CN203444329U - Air leakage testing stand - Google Patents
Air leakage testing stand Download PDFInfo
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- CN203444329U CN203444329U CN201320541485.6U CN201320541485U CN203444329U CN 203444329 U CN203444329 U CN 203444329U CN 201320541485 U CN201320541485 U CN 201320541485U CN 203444329 U CN203444329 U CN 203444329U
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- air
- cabin
- tight cabin
- steel tube
- leakage testing
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Abstract
The utility model relates to a detection apparatus and specifically discloses an air leakage testing stand. The air leakage testing stand comprises an airtight cabin, a seamless steel pipe arranged and connected under the airtight cabin, a differential pressure sensor arranged in a way to be respectively communicated with the airtight cabin and the seamless steel pipe, and a vacuum pump arranged in a way to be connected with the seamless steel pipe. Both the airtight cabin and the seamless steel pipe are provided with a height indicator. An installation hole for installing a cabin pressure exhaust valve is arranged on the airtight cabin. The seamless steel pipe is arranged in a way to be communicated with the airtight cabin through the cabin pressure exhaust valve. The airtight cabin is further respectively communicated with compressed air and the atmospheric air through two pipelines. The two pipelines are both respectively provided with a flow sensor and a control valve. The air leakage testing stand with a small volume is simpler and more convenient to operate. The measuring results are not affected by the environment. The air leakage testing stand can make a cabin pressure controller and the cabin exhaust valve conveniently calibrated and maintained.
Description
Technical field
The utility model relates to a kind of cabin sealing property tester, relates in particular to a kind of cabin pressure failure amount test unit.
Background technology
Aircraft cabin pressure control system is in order to overcome aircraft environment adverse effect to human body and equipment when the high-altitude flight, guarantees the safe and reliable necessaries of personnel and equipment in cabin.Aircraft cabin pressure control system is the important component part in airplane environment control, its major control and the pressure parameter regulating in passenger cabin, make it according to pressure regime requirement, regulate cockpit pressure, guarantee that aircraft can meet human physiological functions in different flying heights, also will guarantee the intact of aircraft fuselage structure simultaneously.
It is exactly to utilize cockpit pressure controller to regulate the open degree of exhaust valve for cabin that the function of Cabin Pressure Control System realizes, thereby change the air capacity of passenger cabin, change by air capacity realizes the control to cockpit pressure and rate of pressure change, makes it meet cabin pressure schedule.Along with more and more higher to the requirement of aircraft safety comfortableness, while control technology is development also, also more and more higher to the requirement of the control accuracy of each assembly of control pressurer system and safety in utilization like this, therefore be necessary to provide a kind of experimental provision, so that cockpit pressure controller and exhaust valve for cabin are carried out to verification and maintenance.
Original air leakage test unit is because design is of the remote past, and selected device is old, for damaging parts, is difficult to repair and replacement.Secondly, original design is comparatively heavy, and components and parts are various, has not only increased the volume of device, has also added assembly technology difficulty.Moreover the by-pass valve control of original air leakage test unit is many and control loaded down with trivial detailsly, and assembly technology is had relatively high expectations.Therefore, extremely urgent for the update of air leakage table apparatus.
Utility model content
The purpose of this utility model is, proposes a kind of air leakage testing table, and its volume is small and exquisite, operates more simple and conveniently, and measurement result is not affected by environment.
For achieving the above object, the utility model provides a kind of air leakage testing table, it comprises: air-tight cabin, be connected in the weldless steel tube of air-tight cabin below, be communicated with the differential pressure pickup arranging and a vacuum pump that is connected setting with weldless steel tube with air-tight cabin and weldless steel tube respectively; One height indicator is all installed on described air-tight cabin and weldless steel tube, and described air-tight cabin is provided with for the mounting hole of a cockpit pressure exhaust valve is installed, and weldless steel tube is communicated with setting by this cockpit pressure exhaust valve with air-tight cabin; Described air-tight cabin is communicated with setting with pressurized air and atmosphere respectively by two pipelines, on this two pipeline, is provided with respectively flow sensor and by-pass valve control.
