CN109649667A - A kind of method of ventilation of aircraft engine nacelle - Google Patents
A kind of method of ventilation of aircraft engine nacelle Download PDFInfo
- Publication number
- CN109649667A CN109649667A CN201811559501.8A CN201811559501A CN109649667A CN 109649667 A CN109649667 A CN 109649667A CN 201811559501 A CN201811559501 A CN 201811559501A CN 109649667 A CN109649667 A CN 109649667A
- Authority
- CN
- China
- Prior art keywords
- ventilation
- ventilation opening
- aircraft engine
- engine nacelle
- equipment
- 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
- 238000009423 ventilation Methods 0.000 title claims abstract description 86
- 238000000034 method Methods 0.000 title claims abstract description 15
- 238000005192 partition Methods 0.000 claims abstract description 10
- 238000001816 cooling Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 4
- 230000029058 respiratory gaseous exchange Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008450 motivation Effects 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
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Ventilation (AREA)
Abstract
A kind of method of ventilation of aircraft engine nacelle, equipment ventilation duct is equipped in aircraft engine nacelle, ventilation opening is equipped on aircraft engine nacelle, the middle part of the ventilation opening is equipped with a cavity partition, ventilation opening is isolated into upper ventilation opening and lower ventilation opening by the cavity partition, upper ventilation opening is connected to equipment ventilation duct, and lower ventilation opening is connected to aircraft engine nacelle.
Description
Technical field
The invention belongs to aircraft power plant ventilating and cooling technical fields, more particularly to a kind of the logical of aircraft engine nacelle
Wind method.
Background technique
Engine and all kinds of accessory devices are installed in aircraft engine nacelle, to prevent heat from gathering, then influence to start
The normal work of machine and equipment need to provide cooling air-flow to enging cabin and equipment.Under normal conditions, equipment inner structure is multiple
Miscellaneous, air-flow will cause biggish flow resistance after flowing through equipment inside, so that it is particularly difficult to divulge information to equipment；On the other hand, gas
During stream flows through enging cabin covering, due to the viscous effect of air-flow, boundary-layer thickeies, the boundary-layer air-flow of low speed low pressure
The intake efficiency of ventilation opening can be further reduced.Therefore, when the ventilation quantity of equipment requirement is larger, inefficient ventilation opening
Often lead to that ventilation opening is oversized, to seriously increase the resistance of aircraft.In addition, to provide ventilation to enging cabin with cooling
Engine wall surface need to also additionally open up ventilation opening in enging cabin skin-surface.The increase of ventilation opening quantity not only breaks up nacelle
Shape, can also interrupt the whole design of nacelle structure, to cause the increase of aircraft weight.Thus, it is desirable to have a kind of technical side
Case overcomes or at least mitigates the drawbacks described above of the prior art.
Summary of the invention
The purpose of the present invention is to provide a kind of aircraft engine nacelle method of ventilation to overcome or at least mitigate the prior art
At least one drawbacks described above.
To achieve the above object, the invention patent provides a kind of method of ventilation of aircraft engine nacelle.
A kind of method of ventilation of aircraft engine nacelle is equipped with equipment ventilation duct, in aircraft engine in aircraft engine nacelle
Cabin is equipped with ventilation opening, which is characterized in that the middle part of the ventilation opening is equipped with a cavity partition, which will lead to
Air port is isolated into ventilation opening and lower ventilation opening, and upper ventilation opening is connected to equipment ventilation duct, lower ventilation opening and aircraft engine nacelle
Connection.
The front end of the cavity partition has oval lip shape.
Thickness of the height of the lower ventilation opening not less than friction layer near wall.
The height of the upper ventilation opening is greater than the height of lower ventilation opening.
The beneficial effects of the present application are as follows: 1) by cavity partition the ventilation opening of enging cabin is isolated into upper and lower two and led to
The boundary-layer air-flow of low speed low pressure near wall is isolated with the high-quality air-flow of the high speed and high pressure on upper layer in air port, and upper layer is excellent
Matter air-flow introduce enging cabin in equipment ventilation duct in, for breathing of engine radiate, guarantee the operating environment of engine, will under
The air-flow of layer introduces enging cabin, is embodied as the ventilation of engine indoor environment；2) this of the application divides draft
Layer-management utilizes, and effectively increases the aeration-cooling effect of the airborne equipment and indoor environment in enging cabin, and reduce hair
The ventilation opening quantity in motivation cabin and the height of ventilation opening, and then optimize the aerodynamic configuration of enging cabin.3) by engine
A ventilation orifice is opened up on cabin, that is, the ventilation to engine and enging cabin can be achieved at the same time；Boundary-layer, which excludes, can also improve
The cooling effect of engine.
The application is described in further detail below in conjunction with attached drawing is implemented.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of aircraft engine nacelle ventilation opening.
Fig. 2 is the method for ventilation schematic illustration of aircraft engine nacelle.
It is numbered in figure: 1 enging cabin, 2 equipment, 3 equipment ventilation ducts, ventilation opening, 5 cavity partitions, 6 lower ventilation openings on 4.
Specific embodiment
Referring to attached drawing, the capital equipment 2 in aircraft engine nacelle 1 is aircraft engine, in order to effectively lead to engine
Wind cooling, is equipped with the aircraft engine nacelle specially proposed to the equipment ventilation duct 3 of breathing of engine, the application in enging cabin
Method of ventilation is that a ventilation opening is opened up on aircraft engine nacelle, and the middle part of the ventilation opening is equipped with a cavity partition
5, which is isolated into upper ventilation opening 4 and lower ventilation opening 6 for ventilation opening, and upper ventilation opening 4 is connected to equipment ventilation duct 3, under
Ventilation opening 6 is connected to the space of aircraft engine nacelle 1.
