angle design.
4. aeroengine protective cover according to claim 1 is characterized in that: the cross section gross area of the free air diffuser of air inlet storehouse assembly admission port assembly is not less than the area of aeroengine admission port.
5. aeroengine protective cover according to claim 1, it is characterized in that: fixed support was to the horizontal throw between the fixed support of back before the longitudinal length of air inlet storehouse assembly housing was smaller than air inlet storehouse assembly, and gap should be retained between itself and the preceding fixed support, and single air inlet storehouse vertical section is trapezoidal.
6. aeroengine protective cover according to claim 1, it is characterized in that: the fixed support bore is greater than back fixed support bore before the assembly of air inlet storehouse, be fixed on the barrier of air inlet storehouse before and after dividing, preceding fixed support connects fairing, and back fixed support connects the aeroengine admission port.
7. aeroengine protective cover according to claim 1 is characterized in that: screening assembly fixed support before and after center of circle direction will be given prominence in air inlet storehouse is a bit of.
8. aeroengine protective cover according to claim 1 is characterized in that: frangible windscreen sheet and windscreen sheet platen are made semi-circular.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101072523A CN101885383A (en) | 2009-05-12 | 2009-05-12 | Aircraft engine protective cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101072523A CN101885383A (en) | 2009-05-12 | 2009-05-12 | Aircraft engine protective cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101885383A true CN101885383A (en) | 2010-11-17 |
Family
ID=43071523
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009101072523A Pending CN101885383A (en) | 2009-05-12 | 2009-05-12 | Aircraft engine protective cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101885383A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104724294A (en) * | 2013-12-18 | 2015-06-24 | 朱津材 | Manufacturing method of shield capable of preventing foreign matters from entering aviation jet engine |
| CN106235547A (en) * | 2016-09-22 | 2016-12-21 | 周崇飞 | A kind of aeroengine umbrella |
| CN106965944A (en) * | 2016-01-13 | 2017-07-21 | 王振牛 | A kind of method that anti-bird of jet plane air intake duct multi-buffer hits cover |
| CN110027716A (en) * | 2019-05-23 | 2019-07-19 | 山东威西特斯航空科技有限公司 | A kind of installation method of aircraft engine air inlet protection sheet |
-
2009
- 2009-05-12 CN CN2009101072523A patent/CN101885383A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104724294A (en) * | 2013-12-18 | 2015-06-24 | 朱津材 | Manufacturing method of shield capable of preventing foreign matters from entering aviation jet engine |
| CN106965944A (en) * | 2016-01-13 | 2017-07-21 | 王振牛 | A kind of method that anti-bird of jet plane air intake duct multi-buffer hits cover |
| CN106235547A (en) * | 2016-09-22 | 2016-12-21 | 周崇飞 | A kind of aeroengine umbrella |
| CN110027716A (en) * | 2019-05-23 | 2019-07-19 | 山东威西特斯航空科技有限公司 | A kind of installation method of aircraft engine air inlet protection sheet |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20101117 |