During use, described cockpit pressure exhaust valve is installed on air-tight cabin by mounting hole, and this cockpit pressure exhaust valve is also connected setting with a cockpit pressure controller, and this cockpit pressure controller is also communicated with setting with air-tight cabin and weldless steel tube respectively.
Concrete, described weldless steel tube is connected setting by a vacuum tube with vacuum pump, and this vacuum tube is provided with one first valve, is also provided with one second valve on the vacuum tube between this first valve and atmosphere chamber.
Optionally, described flow sensor can adopt air mass flow sensor.
In the utility model, the pipeline between described air-tight cabin and pressurized air is compressed air hose, and this compressed air hose is provided with a by-pass valve control, and the compressed air hose between this by-pass valve control and air-tight cabin is provided with one first air mass flow sensor.
Pipeline between described air-tight cabin and atmosphere is air pipe, and this air pipe is provided with a by-pass valve control, and the air pipe between this by-pass valve control and air-tight cabin is provided with one second air mass flow sensor.
Air leakage testing table of the present utility model, it has cancelled original atmosphere chamber, and the relatively original design of volume reduces 1/3; Moreover its circuit design is comparatively simple, and digitized degree is high, and measurement result is not affected by environment, and under equal conditions simulated altitude has improved 1km; It can simulate various high altitude environments, according to flight service manual, test by the parameters such as air mass flow, overbottom pressure, airtight pressure and decompression rate of exhaust valve for cabin, easily cockpit pressure controller and exhaust valve for cabin are carried out to verification and maintenance, guarantee that aircraft can meet human physiological functions in different flying heights, also can guarantee the intact of aircraft fuselage structure simultaneously.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, to the accompanying drawing of required use in embodiment or description of the Prior Art be briefly described below, apparently, accompanying drawing in the following describes is only embodiment more of the present utility model, for those of ordinary skills, do not paying under the prerequisite of creative work, can also obtain according to these accompanying drawings other accompanying drawing.
Fig. 1 is a kind of specific embodiment of air leakage testing table of the present utility model annexation schematic diagram in use;
Fig. 2 is the mounting structure schematic diagram of atmosphere chamber 10 and air-tight cabin 10 in Fig. 1.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is clearly and completely described, obviously, described embodiment is only the utility model part embodiment, rather than whole embodiment.Embodiment based in the utility model, those of ordinary skills are not making the every other embodiment obtaining under creative work prerequisite, all belong to the scope of the utility model protection.
As shown in Figure 1, 2, the utility model provides a kind of air leakage testing table, it comprises: air-tight cabin 10, be connected in the weldless steel tube 20 of air-tight cabin 10 belows, be communicated with the differential pressure pickup 30 arranging and a vacuum pump (not shown) that is connected setting with weldless steel tube 20 with air-tight cabin 10 and weldless steel tube 20 respectively; On described air-tight cabin 10 and weldless steel tube 20, a height indicator is all installed, described air-tight cabin 10 is provided with the mounting hole (not shown) for a cockpit pressure exhaust valve 40 is installed, and weldless steel tube 20 is communicated with setting by this cockpit pressure exhaust valve 40 with air-tight cabin 10; Described air-tight cabin 10 is communicated with setting with pressurized air and atmosphere respectively by two pipelines 11,12, is provided with respectively flow sensor and by-pass valve control 112,122 on this two pipeline 11,12.Air leakage testing table of the present utility model, it can simulate various high altitude environments, the parameters such as the air mass flow according to the service manual test of flying by cockpit pressure exhaust valve 40, overbottom pressure, airtight pressure, decompression rate, so that verification and the maintenance to cockpit pressure exhaust valve 40 and cockpit pressure controller 50.
Especially, the utility model has been cancelled original atmosphere chamber, adopts the function of weldless steel tube 20 integrated atmosphere chambers.This weldless steel tube is a kind of economic section steel, and it has hollow section, compares with solid steel such as round steel, and when bending resistance twisting strength is identical, weight is lighter; Meanwhile, adopt weldless steel tube also can improve stock utilization, simplify manufacturing process, save material and machining period.Atmosphere chamber Main Function is that simulated atmosphere is pressed, and it vacuumizes acquisition negative pressure by vacuum pump, and in actual use, we find to adopt aluminum component atmosphere chamber result of use not obvious, take volume large, and have increased assembling number of times.Therefore in the utility model bold cancellation atmosphere chamber, original atmosphere chamber function is integrated in the middle of weldless steel tube 20.In actual experiment, we find, under same experiment condition, the utility model adopts the design of weldless steel tube 20 integrated atmosphere chambers can obtain higher vacuum tightness, and this just means that we can provide higher altitude simulation, under equal conditions approximately can improve simulated altitude 1km.As a kind of selectivity embodiment of the present utility model, also can use the integrated atmosphere chamber of flexible pipe, flexible pipe has pliability, can assemble easily, do not need right alignment to install, but for hose material, need to test, because be negative pressure in flexible pipe, if be subject to atmospheric pressure to affect flexible pipe hardness, flexible pipe can be inhaled not flat.Therefore utility model can select corrugated tube or wired hose to substitute the integrated atmosphere chamber of weldless steel tube.
In the utility model, on described air-tight cabin 10 and weldless steel tube 20, be separately installed with a height indicator 13,21, this height indicator 13,21 can be inserted in air-tight cabin 10 and weldless steel tube 20 by a pipe respectively.Further, described weldless steel tube 20 is connected setting by a vacuum tube 22 with vacuum pump, and this vacuum tube 22 is provided with one first valve 23, is also provided with one second valve 24 on the vacuum tube 22 between this first valve 23 and weldless steel tube 20.This vacuum pump is for providing negative pressure to be used for simulating various flying heights to weldless steel tube 20.Described the first valve 23 can adopt vacuum butterfly valve, and it can be used as gas medium adjust flux or carries out rupturing operation.Described the second valve 24 is a safety valve, its opening and closing element is subject under External Force Acting in normally off, pressure medium in vacuum tube 22 raises, and automatically opens pressure release while surpassing setting, by outside discharge medium, prevents that the interior pressure medium of vacuum tube 22 from surpassing specified value.
The draught head that adopts differential pressure pickup 30 to measure between air-tight cabin 10 and weldless steel tube 20 in the utility model.This differential pressure pickup 30 has advantages of that compared to traditional mercury differential manometer digitized degree is higher.Moreover these differential pressure pickup 30 units of display are international unit kpa, and the result unit of display of traditional measurement mechanism is mmHg, and net result also needs to carry out one time Conversion of measurement unit again.
In the utility model, described flow sensor can adopt air mass flow sensor, this air mass flow sensor is by molecular mass, to calculate the flow of air, it is measuring equipment of new generation, its measurement result can not be subject to the impact of the environmental factors such as temperature, pressure, therefore measuring accuracy is higher, and measurement range is wider.Moreover this air mass flow sensor unit of display is international unit Nm
3/ H, and the result unit of display of traditional measurement mechanism is kg/h, net result also needs to carry out one time Conversion of measurement unit again.Certainly, as other selectivity embodiment of the present utility model, can also adopt the turbine flow transducer that cost ratio air mass flow sensor is cheap to replace, but the pressure of environment temperature and use need to be set while selecting turbine flow transducer.Concrete, pipeline 11 between described air-tight cabin 10 and pressurized air is compressed air hose, this compressed air hose is provided with a by-pass valve control 112, and the compressed air hose between this this by-pass valve control 112 and air-tight cabin 10 is provided with one first air mass flow sensor 114.Pipeline 12 between described air-tight cabin 10 and atmosphere is air pipe, and this air pipe is provided with a by-pass valve control 122, and the air pipe between this by-pass valve control 122 and air-tight cabin 10 is provided with one second air mass flow sensor 124.In concrete use, the compressed air hose of the external army of described compressed air hose, air pipe is directly connected with air.Described the first air mass flow sensor 114 and the second air mass flow sensor 124 are all for measuring the flow of passenger cabin pressure exhaust valve 40.Concrete, described the first air mass flow sensor 114 is directly installed on compressed air hose, and for bigness scale flow, the value range of its measurement is larger; The second air mass flow sensor 124 is directly installed on air pipe, and for accurate measurement, the value range of its measurement is less.
The utility model in use, described cockpit pressure exhaust valve 40 can be installed on air-tight cabin 10 by mounting hole, this cockpit pressure exhaust valve 40 is equivalent to a valve here, and weldless steel tube 20 is connected with air-tight cabin 10 by this cockpit pressure exhaust valve 40.This cockpit pressure exhaust valve 40 is also connected setting with a cockpit pressure controller 50, and this cockpit pressure controller 50 is also communicated with setting with air-tight cabin 10 and weldless steel tube 20 respectively.Cockpit pressure exhaust valve 40 Wei Yi topworkies, can get rid of the unnecessary air of passenger cabin by the given signal of cockpit pressure controller 50.Cockpit pressure controller 50 is that it can regulate aircraft inside and outside differential pressure to transporting 7, transporting 8 aircraft cabin pressure governor motions, and protection aircraft does not cause the destruction on aircaft configuration because inside and outside differential pressure is excessive.In the utility model specific embodiment, described cockpit pressure exhaust valve 40 can be the model exhaust valve for cabin that is CTQ-19, and cockpit pressure controller 50 can be the model cockpit pressure controller that is CTQ18.Certainly, air leakage testing table of the present utility model can also be for the exhaust valve for cabin to different models such as model are CTQ23, and model is that the cockpit pressure controller of the different models such as CTQ11, CTQ15 carries out verification and maintenance.
Air leakage testing table of the present utility model is when starting vacuum pump, and the height indicator 21 at weldless steel tube 20 places highly starts to increase.At this moment by by-pass valve control, control the air mass flow that enters air-tight cabin 10, and show flow by flow sensor, the shown flow of this flow sensor, and the shown pressure of differential pressure pickup 30 all should meet " exhaust valve for cabin " flight airmanship, " cockpit pressure controller " flight airmanship.For example, when flying height is when being 8000 meters, the flow by cockpit pressure exhaust valve 40 should be 50kg/h-800kg/h (38.5Nm
3/ H-616Nm
3/ h), at this moment the overbottom pressure in aircraft should be 22.1 ± 2kpa(166 ± 15mmhg), aircraft cabin pressure should be at 57.7kpa(433mmhg).Its concrete operations are as follows: first open vacuum pump, make the height indicator 21 at weldless steel tube 20 places have highly reaction, then open the by-pass valve control on compressed air hose, to weldless steel tube 20 air feed 616Nm
3/ h, the height of the height indicator 21 at control weldless steel tube 20 places, at 8000 meters, is at this moment observed differential pressure pickup 30 and be should be 22.1 ± 2kpa(166 ± 15mmhg), at this moment complete a verification.
As the first specific embodiment of the present utility model, described air leakage testing table can detect cockpit pressure controller 50 overbottom pressure performances, and it can adopt following two operations:
A: when cockpit pressure controller 50 overbottom pressure performances are detected, cockpit pressure exhaust valve 40 and cockpit pressure controller 50 are connected on air leakage testing table of the present utility model, be about to a cockpit pressure exhaust valve 40 and be installed on air-tight cabin 10 by mounting hole, cockpit pressure controller 50 is connected with air-tight cabin 10, weldless steel tube 20 and cockpit pressure exhaust valve 40 respectively.Start to be arranged on 101kpa by cockpit pressure controller 50 is airtight, overbottom pressure is arranged on 19.6kpa; Open vacuum pump to weldless steel tube 20 exhausts, when weldless steel tube 20 place's height indicators 21 change, the by-pass valve control 112 of opening on compressed air hose leads to pressurized air to air-tight cabin 10; By the first valve 23 foldings sizes of control vacuum pump, controlling height indicator 21 on weldless steel tubes 20 is 2500 meters, and by controlling the by-pass valve control 112 foldings sizes on compressed air hose, control charge flow rate is 38.5Nm
3/ H-770Nm
3within the scope of/H, now differential pressure pickup 30 shows that pressure reduction should be 19.6 ± 3.3kpa.
B: cockpit pressure exhaust valve 40 and cockpit pressure controller 50 are connected on this air leakage testing table, start to be arranged on 101kpa by cockpit pressure controller 50 is airtight, overbottom pressure is arranged on 29.3kpa; Open vacuum pump to weldless steel tube 20 exhausts, when the height indicator 21 at weldless steel tube 20 places changes, the by-pass valve control 112 of opening on compressed air hose leads to pressurized air to air-tight cabin 10; By the first valve 23 foldings sizes of control vacuum pump, control height indicator 21 on weldless steel tubes 20 and be shown as 9000 meters, by controlling the by-pass valve control 112 foldings sizes on compressed air hose, control charge flow rate is 38.5Nm
3/ H-616Nm
3within the scope of/H, (by the second air mass flow sensor 114, show), now differential pressure pickup 30 shows that pressure reduction should be 29.3 ± 2kpa.
As the second specific embodiment of the present utility model, described air leakage testing table can detect cockpit pressure controller 50 decompression performances.When cockpit pressure controller 50 decompression performances are detected, cockpit pressure exhaust valve 40 and cockpit pressure controller 50 are connected on air leakage testing table, start to be arranged on 101kpa by cockpit pressure controller 50 is airtight; Open vacuum pump to weldless steel tube 20 exhausts, when the height indicator 21 at weldless steel tube 20 places changes, the by-pass valve control 112 of opening on compressed air hose leads to pressurized air to air-tight cabin 10; By the first valve 23 foldings sizes of control vacuum pump, controlling height indicator 21 on weldless steel tubes 20 is 8000 meters, and by controlling the by-pass valve control 112 foldings sizes on compressed air hose, control charge flow rate is 770Nm
3/ H, now differential pressure pickup 30 shows that pressure reduction should be 67pa/s to 667pa/s.
As the third specific embodiment of the present utility model, air leakage testing table of the present utility model can also detect the air leakage of cockpit pressure exhaust valve 40.When the air leakage of cockpit pressure exhaust valve 40 is detected, first a cockpit pressure exhaust valve 40 is connected on air leakage testing table of the present utility model, open vacuum pump, on differential pressure pickup 30, show when pressure reduction is 23kpa, open by-pass valve control 122 on air pipe to air-tight cabin 10 blowing airs, the flow of observing on the second air mass flow sensor 124 should be less than 38.5Nm
3.
As another kind of specific embodiment of the present utility model, described air leakage testing table can detect the 40 overbottom pressure limiter work of cockpit pressure exhaust valve.When to cockpit pressure exhaust valve, 40 overbottom pressure limiter work detect, cockpit pressure exhaust valve 40 is connected on air leakage testing table, open vacuum pump to weldless steel tube 20 exhausts, when the height indicator 21 at weldless steel tube 20 places changes, open by-pass valve control 122 on air pipe to air-tight cabin 10 blowing airs, at this moment by controlling by-pass valve control 122 foldings sizes on compressed air hose, control weldless steel tube 20 place's height indicators 21 and be shown as 5000m, the flow by the by-pass valve control 122 on air pipe should be greater than 38.5Nm
3(by the second air mass flow sensor 124, showing), differential pressure pickup 30 shows that pressure reduction should be 44 ± 2kpa.
The foregoing is only preferred embodiment of the present utility model; not in order to limit the utility model; all within spirit of the present utility model and principle, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (6)
1. an air leakage testing table, is characterized in that, comprises air-tight cabin, is connected in the weldless steel tube of air-tight cabin below, is communicated with respectively the differential pressure pickup arranging with air-tight cabin and weldless steel tube, and be connected the vacuum pump arranging with weldless steel tube; One height indicator is all installed on described air-tight cabin and weldless steel tube, and described air-tight cabin is provided with for the mounting hole of a cockpit pressure exhaust valve is installed, and weldless steel tube is communicated with setting by this cockpit pressure exhaust valve with air-tight cabin; Described air-tight cabin is communicated with setting with pressurized air and atmosphere respectively by two pipelines, on this two pipeline, is provided with respectively flow sensor and by-pass valve control.
2. air leakage testing table as claimed in claim 1, it is characterized in that, described cockpit pressure exhaust valve is installed on air-tight cabin by mounting hole, this cockpit pressure exhaust valve is also connected setting with a cockpit pressure controller, and this cockpit pressure controller is also communicated with setting with air-tight cabin and weldless steel tube respectively.
3. air leakage testing table as claimed in claim 1, is characterized in that, described weldless steel tube is connected setting by a vacuum tube with vacuum pump, and this vacuum tube is provided with one first valve, is also provided with one second valve on the vacuum tube between this first valve and atmosphere chamber.
4. air leakage testing table as claimed in claim 1, is characterized in that, described flow sensor adopts air mass flow sensor.
5. air leakage testing table as claimed in claim 4, it is characterized in that, pipeline between described air-tight cabin and pressurized air is compressed air hose, this compressed air hose is provided with a by-pass valve control, and the compressed air hose between this by-pass valve control and air-tight cabin is provided with one first air mass flow sensor.
6. air leakage testing table as claimed in claim 5, it is characterized in that, pipeline between described air-tight cabin and atmosphere is air pipe, and this air pipe is provided with a by-pass valve control, and the air pipe between this by-pass valve control and air-tight cabin is provided with one second air mass flow sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320541485.6U CN203444329U (en) | 2013-09-02 | 2013-09-02 | Air leakage testing stand |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320541485.6U CN203444329U (en) | 2013-09-02 | 2013-09-02 | Air leakage testing stand |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203444329U true CN203444329U (en) | 2014-02-19 |
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ID=50095362
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320541485.6U Expired - Fee Related CN203444329U (en) | 2013-09-02 | 2013-09-02 | Air leakage testing stand |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203444329U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103424231A (en) * | 2013-09-02 | 2013-12-04 | 成都飞亚航空设备应用研究所有限公司 | Air leakage testing bed and detection method using same |
| CN106768941A (en) * | 2016-12-15 | 2017-05-31 | 南通华夏飞机工程技术股份有限公司 | Outflow safety valve device for testing functions |
| CN110646147A (en) * | 2018-06-27 | 2020-01-03 | 波音公司 | Enhanced assembly inspection and leak detection of aircraft doors |
-
2013
- 2013-09-02 CN CN201320541485.6U patent/CN203444329U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103424231A (en) * | 2013-09-02 | 2013-12-04 | 成都飞亚航空设备应用研究所有限公司 | Air leakage testing bed and detection method using same |
| CN106768941A (en) * | 2016-12-15 | 2017-05-31 | 南通华夏飞机工程技术股份有限公司 | Outflow safety valve device for testing functions |
| CN106768941B (en) * | 2016-12-15 | 2019-07-09 | 南通华夏飞机工程技术股份有限公司 | Outflow safety valve device for testing functions |
| CN110646147A (en) * | 2018-06-27 | 2020-01-03 | 波音公司 | Enhanced assembly inspection and leak detection of aircraft doors |
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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: 20140219 Termination date: 20150902 |
|
| EXPY | Termination of patent right or utility model |