CN204731026U - A kind of airplane engine fuel oil analog control system - Google Patents
A kind of airplane engine fuel oil analog control system Download PDFInfo
- Publication number
- CN204731026U CN204731026U CN201520373035.XU CN201520373035U CN204731026U CN 204731026 U CN204731026 U CN 204731026U CN 201520373035 U CN201520373035 U CN 201520373035U CN 204731026 U CN204731026 U CN 204731026U
- Authority
- CN
- China
- Prior art keywords
- fuel
- pipeline
- pressure
- oil
- dynamic
- 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
Links
Landscapes
- Testing Of Engines (AREA)
Abstract
The utility model provides a kind of airplane engine fuel oil analog control system, and system comprises system pressure and regulates pipeline, dynamic flow field simulation pipeline, oil consumption pipeline; And utilize the various variable valve on pipeline to carry out flow regulation and simulation.The utility model be a kind of simple to operate, parameters precision is high, can in conjunction with fuel consume and can provide the set of dynamic stream again to the consumption of fuel oil, be suitable for simulating the system that all kinds engine fuel consumes by simulated engine separately, this system also has self-checking function, can with system integration test before carry out equipment self-loopa work, verify that can it reach using state.
Description
Technical field
The application relates to aircraft engine control system field, particularly a kind of airplane engine fuel oil analog control system.
Background technology
With the growth of aircraft fleet and the continuous growth of pilot time number, in outfield operation process, fuel system exposes great number of issues and fault.
There is a lot of defect in present existing engine fuel analog control system.Such as: dynamic flowing pressure is shown by pointer pressure, and due to switch-mode regulation coarse, dynamic flowing pressure and instability of flow, make pressure display error comparatively large, in addition, in former simulation system, only have pressure to show, without flow information, cannot the real duty of accurate simulation engine, therefore accurately cannot carry out the functional verification of fuel system qualitatively, use that only can be quantitative.
Now need to provide a kind of airplane engine fuel oil analog control system, can accurately simulate the various state of fuel oil and flow regulation and measurement, meet the requirement of simplation verification in the fault simulation of aircraft fuel system, functional verification and new machine development process.
Summary of the invention
The object of the application is the problem in order to the simulation and flow regulation solving the fuel consume of fuel system under various duty.
A kind of airplane engine fuel oil analog control system, comprises system pressure and regulates pipeline, dynamic flow field simulation pipeline, oil consumption pipeline; System pressure regulates line upstream to connect aircraft fuel system oil transportation outlet, and downstream connects the outlet of fuel system pressure variable valve; System pressure adjustable pipe curb fuel flow direction connects entrance flowmeter, inlet pressure transducer, inlet pressure table, inlet filter, inlet one-way valve, heat abstractor, temperature sensor, variable-frequency motor, retaining valve, system pressure variable valve, safety valve, system pressure sensor, system pressure table successively; Dynamic flow field simulation line upstream connected system pressure-regulating valve outlet, downstream connects the dynamic inflow entrance of fuel system, and the pipeline along fuel flow direction connects dynamic flowing pressure variable valve, dynamic stream pipeline switch, dynamic flow pressure sensor, dynamic flowing pressure table, dynamic stream flowmeter successively; Oil consumption line upstream connected system pressure-regulating valve exports, downstream connects fuel system fuel consume entrance, is connecting oil consumption pipeline switch, oil consumption tensimeter, oil consumption pressure transducer, oil consumption flow control valve, oil consumption flowmeter, oil depot entry switch successively along on the pipeline of fuel flow direction.Self-inspection pipeline is also comprised in system, a wherein road entrance connected system fuel reserve tank outlet, oil absorption filter, fuel reserve tank gate out switch is connected successively along fuel flow direction, outlet is connected to system pressure and regulates the inlet one-way valve on pipeline to export, another road entrance connects the oil consumption flowmeter outlet of oil consumption pipeline, outlet is connected with fuel reserve tank entrance, and two sections of pipelines regulate together with pipeline with system pressure, forms ring seal self-inspection pipeline.
