CN203345201U - Aircraft ejection system - Google Patents
Aircraft ejection system Download PDFInfo
- Publication number
- CN203345201U CN203345201U CN 201320213813 CN201320213813U CN203345201U CN 203345201 U CN203345201 U CN 203345201U CN 201320213813 CN201320213813 CN 201320213813 CN 201320213813 U CN201320213813 U CN 201320213813U CN 203345201 U CN203345201 U CN 203345201U
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- CN
- China
- Prior art keywords
- fan
- air
- mixing chamber
- aircraft
- air inlet
- 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.)
- Expired - Fee Related
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Abstract
The utility model belongs to an aircraft design technology, and relates to an aircraft ejection system. The aircraft ejection system comprises a fan, a mixing chamber and an ejection nozzle. The fan is arranged in an air inlet of the mixing chamber, an air flow outlet of the fan is connected with the air inlet of the mixing chamber, and the ejection nozzle penetrates through the side wall of the mixing chamber, enters the mixing chamber and is arranged on the rear portion of the fan. The fan is arranged at the air inlet of the mixing chamber, so that air amount led to surrounding environment is increased. After the air fan is operated, air inlet amount of the surrounding environment is greatly increased, and the ejection nozzle on the rear portion of the air fan extends from the side wall into the mixing chamber. After the fan is operated, the air inlet amount of the surrounding environment is increased, and the requirement for the air amount led to the surrounding environment is met. The number of ejectors is reduced, generally, two ejectors are symmetrically arranged on the two sides of an aircraft according to the requirement of air distribution, and little installation space of the aircraft is occupied.
Description
Technical field
The utility model belongs to the Flight Vehicle Design technology, relates to a kind of aircraft ejection system.
Background technology
Carry-on passenger cabin is heated, windscreen demist etc. often can be used ejection system; the High Temperature High Pressure air of drawing from the air compressor of driving engine; inject blending box by injector, and ambient air introduced to blending box together, after mixing for passenger cabin heat, the windscreen demist.Because injector is to introduce in proportion surrounding environment gas, and in the situation that use single injector, the High Temperature High Pressure air themperature that the ambient air amount of introducing can't be drawn the air compressor from driving engine neutralizes operable temperature.The ejection system of aircraft tends to shunt with High Temperature High Pressure air that a plurality of injectors will draw from the air compressor of driving engine is set the ambient air amount that injection respectively increases introducing, and this usually causes the too fat to move of aircraft ejection system.
Summary of the invention
The purpose of this utility model is to propose a kind of quantity that increases injector that do not need just can meet the aircraft needs, and does not take again the aircraft ejection system in too much space.
Technical solution of the present utility model is, ejection system comprises fan machine, blending box, driving nozzle, a fan machine is set in the admission port of blending box, the air stream outlet of fan machine (3) connects the admission port of blending box (2), driving nozzle penetrates blending box inside from the sidewall of blending box, and is placed in the rear portion of fan machine.The advantage the utlity model has and beneficial effect, the utility model, at the entrance provided with fan machine of blending box, has improved the ambient air amount of introducing.Can greatly promote the ambient air inlet after the operation of air fan machine, the injector nozzle after the air fan machine stretches in blending box from sidewall.Can increase the introduction volume of ambient air after the fan machine running, the needs of introducing the ambient air amount have been met, the quantity of injector is reduced, and that generally according to air, distributes need to be arranged symmetrically in the aircraft both sides by two injectors, takies the seldom installing space of aircraft.
The accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
The specific embodiment
Below in conjunction with accompanying drawing, the utility model is elaborated.Ejection system comprises fan machine 3, blending box 2, driving nozzle 1, a fan machine 3 is set in the admission port of blending box 2, the air stream outlet of fan machine 3 connects the admission port of blending box 2, and driving nozzle 1 penetrates blending box 2 inside from the sidewall of blending box 2, and is placed in the rear portion of fan machine 3.Ejection system designs the entrance that ambient air 4 around enters system and sets up air fan machine 3, can greatly promote the inlet of ambient air 4 after 3 operations of air fan machine, injector nozzle 1 after air fan machine 3 stretches in blending box 2 from sidewall, mixes with the ambient air 4 by introducing blending box after 3 operations of air fan machine after the High Temperature High Pressure air stream 5 of injector nozzle 1 ejection sprays into blending box, promoted the rear air draught 6 of mixing.
Claims (1)
1. an aircraft ejection system, it is characterized in that, ejection system comprises fan machine (3), blending box (2), driving nozzle (1), a fan machine (3) is set in the admission port of blending box (2), the air stream outlet of fan machine (3) connects the admission port of blending box (2), driving nozzle (1) penetrates blending box (2) inside from the sidewall of blending box (2), and is placed in the rear portion of fan machine (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320213813 CN203345201U (en) | 2013-04-24 | 2013-04-24 | Aircraft ejection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320213813 CN203345201U (en) | 2013-04-24 | 2013-04-24 | Aircraft ejection system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203345201U true CN203345201U (en) | 2013-12-18 |
Family
ID=49745127
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320213813 Expired - Fee Related CN203345201U (en) | 2013-04-24 | 2013-04-24 | Aircraft ejection system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203345201U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542098A (en) * | 2015-09-18 | 2017-03-29 | 哈尔滨飞机工业集团有限责任公司 | A kind of aircraft air condition freezes and forces warm structure |
| CN106892120A (en) * | 2015-12-21 | 2017-06-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of fan exhaust induces the ram-air ring cold integral system of control liquid |
| CN110803288A (en) * | 2019-10-25 | 2020-02-18 | 中航通飞研究院有限公司 | Heating, injecting and mixing device for cabin |
-
2013
- 2013-04-24 CN CN 201320213813 patent/CN203345201U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542098A (en) * | 2015-09-18 | 2017-03-29 | 哈尔滨飞机工业集团有限责任公司 | A kind of aircraft air condition freezes and forces warm structure |
| CN106542098B (en) * | 2015-09-18 | 2019-03-01 | 哈尔滨飞机工业集团有限责任公司 | A kind of aircraft air condition refrigeration and force warm structure |
| CN106892120A (en) * | 2015-12-21 | 2017-06-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of fan exhaust induces the ram-air ring cold integral system of control liquid |
| CN110803288A (en) * | 2019-10-25 | 2020-02-18 | 中航通飞研究院有限公司 | Heating, injecting and mixing device for cabin |
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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 |
Granted publication date: 20131218 Termination date: 20160424 |