In implementation, in order to reduce influence of the ventilation opening for externally protruding out in body surface to aircraft drag, upper ventilation as far as possible
Mouth has low-drag cowl and lip.
In order to which air-flow to be effectively directed into upper ventilation opening 4, lower ventilation opening 6, flow losses, the cavity partition 5 are reduced
Front end there is oval lip shape.
In order to absorb the boundary-layer of air-flow completely, so that entering the cooling air-flow pressure of engine apparatus by equipment ventilation duct
Power and flow velocity are uniform, enhance the heat transfer effect of engine, the height of the lower ventilation opening 6 is not less than friction layer near wall
Thickness.
In general, friction layer thickness and air velocity, the wall surface length flowed through and roughness are closely related, for
For the ventilation of aircraft engine nacelle, in implementation preferably, the height of lower ventilation opening is not less than 4mm.If meeting enging cabin
Ventilation requirement, the height of lower ventilation can be increased in right amount.But generally, the height of lower ventilation is no more than 10mm, in order to avoid into
Cooling air in enging cabin is excessive, in turn results in additional aircraft drag loss.The size of upper ventilation is according to equipment ventilation quantity
Depending on demand, it is preferable that the height above divulged information is not less than the height of lower ventilation opening.
Claims (5)
1. a kind of method of ventilation of aircraft engine nacelle is equipped with equipment ventilation duct, in aircraft engine in aircraft engine nacelle
Cabin is equipped with ventilation opening, which is characterized in that the middle part of the ventilation opening is equipped with a cavity partition, which will divulge information
Mouth is isolated into ventilation opening and lower ventilation opening, and upper ventilation opening is connected to equipment ventilation duct, and lower ventilation opening and aircraft engine nacelle connect
It is logical.
2. the method for ventilation of aircraft engine nacelle as described in claim 1, which is characterized in that the front end of the cavity partition
With oval lip shape.
3. the method for ventilation of aircraft engine nacelle as claimed in claim 1 or 2, which is characterized in that the height of the lower ventilation opening
Thickness of the degree not less than friction layer near wall.
4. the method for ventilation of aircraft engine nacelle as claimed in claim 3, which is characterized in that the height of the upper ventilation opening is big
In the height of lower ventilation opening.
5. the method for ventilation of aircraft engine nacelle as claimed in claim 3, which is characterized in that the height of the lower ventilation opening
Between 4mm-10mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811559501.8A CN109649667A (en) | 2018-12-20 | 2018-12-20 | A kind of method of ventilation of aircraft engine nacelle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811559501.8A CN109649667A (en) | 2018-12-20 | 2018-12-20 | A kind of method of ventilation of aircraft engine nacelle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109649667A true CN109649667A (en) | 2019-04-19 |
Family
ID=66114957
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811559501.8A Pending CN109649667A (en) | 2018-12-20 | 2018-12-20 | A kind of method of ventilation of aircraft engine nacelle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109649667A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110500185A (en) * | 2019-07-25 | 2019-11-26 | 中国商用飞机有限责任公司 | A kind of ventilation cooling device for bleed valve |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2136052A1 (en) * | 2008-06-20 | 2009-12-23 | Rolls-Royce Deutschland Ltd & Co KG | Turboprop engine comprising a device for creating a cooling air flow |
| CN102673793A (en) * | 2012-06-08 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Exhaust ejector system of airplane auxiliary power unit |
| CN102923309A (en) * | 2012-11-16 | 2013-02-13 | 中国航空工业集团公司西安飞机设计研究所 | Invisible air intake system |
| CN204368436U (en) * | 2014-12-19 | 2015-06-03 | 成都飞机设计研究所 | Flat opening wind scoop |
| CN105443247A (en) * | 2014-09-19 | 2016-03-30 | 波音公司 | Pre-cooler inlet ducts that utilize active flow-control and systems and methods including the sam |
| CN107298180A (en) * | 2017-06-09 | 2017-10-27 | 南京航空航天大学 | A kind of aircraft and pneumatic adaptation design method for possessing one flowing control |
-
2018
- 2018-12-20 CN CN201811559501.8A patent/CN109649667A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2136052A1 (en) * | 2008-06-20 | 2009-12-23 | Rolls-Royce Deutschland Ltd & Co KG | Turboprop engine comprising a device for creating a cooling air flow |
| CN102673793A (en) * | 2012-06-08 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Exhaust ejector system of airplane auxiliary power unit |
| CN102923309A (en) * | 2012-11-16 | 2013-02-13 | 中国航空工业集团公司西安飞机设计研究所 | Invisible air intake system |
| CN105443247A (en) * | 2014-09-19 | 2016-03-30 | 波音公司 | Pre-cooler inlet ducts that utilize active flow-control and systems and methods including the sam |
| CN204368436U (en) * | 2014-12-19 | 2015-06-03 | 成都飞机设计研究所 | Flat opening wind scoop |
| CN107298180A (en) * | 2017-06-09 | 2017-10-27 | 南京航空航天大学 | A kind of aircraft and pneumatic adaptation design method for possessing one flowing control |
Non-Patent Citations (1)
| Title |
|---|
| 马文昌，王维，马松等: "某型飞机发动机舱通风冷却仿真研究", 《飞机设计》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110500185A (en) * | 2019-07-25 | 2019-11-26 | 中国商用飞机有限责任公司 | A kind of ventilation cooling device for bleed valve |
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| 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 | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190419 |
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| WD01 | Invention patent application deemed withdrawn after publication |