CN203558213U - Disassembling device for boundary layer of airplane air intake duct - Google Patents
Disassembling device for boundary layer of airplane air intake duct Download PDFInfo
- Publication number
- CN203558213U CN203558213U CN201320718948.1U CN201320718948U CN203558213U CN 203558213 U CN203558213 U CN 203558213U CN 201320718948 U CN201320718948 U CN 201320718948U CN 203558213 U CN203558213 U CN 203558213U
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- CN
- China
- Prior art keywords
- air intake
- intake duct
- disassembling
- diverter
- inlet channel
- 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.)
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Abstract
The utility model relates to a disassembling device for a boundary layer of an airplane air intake duct. The disassembling device is mainly characterized in that a diverter is arranged between an opening of the air intake duct and an airplane body, a beta pointed wedge angle is adopted at the front end of the diverter, the upper portion and the lower portion of the diverter are in smooth connection through an inner arc and an outer arc to guide low-energy airflow of the boundary layer of the airplane body to be exhausted out of the upper surface and the lower surface of the diverter, a disassembling hole and a disassembling gap are machined in a sloping panel, the sloping panel is installed in the opening of the air intake duct, the segment of the disassembling hole is arranged at the front end of the opening of the air intake duct, the segment of the disassembling gap is arranged at the starting position of the throat of the air intake duct, a cavity is formed among the airplane body, the diverter, the sloping panel and the wall of the air intake duct, the upper tail end and the lower tail end of the diverter are provided with leakage flow openings, and the low-energy airflow of the boundary layer enters the cavity from the disassembling hole and the disassembling gap and then is exhausted through the leakage flow openings. According to the disassembling device for the boundary layer of the airplane air intake duct, the flow field quality of the air intake duct is improved, the distortion flow field is reduced, the total pressure recovery coefficient of the air intake duct is improved, and the usable thrust of an engine is increased.
Description
Technical field
The utility model relates to airplane intake aerodynamic characteristic technical field, and specifically a kind of airplane intake boundary-layer that improves airplane intake flow field quality and inlet total pres sure recovery coefficient is let out removal apparatus.
Background technology
Use the aircraft of turbojet engine, the function of design inlet channel is that charge air is introduced to driving engine, meets the driving engine traffic requirement of the need under various height and speed and the requirement of driving engine to inlet channel flow field quality; Also require the Air Flow loss of inlet channel itself as much as possible little, namely the total pressure recovery of inlet channel is high as much as possible, to improve driving engine thrust available simultaneously.Guarantee the flight performance requirement of inlet channel and the work of driving engine matched well and aircraft.Its structure is to be generally connected with in the front of driving engine the inlet channel communicating with atmosphere.Operational aircraft inlet channel is owing to being subject to the restriction of aircraft general layout under normal circumstances, the weak point existing is inlet channel pipe shape complexity, add that aircraft flight attitude complexity, flying speed, flying height region are larger, make Fighter Inlet paste the air current flow complicated condition at fuselage place.When the flight of low, the large angle of attack of subsonic, high angles of side slip, there is the boundary-layer separation phenomenon that flows, while flying when across, hyprsonic, there is the mutual interference phenomenon of boundary-layer and shock wave, cause inlet channel flow field quality variation, total pressure recovery coefficient reduces, and engine thrust loss is larger; Difficulty is given and is guaranteed that aircraft, under various flight Mach numbers, various flying height condition, has good flow field quality.
Summary of the invention
The deficiency existing for overcoming prior art, the utility model provides a kind of airplane intake boundary-layer to let out removal apparatus.By set up swash plate in the inner side at air inlet road junction, make low-yield air-flow through letting out except hole and letting out except seam and let out and remove, can obviously improve inlet channel flow field quality, improve the airworthiness of inlet total pres sure recovery coefficient, driving engine thrust available and operational aircraft.
The technical solution of the utility model is achieved in that between air inlet road junction and fuselage and is provided with every road, every road front end, adopt β glut angle, by inside and outside circular arc, be smoothly connected upper and lower surface, the guiding low-yield air-flow Cong Ge of fuselage boundary-layer road respectively and discharge every road is upper and lower.On swash plate, be processed with and let out except hole and let out except seam, swash plate is contained in air inlet road junction, lets out the front end that is placed in air inlet road junction except hole section, lets out the venturi section start that is placed in inlet channel except seam section.Fuselage, between road, swash plate and inlet channel wall, form a plenum chamber, every road, upper and lower tail end offers relief port, and the low-yield air-flow of boundary-layer enters cavity by letting out except mouthful discharging except seam from letting out except hole and letting out.
The advantage the utlity model has is: the control principle that utilizes viscosity fluid mechanics ABC and boundary-layer, adopting fuselage boundary-layer on road and Fighter Inlet swash plate, to open boundary-layer lets out and lets out except seam method except hole and venturi boundary-layer, improved Fighter Inlet flow field condition, improve inlet channel flow field quality, reduce Distorted Flow Field, improve inlet total pres sure recovery coefficient, increase the object of driving engine thrust available.Solve boundary-layer in airplane intake design and let out the key of removing.
Accompanying drawing explanation
Accompanying drawing drawing of the present utility model is described as follows:
Fig. 1 is that the utility model airplane intake boundary-layer is let out removal apparatus integral structure view;
Fig. 2 is that the A of Fig. 1 is to view;
Fig. 3 is the sound view of Fig. 2 along B-B.
1. fuselages in figure, 2.Ge road, 3. inlet channel, 4. swash plate, 5. goes up relief port, 6. lets out except seam, 7. descends relief port, 8. lets out except hole, 9. plenum chamber.
The specific embodiment
Below in conjunction with accompanying drawing and embodiment, the utility model is described in further detail.
Fig. 1, Fig. 2 and Fig. 3 show the utility model integral structure.
Between 3 mouthfuls of inlet channels and fuselage 1, be provided with every road 2, every road, 2 front ends adopt glut angle β, and angle of wedge β is 30 °.Every road 2, the upper and lower circular arc that is 1000mm by inside and outside radius R is respectively smoothly connected, and discharge on upper and lower surface, the arc surface guiding fuselage low-yield air-flow Cong Ge of 1 boundary-layer road 2.On swash plate 4, be processed with let out except hole 8 and let out except seam 6, let out except 8 apertures, hole be φ 2.5mm～φ 3.5mm, hole area accounts for every side inlet channel 3 import throat areas 5%～6%; Let out the wide 20mm～30mm of being of seam except seam 6.Swash plate 4 is contained in 3 mouthfuls of inlet channels, lets out the front end that is placed in 3 mouthfuls of inlet channels except hole 8, lets out the venturi section start that is placed in inlet channel 3 except seam 6.Fuselage 1, between road 2, swash plate 4 and inlet channel 3 walls, form a plenum chamber 9, every the upper and lower tail end in road 2, offer upper relief port 5 and lower relief port 7, the low-yield air-flow of boundary-layer is from letting out except hole 8 and letting out to remove seam 6 enters plenum chamber 9 and discharged by upper relief port 5 and lower relief port 7.
Claims (3)
1. an airplane intake boundary-layer is let out removal apparatus, mainly by fuselage, form every road, swash plate and inlet channel etc., it is characterized in that: between inlet channel (3) mouth and fuselage (1), be provided with every road (2), on swash plate (4), be processed with and let out except hole (8) and let out except seam (6), swash plate (4) is contained in inlet channel (3) mouthful, let out the front end that is placed in inlet channel (3) mouth except hole (8) section, let out the venturi section start that is placed in inlet channel (3) except seam (6) section; Fuselage (1), between road (2), swash plate (4) and inlet channel (3) wall, form a plenum chamber (9); Every the upper and lower tail end of road (2), offer upper relief port (5) and lower relief port (7).
2. airplane intake boundary-layer according to claim 1 is let out removal apparatus, it is characterized in that: let out except aperture, hole (8) be φ 2.5mm～φ 3.5mm, hole area accounts for every side inlet channel (3) import throat area 5%～6%.
3. airplane intake boundary-layer according to claim 1 is let out removal apparatus, it is characterized in that: let out the wide 20mm～30mm of being of seam except seam (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320718948.1U CN203558213U (en) | 2013-11-10 | 2013-11-10 | Disassembling device for boundary layer of airplane air intake duct |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320718948.1U CN203558213U (en) | 2013-11-10 | 2013-11-10 | Disassembling device for boundary layer of airplane air intake duct |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203558213U true CN203558213U (en) | 2014-04-23 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320718948.1U Expired - Fee Related CN203558213U (en) | 2013-11-10 | 2013-11-10 | Disassembling device for boundary layer of airplane air intake duct |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203558213U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109367797A (en) * | 2018-10-17 | 2019-02-22 | 江西洪都航空工业集团有限责任公司 | A kind of drawing-in type airplane air intake duct exported after engine power |
| CN113022858A (en) * | 2021-03-04 | 2021-06-25 | 中国电子科技集团公司第二十九研究所 | Nacelle air inlet and exhaust device |
-
2013
- 2013-11-10 CN CN201320718948.1U patent/CN203558213U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109367797A (en) * | 2018-10-17 | 2019-02-22 | 江西洪都航空工业集团有限责任公司 | A kind of drawing-in type airplane air intake duct exported after engine power |
| CN109367797B (en) * | 2018-10-17 | 2022-03-15 | 江西洪都航空工业集团有限责任公司 | Pull-in type layout aircraft air inlet channel with engine power output later |
| CN113022858A (en) * | 2021-03-04 | 2021-06-25 | 中国电子科技集团公司第二十九研究所 | Nacelle air inlet and exhaust device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140423 Termination date: 20181110 |