CN205175581U - Aviation pressure boost conversion valve pressure automatic measuring device - Google Patents
Aviation pressure boost conversion valve pressure automatic measuring device Download PDFInfo
- Publication number
- CN205175581U CN205175581U CN201520899665.0U CN201520899665U CN205175581U CN 205175581 U CN205175581 U CN 205175581U CN 201520899665 U CN201520899665 U CN 201520899665U CN 205175581 U CN205175581 U CN 205175581U
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- aviation
- pressure
- supercharging
- changeover valve
- performance test
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Abstract
The utility model relates to an aviation pressure boost conversion valve pressure automatic measuring device belongs to aeroengine automatic measure technical field, and the device includes a plurality of pressure transmitter, signal isolation ware, data collection card and industrial computer, pressure transmitter installs on aviation pressure boost conversion valve performance test ware, the input of signal isolation ware is connected to pressure transmitter's output, and data collection card's input is connected to the output of signal isolation ware, and the input of industrial computer is connected to data collection card's output. The utility model discloses accomplish standard sample piece's tentation data and result analysis, satisfied the technological requirement to through metrological verification, get into the application of results stage, the device has not only improved experimental precision, has improved work efficiency moreover, has accomplished the requirement of precision equipment production domesticization and the production needs of mill, also provides new thinking for reforming transform later on, has not only solved production efficiency, has improved standard sample piece's quality moreover.
Description
Technical field
The invention belongs to aeromotor automatic measurement technology field, be specifically related to a kind of aviation supercharging changeover valve automatic pressure measuring device.
Background technology
At present, in the prior art, aviation supercharging changeover valve performance test device is adopted to the measurement of aviation supercharging changeover valve pressure, current aviation supercharging changeover valve performance test device is many years ago from the equipment of external import, and oscillography display system is made up of 3 pressure units, light-beam oscillograph and annexes; Test operation flow process is generally: the pressure signal gathered by pressure unit, read with oscillograph, process these pressure signals and get oscillogram at light sensation band, with chi corresponding with measurement verification standard drawing go out actual value, judge aviation supercharging changeover valve positive and negative collaborate whether qualified; This kind of metering system exists that data readings is inaccurate, complex operation, judgement cycle are long, intuitively can not read pressure value, easily occur the shortcomings such as mistake; Due to the widespread use of aviation supercharging changeover valve performance test device, be not easy to be replaced, for many years, there is catabiosis in display system in continuous working, often breaks down, and is difficult to provide good measurement result in motivation overhaul task.
Utility model content
For the deficiencies in the prior art, the utility model proposes a kind of aviation supercharging changeover valve automatic pressure measuring device, improve test accuracy to reach, increase work efficiency and improve the object of master body quality.
A kind of aviation supercharging changeover valve automatic pressure measuring device, comprises multiple pressure unit, signal isolator, data collecting card and industrial computer;
Described pressure unit is arranged on aviation supercharging changeover valve performance test device; The input end of the output terminal connection signal isolator of pressure unit, the input end of the output terminal connection data capture card of signal isolator, the output terminal of data collecting card connects the input end of industrial computer.
This device comprises three pressure units, and the first pressure unit is arranged on the tube wall of the first aspirating pipeline of aviation supercharging changeover valve performance test device, and is connected with the former pressure transducer on the first aspirating pipeline; Second pressure unit is arranged on the tube wall of the gas exhaust piping of aviation supercharging changeover valve performance test device, and is connected with the former pressure transducer on gas exhaust piping; 3rd pressure unit is arranged on the tube wall of the second aspirating pipeline of aviation supercharging changeover valve performance test device, and is connected with the former pressure transducer on the second aspirating pipeline.
Advantage of the present utility model:
A kind of aviation supercharging of the utility model changeover valve automatic pressure measuring device, by the applied research in aviation supercharging changeover valve performance test, complete test figure and the interpretation of result of master body, meet technological requirement, and by measurement verification, enter the application of result stage; This device not only increases test accuracy, and improves work efficiency, completes the requirement of precision equipment production domesticization and the need of production of factory, also for transformation later provides new approaches, not only solves production efficiency, and improves the quality of master body.
Accompanying drawing explanation
Fig. 1 is the aviation supercharging changeover valve automatic pressure measuring device structural representation of a kind of embodiment of the utility model;
Fig. 2 is the aviation supercharging changeover valve performance test device structural representation of a kind of embodiment of the utility model;
Fig. 3 is the pressure transducer of a kind of embodiment of the utility model and the connected mode schematic diagram of pressure unit;
Fig. 4 is the aviation supercharging changeover valve structural representation of a kind of embodiment of the utility model;
To be that the aviation supercharging changeover valve of a kind of embodiment of the utility model is positive and negative collaborate oscillogram to Fig. 5.
Embodiment
Below in conjunction with accompanying drawing, a kind of embodiment of the utility model is described further.
In the present embodiment, as shown in Figure 1, a kind of aviation supercharging changeover valve automatic pressure measuring device, comprises three pressure units, signal isolator, data collecting card and industrial computers;
The input end of the output terminal connection signal isolator of described pressure unit, the input end of the output terminal connection data capture card of signal isolator, the output terminal of data collecting card connects the input end of industrial computer;
In the present embodiment, first pressure unit adopts the pressure unit of P52-1barS-PF-H-20mA (0.1MPa) model, second pressure unit adopts the pressure unit of P51-6barG-P-HD-20mA (0.6MPa) model, and the 3rd pressure unit adopts the pressure unit of P51-25barS-PF-HD-20mA (2.5MPa) model; Signal isolator adopts the signal isolator of Beijing gentle venture company PH-20 model; Data collecting card adopts Taiwan to grind the data collecting card of magnificent PL1-1714 model; Industrial computer adopts the industrial computer grinding magnificent AdvantechIPC610 model; And adopt the LabVIEW2010 common software of America NI company to carry out signal transacting;
In the present embodiment, as shown in Figure 2, in Fig. 2,1 is pressurized air, and 2 is equipment room, 3 is the first variable valve, and 4 is filtrator, and 5 is well heater, 6 is accumulator, and 7 is the second variable valve, and 8 is the first aspirating pipeline, 9 is the first pressure transducer, and 10 is the second aspirating pipeline, and 11 is gas exhaust piping, 12 is the second pressure transducer, and 13 for supercharging changeover valve is by test specimen, and 14 is the 3rd pressure transducer, 15 is display, and 16 is keyboard, and 17 is control stand; First pressure unit is arranged on the tube wall of the first aspirating pipeline of aviation supercharging changeover valve performance test device, and is connected with former first pressure transducer on the first aspirating pipeline; Second pressure unit is arranged on the tube wall of the gas exhaust piping of aviation supercharging changeover valve performance test device, and is connected with former second pressure transducer on gas exhaust piping; 3rd pressure unit is arranged on the tube wall of the second aspirating pipeline of aviation supercharging changeover valve performance test device, and is connected with former 3rd pressure transducer on the second aspirating pipeline; The connected mode of described pressure unit and pressure transducer as shown in Figure 3;
In the present embodiment, can store pressure data, additionally use color laser printer, for printing obtained pressure data, be convenient to staff and checking;
In the present embodiment, aviation supercharging changeover valve structural representation as shown in Figure 4, aviation supercharging changeover valve is contained in by test specimen on the device table top of valve performance test device, and air feed and gas exhaust piping are connected on fixture conversion seat, carry out valve and collaborate pressure test, aviation supercharging changeover valve carries out action (forward is with reverse) and is no less than 3 circulations under auto state, and adopt aviation supercharging changeover valve automatic pressure measuring device to gather the pressure value P 1 of the first aspirating pipeline, the pressure value P 3 of the second aspirating pipeline and the pressure value P 2 of gas exhaust piping also record display,
In the present embodiment, the positive and negative oscillogram that collaborates of aviation supercharging changeover valve (facilitates P1 force value to expand 10 times of displays in the graphic for the ease of observing) as shown in Figure 5, and wherein dotted portion is vernier;
In the present embodiment, process of the test is: under auto state, automatically records real-time pressure data; The wave regions that can gather is amplified, in automatically testing for the first time, the waveform needing to search part is selected to amplify, test be P2 force value start decline that correspondence see current P1 force value, first the vernier of longitudinal direction can be placed on P2 force value start decline that, then keep motionless, again the vernier of transverse direction is placed on P3 force value curve, now horizontal vernier and longitudinal vernier have individual point of crossing, click this point of crossing P13 by right key, so the force value of P3 just can be recorded on the corresponding position of form automatically; Same, test is the force value seeing current P1 at the end of P3 force value, first the vernier of longitudinal direction can be placed on the prominent cusp at the end of P3 force value, then keep motionless, again the vernier of transverse direction is placed on P1 force value curve, now horizontal vernier and longitudinal vernier have individual point of crossing, click this point of crossing P11 by right key, and so the value of P1 just can record on a corresponding position automatically; Same acquisition second time is as shown in table 1 from the pressure data of dynamic test with third time from dynamic test:
Table 1
In the present embodiment, former oscillography display system is manual mode, and what check aviation supercharging changeover valve for 3 times collaborates situation; The utility model is auto state, obtains P1=(0.0653+0.0652+0.0651)/3=0.0652MPa, P3=(0.352+0.351+0.353)/3=0.352MPa; Aviation supercharging changeover valve standard component XX.XX.XX.000-01 standard value is P1=0.0652 (MPa), P3=0.352 (MPa); As can be seen here, after aviation supercharging changeover valve performance test device has been transformed, take from pressure unit input normal pressure at aviation supercharging changeover valve performance test device scene, the method reading force value display result in video data terminal carries out effect, on aviation supercharging changeover valve performance test device, complete duty test has been carried out with aviation supercharging changeover valve standard component after qualified, test the data drawn consistent with standard component nominal data, demonstrate the accuracy of the utility model aviation supercharging changeover valve automatic pressure measuring device.
Claims (2)
1. an aviation supercharging changeover valve automatic pressure measuring device, is characterized in that: this device comprises multiple pressure unit, signal isolator, data collecting card and industrial computer;
Described pressure unit is arranged on aviation supercharging changeover valve performance test device; The input end of the output terminal connection signal isolator of pressure unit, the input end of the output terminal connection data capture card of signal isolator, the output terminal of data collecting card connects the input end of industrial computer.
2. aviation supercharging changeover valve automatic pressure measuring device according to claim 1, it is characterized in that: this device comprises three pressure units, first pressure unit is arranged on the tube wall of the first aspirating pipeline of aviation supercharging changeover valve performance test device, and is connected with the former pressure transducer on the first aspirating pipeline; Second pressure unit is arranged on the tube wall of the gas exhaust piping of aviation supercharging changeover valve performance test device, and is connected with the former pressure transducer on gas exhaust piping; 3rd pressure unit is arranged on the tube wall of the second aspirating pipeline of aviation supercharging changeover valve performance test device, and is connected with the former pressure transducer on the second aspirating pipeline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520899665.0U CN205175581U (en) | 2015-11-11 | 2015-11-11 | Aviation pressure boost conversion valve pressure automatic measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520899665.0U CN205175581U (en) | 2015-11-11 | 2015-11-11 | Aviation pressure boost conversion valve pressure automatic measuring device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205175581U true CN205175581U (en) | 2016-04-20 |
Family
ID=55739559
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520899665.0U Expired - Fee Related CN205175581U (en) | 2015-11-11 | 2015-11-11 | Aviation pressure boost conversion valve pressure automatic measuring device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205175581U (en) |
-
2015
- 2015-11-11 CN CN201520899665.0U patent/CN205175581U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160420 Termination date: 20201111 |