CN203403956U - Starting device of small-sized turbojet engine - Google Patents
Starting device of small-sized turbojet engine Download PDFInfo
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- CN203403956U CN203403956U CN201320476039.1U CN201320476039U CN203403956U CN 203403956 U CN203403956 U CN 203403956U CN 201320476039 U CN201320476039 U CN 201320476039U CN 203403956 U CN203403956 U CN 203403956U
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Abstract
The utility model discloses a starting device of a small-sized turbojet engine. The starting device of the small-sized turbojet engine comprises a power system, a fuel gas system, a control circuit and a high-pressure air system, wherein a high-pressure air pipeline is arranged in a control cabinet, an air input connector and an air output connector are arranged on a panel of the control cabinet, a control valve used for having control over the high-pressure air pipeline is arranged on the panel of the control cabinet, a high-pressure air source is communicated with the air input connector through a high-pressure air pipe, and an air starting connector is communicated with the air output connector formed in the panel of the control cabinet through the high-pressure air pipe. According to the starting device of the small-sized turbojet engine, a compressed gas starting mode is adopted, high-pressure gas is used for blowing rotor blades to rotate, all the components of the starting device are arranged on the ground, only gas pipelines are installed on an unmanned aerial vehicle, the additional weight is not increased, and the defects of motor starting are effectively overcome. Due to the fact that the gas pressure on an outlet of a high-pressure gas cylinder is adjusted through a regulating valve, the requirement of various engines for starting torque can be met.
Description
Technical field
The utility model belongs to unmanned aerial vehicle ground installation technical field, relates to a kind of small sized turbine air breathing engine starting arrangement.
Background technique
In order to obtain good flight performance, SUAV is also brought into use turbojet engine at present, and this class small sized turbine air breathing engine generally, at an actuating motor of the coaxial installation of engine rotor front end, drags the son of walking around during for engine start.But SUAV does not generally have airstart requirement, during airflight, actuating motor is equivalent to invalid load, has additionally increased unmanned plane weight, and the motor that engine rotor front end protrudes also can have a negative impact to the air inlet of motor.
Model utility content
The utility model is a kind of small sized turbine air breathing engine starting arrangement, can realize small sized turbine air breathing engine fast, reliably starting.
The technical solution of the utility model: a kind of small sized turbine air breathing engine starting arrangement, comprise power-supply system, gas burning system and control circuit, also comprise high pressure air system, described high pressure air system comprises high-pressure air source, control box and is arranged on the air actuation interface of turbogenerator (described air actuation interface is to be provided with the interface that can drive turbine rotation on the fuselage of turbogenerator); In described control box, be provided with high pressure airline, on the panel of control box, be provided with air input interface and air output interface, and for controlling the control valve of high pressure airline; Described high-pressure air source is communicated with air input interface by high-pressure air pipe, and described air actuation interface is communicated with the air output interface on control box panel by high-pressure air pipe, is also connected with air manometer on described high pressure airline.High pressure air system provides engine start needed pressurized gas, drags forwarding motor rotor.
Described control valve is pneumatic pilot-valve, on this pneumatic pilot-valve, by auxiliary-air line, is connected with auxiliary source of the gas, and on auxiliary-air line, is provided with solenoid valve.
Described gas burning system is in control box, to be provided with fuel gas pipeline, solenoid valve is set on fuel gas pipeline and is connected with gas pressure gage, the two ends of fuel gas pipeline are respectively combustion gas input interface and the combustion gas output interfaces being positioned on control box panel, described combustion gas input interface is connected with combustion gas gas cylinder, and described combustion gas output interface is connected with engine gas interface.Gas burning system provides engine start needed inflammable gas.
Power-supply system provides 12V power supply for small sized turbine air breathing engine starting arrangement internal circuit.
Control circuit and the collaborative work of engine electronic control system device, control gas valve in suitable time opening and closing.
The beneficial effects of the utility model:
The utility model adopts pressurized gas start mode, utilizes pressurized gas to blow rotor blade and rotates, and all starting arrangements are ground installation, on unmanned plane, except installing gas pipeline, need not increase extra weight, have effectively overcome the defect of electric motor starting.By modulating valve, regulate gas cylinder exit gas pressure, can meet the starting torque demand of different model motor.
Accompanying drawing explanation
Fig. 1 is turbojet engine starting arrangement schematic appearance;
Fig. 2 is control circuit schematic diagram;
Fig. 3 is gas burning system schematic diagram;
Fig. 4 is high pressure air system schematic diagram.
In figure, label 1 is control box panel, and 2 is combustion gas input interface, 3 is combustion gas input interface, 4 is air input interface, and 5 is air output interface, and 6 is air manometer, 7 is gas pressure gage, 8 is line voltmeter, and 9 is charging inlet, and 10 is fuel gas pipeline, 11 is combustion gas gas cylinder, 12 is the air actuation access port of motor, and 13 is gas electromagnetic valve, and 14 is high pressure airline, 15 is high-pressure air source, 16 for engine air plays mobile interface, and 17 is pneumatic pilot-valve, and 18 is auxiliary-air line, 19 is pilot solenoid valve, and 20 is auxiliary source of the gas.
Embodiment
Embodiment: referring to Fig. 1---4.
This small sized turbine air breathing engine starting arrangement is start specialized designs and drop into concrete model and use a kind of ground installation for certain type unmanned aerial vehicle turbojet engine, and Fig. 1 shows its surface structure.
This small sized turbine air breathing engine starting arrangement can be divided into power-supply system, gas burning system, high pressure air system, several major parts of control circuit.Power-supply system and control circuit can be referring to Fig. 2, and power-supply system provides 12V power supply for small sized turbine air breathing engine starting arrangement internal circuit.Control circuit and the collaborative work of engine electronic control system device, control gas valve in suitable time opening and closing.
Gas burning system can be referring to Fig. 3, and gas burning system provides engine start needed inflammable gas.Described gas burning system is in control box, to be provided with fuel gas pipeline 10, gas electromagnetic valve 13 is set on fuel gas pipeline 10 and is connected with gas pressure gage 6, the two ends of fuel gas pipeline 10 are respectively combustion gas input interface 2 and the combustion gas output interfaces 3 being positioned on control box panel, described combustion gas input interface 2 is connected with combustion gas gas cylinder 11, and described combustion gas output interface 3 is connected with engine gas interface 12.
High pressure air system can be referring to Fig. 4, and high pressure air system provides engine start needed pressurized gas, drags forwarding motor rotor.High pressure air system comprises high-pressure air source 15 and is arranged on the air actuation interface 16 of turbogenerator.In control box, be provided with high pressure airline 14, on control box panel 1, be provided with air input interface 3 and air output interface 4, and starting pilot valve 17, on this pneumatic pilot-valve 17, by auxiliary-air line 18, be connected with auxiliary source of the gas 20, and on auxiliary-air line 18, be provided with pilot solenoid valve 19.
Described high-pressure air source 15 is communicated with air input interface 4 by high-pressure air pipe, and described air actuation interface 16 is communicated with the air output interface 5 on control box panel by high-pressure air pipe, is also connected with air manometer 7 on described high pressure airline.
Claims (3)
1. a small sized turbine air breathing engine starting arrangement, comprise power-supply system, gas burning system and control circuit, it is characterized in that, also comprise high pressure air system, described high pressure air system comprises high-pressure air source, control box and is arranged on the air actuation interface of turbogenerator; In described control box, be provided with high pressure airline, on the panel of control box, be provided with air input interface and air output interface, and for controlling the control valve of high pressure airline; Described high-pressure air source is communicated with air input interface by high-pressure air pipe, and described air actuation interface is communicated with the air output interface on control box panel by high-pressure air pipe, is also connected with air manometer on described high pressure airline.
2. small sized turbine air breathing engine starting arrangement according to claim 1, it is characterized in that, described control valve is pneumatic pilot-valve, on this pneumatic pilot-valve, by auxiliary-air line, is connected with auxiliary source of the gas, and on auxiliary-air line, is provided with solenoid valve.
3. small sized turbine air breathing engine starting arrangement according to claim 1, it is characterized in that, described gas burning system is in control box, to be provided with fuel gas pipeline, solenoid valve is set on fuel gas pipeline and is connected with gas pressure gage, the two ends of fuel gas pipeline are respectively combustion gas input interface and the combustion gas output interfaces being positioned on control box panel, described combustion gas input interface is connected with combustion gas gas cylinder, and described combustion gas output interface is connected with engine gas interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320476039.1U CN203403956U (en) | 2013-08-06 | 2013-08-06 | Starting device of small-sized turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320476039.1U CN203403956U (en) | 2013-08-06 | 2013-08-06 | Starting device of small-sized turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203403956U true CN203403956U (en) | 2014-01-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320476039.1U Expired - Lifetime CN203403956U (en) | 2013-08-06 | 2013-08-06 | Starting device of small-sized turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203403956U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110805495A (en) * | 2019-12-05 | 2020-02-18 | 江西洪都航空工业集团有限责任公司 | Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft |
-
2013
- 2013-08-06 CN CN201320476039.1U patent/CN203403956U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110805495A (en) * | 2019-12-05 | 2020-02-18 | 江西洪都航空工业集团有限责任公司 | Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft |
| CN110805495B (en) * | 2019-12-05 | 2021-10-01 | 江西洪都航空工业集团有限责任公司 | Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft |
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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 |
Granted publication date: 20140122 |
|
| CX01 | Expiry of patent term |