The advantage of the application be it be a kind of simple to operate, parameters precision is high, can in conjunction with fuel consume and can provide the set of dynamic stream again to the consumption of fuel oil, be suitable for simulating the system that all kinds engine fuel consumes by simulated engine separately, this system also has self-checking function, can with fuel system joint-trial before carry out self-loopa work, verify that can it reach using state.
Below in conjunction with embodiment accompanying drawing, this application is described in further detail.
Accompanying drawing explanation
Fig. 1 starts motor-driven flow field simulation equipment schematic
Number description:
1 inlet flow rate meter; 2 inlet pressure transducers; 3 inlet pressure tables; 4 inlet filters; 5 inlet one-way valves; 6 heat abstractors; 7 temperature sensors; 8 variable-frequency motors; 9 retaining valves; 10 system pressure variable valve; 11 safety valve; 12 dynamic flowing pressure variable valve; 13 system pressure sensor; 14 system pressure tables; 15 dynamic stream pipeline switchs; 16 dynamic flow pressure sensors; 17 dynamic flowing pressure tables; 18 dynamic stream flowmeters; 19 oil consumption pipeline switchs; 20 oil consumption tensimeters; 21 oil consumption pressure transducers; 22 oil consumption flow control valves; 23 oil consumption flowmeters; 24 oil depot entry switches; 25 fuel reserve tank entry switches; 26 fuel reserve tank temperature sensors; 27 fuel reserve tank air cleaner; 28 fuel reserve tank fuel outlet valves; 29 fuel reserve tanks; 30 fuel reserve tank liquid level gauges; 31 oil absorption filters; 32 fuel reserve tank gates out switch; 33 fuel pumps.
Embodiment
As shown in Figure 1, airplane engine fuel oil analog control system, comprises system pressure and regulates pipeline, dynamic flow field simulation pipeline, oil consumption pipeline; System pressure regulates line upstream to connect aircraft fuel system oil transportation outlet, and downstream connects fuel system pressure variable valve 10 and exports; System pressure adjustable pipe curb fuel flow direction connects entrance flowmeter 1, inlet pressure transducer 2, inlet pressure table 3, inlet filter 4, inlet one-way valve 5, heat abstractor 6, temperature sensor, variable-frequency motor, retaining valve, system pressure variable valve, safety valve, system pressure sensor 13, system pressure table 14 successively; Dynamic flow field simulation line upstream connected system pressure-regulating valve 10 exports, downstream connects the dynamic inflow entrance of fuel system, and the pipeline along fuel flow direction connects dynamic flowing pressure variable valve 12, dynamic stream pipeline switch 15, dynamic flow pressure sensor 16, dynamic flowing pressure table 17, dynamic stream flowmeter 18 successively; Oil consumption line upstream connected system pressure-regulating valve 10 exports, downstream connects fuel system fuel consume entrance, is connecting oil consumption pipeline switch 19, oil consumption tensimeter 20, oil consumption pressure transducer 21, oil consumption flow control valve 22, oil consumption flowmeter 23, oil depot entry switch 24 successively along on the pipeline of fuel flow direction.
The self-inspection of internal duct also can be carried out in system, comprise two sections of pipelines, wherein a road entrance connected system fuel reserve tank outlet, connects oil absorption filter 31, fuel reserve tank gate out switch 32 successively along fuel flow direction, and outlet is connected to system pressure and regulates the inlet one-way valve 5 on pipeline to export; The oil consumption flowmeter 23 that another road entrance connects oil consumption pipeline exports, and export as fuel reserve tank 29 entrance, centre is provided with fuel reserve tank entry switch 25; Two sections of pipelines regulate together with pipeline with system pressure, form ring seal self-inspection pipeline.
When carrying out fuel-flow control with airplane engine fuel oil analog control system and regulating, can operate as follows:
A) opening fuel system motor drives fuel pump 33 to work, by fuel oil suction system pressure regulation tube road, fuel oil filters out impurity in fuel through inlet filter 4, again after heat abstractor 6 cools, fuel oil temperature is measured with temperature sensor 7, regulate fuel pump 33 simultaneously, fuel oil mineralization pressure oil is exported;
B) system pressure variable valve 10 is transferred to a force value (working pressure of a little higher than fuel system demand); When regulating force value, if pressure exceedes equipment requirement index, by safety valve 11 pressure release, equipment is protected;
C) the dynamic flowing pressure variable valve 12 on dynamic flow field simulation pipeline is regulated, pressure needed for adjustment fuel pressure to system works;
D) open dynamic stream pipeline switch 15, with dynamic flow pressure sensor 16 measure, dynamic flowing pressure table 17 shows current fuel pressure, continues to regulate the dynamic flowing pressure variable valve on dynamic flow field simulation pipeline, makes that the pressure displayed value after adjustment is satisfied moves flowing pressure requirement; Make fuel oil enter fuel system by dynamic flow export at this pressure, the height formed needed for system works presses stream, drives fuel system work, and checks that whether fuel system is working properly under this dynamic flowing pressure value;
E) while dynamic stream pipeline switch 15 is opened, open oil consumption pipeline switch 19, regulate oil consumption flow (i.e. simulated engine oil consumption oil mass), open oil depot entry switch 24, fuel oil enters oil depot (namely simulating fuel oil to be consumed by engine) by oil consumption outlet;
F) self-inspection can be carried out before the work of connection fuel system;
F-1) closing dynamic stream pipeline switch 15, oil depot entry switch 24, refueling in fuel reserve tank 29 to being greater than 200L (being observed by fuel reserve tank liquid level gauge)
F-2) open fuel reserve tank 29 gate out switch 32, fuel reserve tank entry switch 25, oil consumption pipeline switch 19, start fuel pump 33
F-3) fuel oil in fuel reserve tank 29 cools through oil absorption filter filter 23 1, heat abstractor 6 under pressure, measures the fuel oil temperature after heat radiation, enter fuel pump 33 inlet port with temperature sensor 7
F-4) regulate fuel pump 33 mineralization pressure oil to export from fuel pump outlet, through oil consumption pipeline switch 19, oil consumption pressure transducer 20, oil consumption tensimeter 21 detect,
F-5) regulate oil consumption flow, detect oil return flow with oil consumption flowmeter 23, fuel oil flows in fuel reserve tank 29 through fuel reserve tank entry switch 25, observes home loop state, completion system self-inspection.
Claims (2)
1. an airplane engine fuel oil analog control system, is characterized in that, comprises system pressure and regulates pipeline, dynamic flow field simulation pipeline, oil consumption pipeline; Described system pressure regulates line upstream to connect aircraft fuel system oil transportation outlet, and downstream connects the outlet of fuel system pressure variable valve; Described system pressure adjustable pipe curb fuel flow direction connects entrance flowmeter, inlet pressure transducer, inlet pressure table, inlet filter, inlet one-way valve, heat abstractor, temperature sensor, variable-frequency motor, retaining valve, system pressure variable valve, safety valve, system pressure sensor, system pressure table successively; Described dynamic flow field simulation line upstream connected system pressure-regulating valve outlet, downstream connects the dynamic inflow entrance of fuel system, and the pipeline along fuel flow direction connects dynamic flowing pressure variable valve, dynamic stream pipeline switch, dynamic flow pressure sensor, dynamic flowing pressure table, dynamic stream flowmeter successively; Described oil consumption line upstream connected system pressure-regulating valve outlet, downstream connects fuel system fuel consume entrance, is connecting oil consumption pipeline switch, oil consumption tensimeter, oil consumption pressure transducer, oil consumption flow control valve, oil consumption flowmeter, oil depot entry switch successively along on the pipeline of fuel flow direction.
