CN204250376U - A kind of Submerged Inlet structure of aircraft - Google Patents
A kind of Submerged Inlet structure of aircraft Download PDFInfo
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- CN204250376U CN204250376U CN201420707442.5U CN201420707442U CN204250376U CN 204250376 U CN204250376 U CN 204250376U CN 201420707442 U CN201420707442 U CN 201420707442U CN 204250376 U CN204250376 U CN 204250376U
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- fumarole
- inlet channel
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Abstract
The utility model relates to aircraft inlet channel field, relates to a kind of Submerged Inlet structure of aircraft.Comprise Submerged Inlet and aircraft, Submerged Inlet divides admission port, air extractor duct and inlet channel, admission port is arranged on the surface of aircraft, air extractor duct is communicated with the admission port of the driving engine of aircraft, in inlet channel, have some fumaroles, after the fan or air compressor of driving engine, draw a bleed conduit be communicated with each fumarole.Fumarole is arranged near the upstream i.e. front lip guide face of the potential stall spot of boundary layer airflow in inlet channel.Fumarole axis and front lip guide face are angle of inclination.The beneficial effects of the utility model are: structure is simple, are convenient to implement, significantly improve the total pressure recovery coefficient of Submerged Inlet, effectively reduce distortion index.
Description
Technical field
The utility model relates to aircraft inlet channel field, relates to a kind of Submerged Inlet structure of aircraft specifically.
Background technology
Submerged Inlet is combined together at import and aircraft, without any the special inlet channel of jut.Submerged Inlet not only effectively can reduce frontal resistance and the radar scattering area of aircraft because wind area is little, and the fusion of itself and body makes the size of body reduce, and is conducive to installing, transport and multi-platform transmitting.Therefore, Submerged Inlet is being subject to paying close attention to more and more widely and applying.But the import of Submerged Inlet is placed in the low energy stream of body boundary-layer completely, can not utilize incoming flow punching press as S shape inlet channel, before only relying on, the pressure gradient at lip place and incline place entrainments whirlpool air inlet.When entrainmenting vortices breakdown and being too little, the air inlet weak effect of Submerged Inlet; And the distortion of air intake port can be very large when entrainmenting whirlpool and crossing strong.
Summary of the invention
The purpose of this utility model is to solve the problem, and provides a kind of Submerged Inlet structure of aircraft.
In order to realize the purpose of this utility model, the technical solution adopted in the utility model is:
A kind of Submerged Inlet structure of aircraft, comprise Submerged Inlet and aircraft, Submerged Inlet divides admission port, air extractor duct and inlet channel, admission port is arranged on the surface of aircraft, air extractor duct is communicated with the admission port of the driving engine of aircraft, in inlet channel, have some fumaroles, after the fan or air compressor of driving engine, draw a bleed conduit be communicated with each fumarole.
Fumarole is arranged near the upstream i.e. front lip guide face of the potential stall spot of boundary layer airflow in inlet channel.
Fumarole axis and front lip guide face are angle of inclination.
The beneficial effects of the utility model are: structure is simple, are convenient to implement, significantly improve the total pressure recovery coefficient of Submerged Inlet, effectively reduce distortion index.
Accompanying drawing explanation
Fig. 1 is the utility model structural representation,
Fig. 2 is Submerged Inlet structural representation of the present utility model.
Detailed description of the invention
Below in conjunction with drawings and Examples, the utility model is further illustrated:
Embodiment: see Fig. 1, Fig. 2.
A kind of Submerged Inlet structure of aircraft, comprise Submerged Inlet 2 and aircraft 1, Submerged Inlet divides admission port 201, air extractor duct 202 and inlet channel 203, admission port 201 is arranged on the surface of aircraft 1, air extractor duct 201 is communicated with the admission port of the driving engine 3 of aircraft 1, in inlet channel 203, have some fumaroles 204, after the fan or air compressor of driving engine 3, draw a bleed conduit 4 be communicated with each fumarole 204.
Fumarole 204 is arranged near the upstream i.e. front lip guide face of the potential stall spot of boundary layer airflow in inlet channel 203.
Fumarole 204 axis and front lip guide face are angle of inclination.
The utility model principle: the high pressure draft come from the fan of driving engine 3 or air compressor is imported Submerged Inlet 2 by bleed conduit 4.Due to the pressure reduction in bleed conduit 4 between air-flow and inlet boundary layer air-flow, air-flow will with specific angle from ejection in inlet channel fumarole 204, the whirlpool produced will strengthen the blending of boundary layer airflow and main flow, thus suppresses the separation of boundary 1ayer, reduces flow losses.The whirlpool formed serves the effect being equivalent to vane type vortex generator, significantly can improve the performance of Submerged Inlet 2.So, be realize improving outlet total pressure recovery coefficient based on the Submerged Inlet of jet-propelled vortex generator and reducing the powerful measure of distortion index by bleed conduit 4 from bleed after driving engine 3 fan or air compressor.
One of preferred embodiment that what embodiment of the present utility model was announced is also; but be not limited thereto; those of ordinary skill in the art; very easily according to above-described embodiment; understand spirit of the present utility model; and make different amplifications and change, but only otherwise depart from spirit of the present utility model, all in protection domain of the present utility model.
Claims (3)
1. the Submerged Inlet structure of an aircraft, comprise Submerged Inlet and aircraft, Submerged Inlet divides admission port, air extractor duct and inlet channel, admission port is arranged on the surface of aircraft, air extractor duct is communicated with the admission port of the driving engine of aircraft, it is characterized in that: in inlet channel, have some fumaroles, after the fan or air compressor of driving engine, draw a bleed conduit be communicated with each fumarole.
2. the Submerged Inlet structure of a kind of aircraft according to claim 1, is characterized in that: fumarole is arranged near the upstream i.e. front lip guide face of the potential stall spot of boundary layer airflow in inlet channel.
3. the Submerged Inlet structure of a kind of aircraft according to claim 2, is characterized in that: fumarole axis and front lip guide face are angle of inclination.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420707442.5U CN204250376U (en) | 2014-11-24 | 2014-11-24 | A kind of Submerged Inlet structure of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420707442.5U CN204250376U (en) | 2014-11-24 | 2014-11-24 | A kind of Submerged Inlet structure of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204250376U true CN204250376U (en) | 2015-04-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420707442.5U Active CN204250376U (en) | 2014-11-24 | 2014-11-24 | A kind of Submerged Inlet structure of aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN204250376U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443402A (en) * | 2014-11-24 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Embedded type air inlet passage structure of aircraft |
| CN107719645A (en) * | 2016-08-11 | 2018-02-23 | 通用电气公司 | Intake assembly for aircraft aft-fan |
-
2014
- 2014-11-24 CN CN201420707442.5U patent/CN204250376U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443402A (en) * | 2014-11-24 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Embedded type air inlet passage structure of aircraft |
| CN107719645A (en) * | 2016-08-11 | 2018-02-23 | 通用电气公司 | Intake assembly for aircraft aft-fan |
| CN107719645B (en) * | 2016-08-11 | 2023-04-07 | 通用电气公司 | Inlet assembly for an aircraft rear fan |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |