CN202853900U - Starting oil supply control system for engine ground test - Google Patents
Starting oil supply control system for engine ground test Download PDFInfo
- Publication number
- CN202853900U CN202853900U CN 201220547120 CN201220547120U CN202853900U CN 202853900 U CN202853900 U CN 202853900U CN 201220547120 CN201220547120 CN 201220547120 CN 201220547120 U CN201220547120 U CN 201220547120U CN 202853900 U CN202853900 U CN 202853900U
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- oil
- ground test
- engine
- solenoid valve
- valve
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Abstract
The utility model relates to a starting oil supply control system for an engine ground test, comprising an oil supply apparatus and a control apparatus, wherein the oil supply apparatus comprises a coarse oil filter, an electric oil pump, a fine oil filter, a reducing valve, a non-return valve and a solenoid valve which are orderly connected, the control apparatus comprises a controller, an operation system, a display system, a data collection system and a pressure sensor, one end of the pressure sensor is connected an oil output end of the oil supply apparatus, the other end of the pressure sensor is connected with the data collection system, and the controller is also connected with the solenoid valve and the electric oil pump respectively. The starting oil supply control system for an engine ground test can supply oil according to the starting time sequence of an engine, and can ensure the ignition opportunity of the engine; and the engine does not need fireworks for ignition, and can be continuously started for many times, thereby greatly reducing ignition cost.
Description
Technical field
The utility model relates to a kind of control system, and especially a kind of rocket engine ground test starting is for EFM Electronic Fuel Management.
Background technology
Aeromotor all needs to carry out the several times ground experiment before coming into operation at present, therefore need to carry out ignition start many times.But for some engine, for being adopted as disposable priming system cartridge ignition, if all adopt this mode at every turn, cost is high, resource is lost weary, complicated operation, does not utilize carrying out smoothly of product development such as certain bullet engine.If adopt fuel ignition blast mode to start, but engine itself only has main and auxiliary fuel feeding, does not start fuel feeding, can not satisfy the requirement of fuel ignition blast mode.
Summary of the invention
The utility model provides a kind of cost low, easy and simple to handle, realizes supply and the control of fuel oil, and can reach the rocket engine ground test starting confession EFM Electronic Fuel Management of continuous start-up function.
The technical solution of the utility model is, control system comprises fueller and control device, described fueller comprises the thick oil filter that is connected successively by oil pipe, electric oil pump, thin oil filter, reduction valve, retaining valve, solenoid valve, the other end of described thick oil filter is connected with oily tower, the other end of solenoid valve is connected with igniter nozzle, an oil circuit that hand valve is installed also is set between the oil-out of described electric oil pump and the oily tower, be provided with an oil circuit between reduction valve oil-out end and the oily tower, described control device comprises controller, operating system, display system, data acquisition system (DAS) and pressure transducer, described pressure transducer one end connects the oil outlet end of fueller, the other end links to each other with the data acquisition system (DAS) of control device, described controller also respectively with solenoid valve, electric oil pump is connected.The oil-out place of described thin oil filter and oil-feed place of solenoid valve are provided with tensimeter, and described controller is the PLC Programmable Logic Controller.The opertaing device of described controller, operating system, display system, data acquisition system (DAS) and test bay shares.
Thin oil filter of the present utility model guarantees that the cleanliness of input fuel oil prevent plug nozzle; The electric oil pump fuel feeding provides the pressure fuel oil; Reduction valve is adjusted the front fuel outlet constant pressure of nozzle, can be stabilized in different value according to different demands; Hand valve is normally closed, can be manually opened when emergent, to cut off fuel delivery, the protection engine; Solenoid valve is realized fuel feed control; Pressure before the pressure transducer gaging nozzle monitors to the number extraction system signal feedback.The unidirectional protection valve prevents that fuel oil from flowing backwards, and produces vent plug when avoiding starting.The utility model part system and test bay opertaing device share, and cost is lower, and fuel feeding is stable, can adjust according to the performance of engine the oil-gas ratio of charge oil pressure and then adjustment start-up period.This equipment can independently be installed in the test bay, can be used as test bay equipment, need not be installed on the engine.For a certain engine, starting is after fuel pressure adjusts, just can stable ignition, do not need frequent adjustment.Engine is when ground experiment, lighting the formation of starting fuel oil with electrical igniter ignites the torch, ignite the torch and light auxiliary fuel and finish engine ignition, because according to engine start sequential control fuel feeding, can guarantee engine ignition opportunity, guarantee the engine ignition starting, make engine need not use cartridge ignition, and can continuous several times start, the igniting cost reduces greatly.
Description of drawings
Fig. 1 is structural representation of the present utility model.
Embodiment
As shown in the figure, the rocket engine ground test starting comprises fueller and control device for EFM Electronic Fuel Management, described fueller comprises the thick oil filter 10 that is connected successively by oil pipe, electric oil pump 9, thin oil filter 7, reduction valve 6, retaining valve 5, solenoid valve 2, the other end of described thick oil filter 10 is connected with oily tower, the other end of solenoid valve 2 is connected with igniter nozzle, an oil circuit that hand valve 8 is installed also is set between the oil-out of described electric oil pump 9 and the oily tower, be provided with an oil circuit between reduction valve 6 oil-out ends and the oily tower, described control device comprises controller 11, operating system 14, display system 13, data acquisition system (DAS) 12 and pressure transducer 1, described pressure transducer 1 one ends connect the oil outlet end of fueller, the other end links to each other with the data acquisition system (DAS) 12 of control device, described controller 11 also respectively with solenoid valve 2, electric oil pump 9 is connected.The oil-out place of described thin oil filter 7 is provided with tensimeter 4.Oil-feed place of described solenoid valve 2 is provided with tensimeter 3.Described controller 11 is the PLC Programmable Logic Controller.Described controller 11, operating system 14, display system 13, data acquisition system (DAS) 12 share with the opertaing device of test bay.
In use, PLC Programmable Logic Controller 11 sends the starting reserved instruction, and supply line is to electric oil pump 9 power supplies, and fuel oil is self-loopa in system.After sending starting order, open to solenoid valve 2 power supply solenoid valves 2, the starting fueller begins fuel feeding.When engine speed reaches 65%, to the circuit outage of electric oil pump and solenoid valve.When sending emergency stop, chain circuit to electric oil pump and solenoid valve, above two supply lines outage this moment.
Claims (5)
1. a rocket engine ground test starting is for EFM Electronic Fuel Management, it is characterized in that, control system comprises fueller and control device, described fueller comprises the thick oil filter [10] that is connected successively by oil pipe, electric oil pump [9], thin oil filter [7], reduction valve [6], retaining valve [5], solenoid valve [2], the other end of described thick oil filter [10] is connected with oily tower, the other end of solenoid valve [2] is connected with igniter nozzle, an oil circuit that hand valve [8] are installed also is set between the oil-out of described electric oil pump [9] and the oily tower, be provided with an oil circuit between reduction valve [6] oil-out end and the oily tower, described control device comprises controller [11], operating system [14], display system [13], data acquisition system (DAS) [12] and pressure transducer [1], described pressure transducer [1] one end connects the oil outlet end of fueller, the other end links to each other with the data acquisition system (DAS) [12] of control device, described controller [11] also respectively with solenoid valve [2], electric oil pump [9] is connected.
2. rocket engine ground test starting as claimed in claim 1 is characterized in that for EFM Electronic Fuel Management the oil-out place of described thin oil filter [7] is provided with tensimeter [4].
3. rocket engine ground test starting as claimed in claim 1 is characterized in that for EFM Electronic Fuel Management oil-feed place of described solenoid valve [2] is provided with tensimeter [3].
4. rocket engine ground test starting as claimed in claim 1 is characterized in that for EFM Electronic Fuel Management described controller [11] is the PLC Programmable Logic Controller.
5. rocket engine ground test starting as claimed in claim 1 is characterized in that for EFM Electronic Fuel Management, and described controller [11], operating system [14], display system [13], data acquisition system (DAS) [12] share with the opertaing device of test bay.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220547120 CN202853900U (en) | 2012-10-24 | 2012-10-24 | Starting oil supply control system for engine ground test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220547120 CN202853900U (en) | 2012-10-24 | 2012-10-24 | Starting oil supply control system for engine ground test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202853900U true CN202853900U (en) | 2013-04-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220547120 Expired - Fee Related CN202853900U (en) | 2012-10-24 | 2012-10-24 | Starting oil supply control system for engine ground test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202853900U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102926882A (en) * | 2012-10-24 | 2013-02-13 | 哈尔滨东安发动机（集团）有限公司 | Engine ground test start oil supply control system |
| CN106769059A (en) * | 2016-11-30 | 2017-05-31 | 江西洪都航空工业集团有限责任公司 | A kind of after-burner nozzle area regulation and measurement apparatus |
-
2012
- 2012-10-24 CN CN 201220547120 patent/CN202853900U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102926882A (en) * | 2012-10-24 | 2013-02-13 | 哈尔滨东安发动机（集团）有限公司 | Engine ground test start oil supply control system |
| CN106769059A (en) * | 2016-11-30 | 2017-05-31 | 江西洪都航空工业集团有限责任公司 | A kind of after-burner nozzle area regulation and measurement apparatus |
| CN106769059B (en) * | 2016-11-30 | 2019-05-14 | 江西洪都航空工业集团有限责任公司 | A kind of after-burner nozzle area adjusts and measuring 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 |
Granted publication date: 20130403 Termination date: 20171024 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |