CN202628333U - Air plane air charge system capable of realizing automatic regulation of flow rate of charged air - Google Patents
Air plane air charge system capable of realizing automatic regulation of flow rate of charged air Download PDFInfo
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- CN202628333U CN202628333U CN 201220270763 CN201220270763U CN202628333U CN 202628333 U CN202628333 U CN 202628333U CN 201220270763 CN201220270763 CN 201220270763 CN 201220270763 U CN201220270763 U CN 201220270763U CN 202628333 U CN202628333 U CN 202628333U
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- air
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- door
- air door
- flow rate
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Abstract
The utility model belongs to the technical field of general aviation, and relates to an air plane air charge system capable of realizing automatic regulation of the flow rate of charged air. The air plane air charge system comprises an air charge filter mesh, an air charge channel, an auxiliary air inlet, an air charge pipeline, an engine air inlet and an air door, wherein the air charge filter mesh is arranged at an air charge channel inlet; the auxiliary air inlet is arranged on the side wall of the air charge channel, the inner side of the auxiliary air inlet is provided with the air door, the shape of the air door is completely as same as the shape of the auxiliary air inlet, and the air door can completely cover the auxiliary air inlet. One end of the air charge pipeline is communicated with the air charge channel, and the other end of the air charge pipeline is provided with the engine air inlet; and the air door is connected with a fixed support through a rotary shaft. The air plane air charge system disclosed by the utility model does not need manual interference, is reliable in operation, simple in machining process and good in regulation performance of air flow, can automatically meet the requirement of air charge flow rate of an engine under various conditions, and are worthy of being practically applied largely.
Description
Technical field
The utility model belongs to the General Aviation technical field, relates to a kind ofly realizing the self-regulating aircraft gas handling system of charge flow rate.
Background technique
When general class baby plane gas handling system meets with that air inlet screen stops up or aircraft when being strayed into icing area, intake duct can take place to be blocked, make air input of engine by air reduce, thereby can directly influence the flight safety of aircraft, so gas handling system must be considered anti-icing design emphatically.To this problem; The solution that current domestic and international general class baby plane uses is mainly: in the intake duct bottom auxiliary intake valve is set; And lay special push-and-pull cable wire, it is opened and closes by pilot's hand control, when case of emergency takes place; The push-and-pull cable wire that operates by manual manipulation opens or closes auxiliary intake valve, and ventilation cooling blast in the cabin is sucked to replenish the deficiency of air input of engine by air.The method has the design cost height, cable wire is laid a series of problems such as difficulty and increase pilot emergency operation.
Summary of the invention
The purpose of the utility model is: a kind of simple in structure, reliable operation, easy to maintenance, no manual intervention are provided, can realize the self-regulating aircraft gas handling system of charge flow rate.
The technological scheme of the utility model is: a kind ofly can realize the self-regulating aircraft gas handling system of charge flow rate, it comprises air inlet screen 1, intake duct 2, auxilairy air intake 4, air inlet pipeline 5, engine intake 6 and air door 7.Wherein, air inlet screen 1 is arranged on intake duct 2 imports; Auxilairy air intake 4 is opened on the intake duct sidewall 3, and to be provided with shape consistent with it in auxilairy air intake 4 inboards, and can cover the air door 7 of auxilairy air intake 4 fully; Air inlet pipeline 5 one ends communicate with intake duct 2, and the other end is an engine intake 6; Air door 7 links to each other with fixed support 9 through rotating shaft 8, and through rotating shaft 8 air door 7 is opened to intake duct 2 inside; Rotating shaft 8 places the front side, suitable course of air door 7, vertically place, and fixed support 9 is fixed on the intake duct sidewall 3 through rivet 10, and rotating shaft 8 middle parts is socketed with the spring 11 of inside and outside air-flow differential when being used for damper 7 and opening.
Rotating shaft 8 places the front side, suitable course of air door 7, vertically places.
The advantageous effect that the utlity model has: the utility model utilizes the pressure reduction of the inside and outside air-flow of intake duct on air door both sides; Automatically the open angle of damper is realized ventilation cooling blast in the cabin is sucked intake duct inside to replenish the deficiency of air input of engine by air through auxilairy air intake and air door.Whole process need not manual intervention, reliable operation, and processing technology is simple, and under various situation, can both satisfy the charge flow rate requirement of motor automatically, need not the auxiliary intake valve single pavement is handled cable wire, has reduced design cost and pilot operator burden.In addition,, can significantly offset gravity, thereby improve the adjusting function of air-flow, therefore have bigger actual application value because air door is arranged on the intake duct inside sidewalls, and vertically places.
Description of drawings
Fig. 1 is the structural representation that the utility model can be realized the self-regulating aircraft gas handling system of charge flow rate.
Fig. 2 is the structural representation of air door.
Wherein: air inlet screen 1; Intake duct 2; Intake duct sidewall 3; Auxilairy air intake 4; Air inlet pipeline 5; Engine intake 6; Air door 7; Rotating shaft 8; Fixed support 9; Rivet 10; Spring 11.
Embodiment
Below in conjunction with concrete accompanying drawing the utility model is described further.
See also Fig. 1, it is the structural representation that the utility model can be realized the self-regulating aircraft gas handling system of charge flow rate.The utility model aircraft gas handling system comprises air inlet screen 1, intake duct 2, auxilairy air intake 4, air inlet pipeline 5, engine intake 6 and air door 7.Wherein, air inlet screen 1 is arranged on intake duct 2 imports, is used to filter impurity such as dust; Auxilairy air intake 4 is opened on the intake duct sidewall 3; And it is consistent with it that auxilairy air intake 4 inboards are provided with shape; And area is slightly larger than the air door 7 (be air door 7 than auxilairy air intake 4 big circles, the imbricate amount is 5mm at least, to realize sealing fully) of auxilairy air intake 4; Air inlet pipeline 5 one ends communicate with intake duct 2, and the other end is an engine intake 6.
See also Fig. 2, it is the structural representation of air door.Said air door 7 links to each other with fixed support 9 through rotating shaft 8, and through rotating shaft 8 air door 7 is opened to intake duct 2 inside; And this rotating shaft 8 places the front side, suitable course of air door 7, vertically places, thereby offsets air door 7 self gravitations, makes the influence of air door 7 self gravitations be decreased to minimum; Spring 11 is enclosed within rotating shaft 8 middle parts, the inside and outside air-flow differential when utilizing spring 11 pretightening forces to come damper 7 to open; Said fixed support 9 is fixed on the intake duct sidewall 3 through rivet 10.
The utility model aircraft gas handling system realizes that the self-regulating principle of charge flow rate is following: the open angle that utilizes the automatic damper 7 of magnitude of pressure differential of air-flows and intake duct 2 outer air-flows (ventilation cooling blast) in the intake duct 2 on air door 7 both sides; Ventilation cooling blast in the cabin is sucked intake duct 2 inside to replenish the deficiency of air input of engine by air through auxilairy air intake 4 and air door 7.
Practical work process is following:
When air input of engine by air 6 was enough, stream pressures were greater than intake duct 2 outer air-flows (ventilation cooling blast) pressure in the intake duct 2, and air door 7 is close to intake duct internal face 3 under the effect of inside and outside differential pressure, and air door 7 is closed; When meeting with that air inlet screen 1 stops up or aircraft when being strayed into icing area, the reducing of air input of engine by air 6 can cause that stream pressures reduce in the intake duct 2; When air input of engine by air 6 deficiencies; When stream pressure is less than intake duct 2 outer air-flows (ventilation cooling blast) pressure in the intake duct 2; Air door 7 can be opened under the effect of inside and outside differential pressure automatically, and ventilation cooling blast in the cabin is sucked intake duct 2 inside to replenish the deficiency of air input of engine by air 6 through auxilairy air intake 4 and air door 7.And the aperture of air door 7 size is directly by the magnitude of pressure differential decision of air door 7 both sides air-flows, stopped up by air inlet screen 1 indirectly or the order of severity that aircraft is strayed into icing area decides; When air inlet screen 1 stop up or aircraft to be strayed into icing area serious more, when promptly air input of engine by air 6 was more not enough, the pressure reduction of air door 7 both sides air-flows was big more, air door 7 apertures are just big more, air inflow is also big more, vice versa, thereby realization is to the automatic adjusting of charge flow rate.
Claims (3)
1. can realize the self-regulating aircraft gas handling system of charge flow rate for one kind; It is characterized in that; Comprise air inlet screen (1), intake duct (2), auxilairy air intake (4), air inlet pipeline (5), engine intake (6) and air door (7), wherein, air inlet screen (1) is arranged on intake duct (2) import; Auxilairy air intake (4) is opened on the intake duct sidewall (3), and to be provided with shape consistent with it in auxilairy air intake (4) inboard, and can cover the air door (7) of auxilairy air intake (4) fully; Air inlet pipeline (5) one ends communicate with intake duct (2), and the other end is engine intake (6); Air door (7) links to each other with fixed support (9) through rotating shaft (8), and through rotating shaft (8) air door (7) is opened to intake duct (2) inside; Rotating shaft (8) places the front side, suitable course of air door (7), vertically place, and fixed support (9) is fixed on the intake duct sidewall (3) through rivet (10), and rotating shaft (8) middle part is socketed with the spring (11) that is used for damper (7) inside and outside air-flow differential when opening.
2. according to claim 1ly can realize the self-regulating aircraft gas handling system of charge flow rate, it is characterized in that: rotating shaft (8) places the front side, suitable course of air door (7), vertically places.
3. according to claim 2ly can realize the self-regulating aircraft gas handling system of charge flow rate, it is characterized in that: air door (7) is than auxilairy air intake (4) Da Yiquan, and the imbricate amount is 5mm at least, to realize sealing fully.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220270763 CN202628333U (en) | 2012-06-08 | 2012-06-08 | Air plane air charge system capable of realizing automatic regulation of flow rate of charged air |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220270763 CN202628333U (en) | 2012-06-08 | 2012-06-08 | Air plane air charge system capable of realizing automatic regulation of flow rate of charged air |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202628333U true CN202628333U (en) | 2012-12-26 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220270763 Expired - Lifetime CN202628333U (en) | 2012-06-08 | 2012-06-08 | Air plane air charge system capable of realizing automatic regulation of flow rate of charged air |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202628333U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106288853A (en) * | 2016-08-29 | 2017-01-04 | 李其兰 | Low-temperature negative-pressure cross flow cooling tower |
| CN107744699A (en) * | 2017-11-30 | 2018-03-02 | 中车（天津）轨道交通设备有限公司 | Automatic blasting air filtration system for means of transport air inlet |
| CN110576978A (en) * | 2019-09-23 | 2019-12-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Air inlet channel auxiliary air inlet device and airplane with same |
-
2012
- 2012-06-08 CN CN 201220270763 patent/CN202628333U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106288853A (en) * | 2016-08-29 | 2017-01-04 | 李其兰 | Low-temperature negative-pressure cross flow cooling tower |
| CN107744699A (en) * | 2017-11-30 | 2018-03-02 | 中车（天津）轨道交通设备有限公司 | Automatic blasting air filtration system for means of transport air inlet |
| CN107744699B (en) * | 2017-11-30 | 2023-06-27 | 中车（天津）轨道交通设备有限公司 | Automatic blowing and air filtering system for air inlet of transport means |
| CN110576978A (en) * | 2019-09-23 | 2019-12-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Air inlet channel auxiliary air inlet device and airplane with same |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121226 |