2. a kind of airplane engine fuel oil analog control system according to claim 1, it is characterized in that comprising System self-test pipeline, described System self-test pipeline, a wherein road entrance connected system fuel reserve tank outlet, oil absorption filter, fuel reserve tank gate out switch is connected successively along fuel flow direction, outlet is connected to system pressure and regulates the inlet one-way valve on pipeline to export, another road entrance connects the oil consumption flowmeter outlet of oil consumption pipeline, outlet is connected with fuel reserve tank entrance, two sections of pipelines regulate together with pipeline with system pressure, form ring seal self-inspection pipeline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520373035.XU CN204731026U (en) | 2015-06-02 | 2015-06-02 | A kind of airplane engine fuel oil analog control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520373035.XU CN204731026U (en) | 2015-06-02 | 2015-06-02 | A kind of airplane engine fuel oil analog control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204731026U true CN204731026U (en) | 2015-10-28 |
Family
ID=54389366
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520373035.XU Expired - Fee Related CN204731026U (en) | 2015-06-02 | 2015-06-02 | A kind of airplane engine fuel oil analog control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204731026U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109655274A (en) * | 2017-10-11 | 2019-04-19 | 中国航发西安动力控制科技有限公司 | A kind of environmental tester having failure of pump diagnostic function |
-
2015
- 2015-06-02 CN CN201520373035.XU patent/CN204731026U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109655274A (en) * | 2017-10-11 | 2019-04-19 | 中国航发西安动力控制科技有限公司 | A kind of environmental tester having failure of pump diagnostic function |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104931266B (en) | A kind of airplane engine fuel oil analog control system and adjusting method | |
| CN103306968B (en) | transformer oil pump test device and test method thereof | |
| CN202133551U (en) | Airplane fuel accessory performance test system | |
| CN203549406U (en) | Fuel gas pressure regulating metering skid-mounted device for petroleum and gas | |
| CN106200668B (en) | Outer loop energy resource system and its test method for semi-physical simulation | |
| CN102996426B (en) | Test system for main fuel pump of airplane | |
| CN201548400U (en) | Test system of aviation auxiliary engine fuel regulator | |
| CN109026484B (en) | Control system of on-line detection platform of automobile air inlet type oil sprayer | |
| CN203216670U (en) | Pressure gauge concentrated pressure supply batch verification apparatus | |
| CN110455547B (en) | High-temperature and high-pressure test system for power machinery combustion chamber test | |
| CN110595760A (en) | Test bed system suitable for measuring fuel nozzle main pipe of combustion chamber of gas turbine | |
| CN202140375U (en) | Comprehensive testing table of plane servo valve, steering engine and braking valve | |
| CN201034807Y (en) | Test bench of vaporizing oil servo gear unit test system | |
| CN204731026U (en) | A kind of airplane engine fuel oil analog control system | |
| CN201126688Y (en) | Nuclear power plant instrument control synthetic training apparatus | |
| CN203981382U (en) | Large flow pneumatic accessories testing table | |
| CN204458305U (en) | A kind of detection facility of Double-liquid mud-injection pump | |
| CN109383847A (en) | A kind of auxiliary power unit fuel nozzle testboard | |
| CN111735633B (en) | Pressure load loading and strain online test system for fuel oil electric control regulator | |
| CN205740325U (en) | A kind of portable quantitatively barrelling equipment | |
| CN209321289U (en) | A kind of auxiliary power unit fuel nozzle testboard | |
| CN203980439U (en) | Heat measuring system auto hydraulic balance control device | |
| CN201364178Y (en) | Fuel consumption rate measuring device for real ship | |
| CN207066730U (en) | A kind of fuel nozzle air pulling liquid type multi-function test stand | |
| CN205918535U (en) | Engine fuel pressure regulation system |
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: 20151028 Termination date: 20190602 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |