CN2788164Y - Airplane engine gas directing system detector - Google Patents
Airplane engine gas directing system detector Download PDFInfo
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- CN2788164Y CN2788164Y CN 200420056825 CN200420056825U CN2788164Y CN 2788164 Y CN2788164 Y CN 2788164Y CN 200420056825 CN200420056825 CN 200420056825 CN 200420056825 U CN200420056825 U CN 200420056825U CN 2788164 Y CN2788164 Y CN 2788164Y
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- pressure
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- pipeline
- aircraft engine
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Abstract
The utility model relates to a detector for an air directing system of an airplane engine, which is composed of a precision pressure meter, a pressure meter of oil damping, a differential pressure gauge, a pressure reducer, a precision regulator, a shut-off shutter, a system selection shutter, an air supplying and venting selection shutter, a high pressure air storage bottle, an air venting needle valve, an air pouring interface and a testing interface which are all connected by pipelines. The utility model adopts high precision instruments and reasonable allocation of instruments and air control elements, which can enable the instruments to rapidly and accurately carry out wing tests to an air directing system of an airplane engine, and an active test structure of containing a personal air source is formed; the utility model is also provided with a structure of pouring air by the air bottle, which can enable the active property to be combined with operations of convenient air replenishment and ensure operation of the air source with air supply. The utility model is a device combining a box body with a walking vehicle, and realizes technical goals of convenience, easy carrying, safety and flexible movement.
Description
Technical field
The utility model relates to a kind of pick-up unit of aircraft engine air supply system, especially has the pick-up unit of tonifying Qi structure, portable aircraft engine air supply system.
Background technology
The function of engine bleed air system is to go up bleed from engine or APU, is air-conditioning on the machine, hot anti-icing, the potable water of wing and radome fairing and hydraulic system supercharging, and provide the air of the High Temperature High Pressure with uniform temperature and certain pressure for engine starting system.Its normal operation not only provides safety, comfortable flight environment of vehicle and normal water supply function for passenger cabin and driving cabin, also provides anti-icing thermal source of heat and the power source in the engine starting process for engine health.Out of control as this bleed air system at the myriametre height, will cause the not normal of cabin internal pressure and temperature, light clamp lug then is heavy then cause injury to the passenger.
Engine bleed air system is the ecp system of a complexity, comprise precooler control valve, valve is regulated and turn-offed to pressure, the bleed regulator, the high pressure stage valve, the high pressure stage regulator, 390 thermostats, 450 thermostats and 490 numerous assemblies such as overtemperature electric switch have the numerous regulation device, valve, sensor and attached electrical equipment, and connected pipeline, wherein any one part goes wrong, the capital causes the fault of bleed air system, want to find the problem part in the system that these numerous parts are formed, just become difficult thing, the site examining and repairing work of taking over is which parts decision problem by rule of thumb appears on and investigate one by one with the way of replacement parts, observe through dismounting repeatedly, come the problem identificatioin place.
Disclosed Chinese patent 01247057.0 has been introduced a kind of pressure tester.Be to constitute by air compression assembly, pressure survey display module, Control Component and Power Supply Assembly, described air compression assembly comprises pump and motor, described Control Component comprise with the air compression assembly in total head interface, the static pressure interface of pressure accumulation bottle by pipeline connection, and the total head variable valve static pressure protective valve on the pipeline, wherein: employed pump is the oil-free vacuum forcing pump in the described air compression assembly; Described pressure survey display module comprises pressure transducer and the single-chip microcomputer, display and the function supervisory keyboard that are attached thereto.Be used to check impermeability, the bellows instruments of aircraft pitot-static pressure system, also can be used for the measurement and the manometric calibration of various pipeline pressures.Its technology belongs to computer-controlled atmosphere data test macro.Can not solve the detection of aircraft engine bleed air system.
Industry demands that a kind of not only handled easily person carries, but also whether normal checkout equipment comes out can to differentiate aircraft engine bleed air system parts at the wing urgently.
Summary of the invention
Problem to be solved in the utility model be to answer market urgently, overcome the deficiencies in the prior art, a kind of detector of aircraft engine bleed air system is provided, be convenient to each parts be carried out detecting at the wing at the fault of aircraft engine bleed air system;
Primary and foremost purpose of the present utility model is, a kind of detector of the aircraft engine bleed air system with the instrument configuration gas supply assembly is provided;
Another purpose of the present utility model is, the detector of the portable aircraft engine bleed air system of a kind of box body shape is provided;
A purpose more of the present utility model is, a kind of detector safe and reliable, mobile portable aircraft engine bleed air system is provided.
The utility model solves its technical matters and takes following technical scheme to realize:
According to a kind of aircraft engine bleed air system detector that the utility model provides, comprise test port and the tensimeter, the regulator that meet accuracy requirement, wherein:
One main decompressor high-pressure side connects with a high-pressure air feed assembly by pipeline, main decompressor has its high pressure of demonstration and low-pressure side reading one an oil damping tensimeter and a principal pressure table, the low pressure end of this main decompressor is connected in series with air feed venting selector valve and system's selector valve successively, a needle-valve and this air feed venting selector valve one termination dress; Described system selector valve one end and a test port are connected;
Another outlet side, road by system's selector valve is connected in series a regulator by pipeline, and the output terminal of this regulator is connected by pipeline and No. four test ports via this output terminal of pressure neon of pipeline tipping
Between a regulator and a tensimeter, pass through line branches, be connected in series successively and turn-off valve for No. three, turn-off valve No. four, between this two shutoffs valve, connect by pipeline and No. six test ports;
The pipeline place of turn-offing valve and No. six test port connections at No. three passes through line branches, turn-offs valve, differential pressure indicator No. two of serial connection successively, and connects with No. five test ports;
Between described take-off line place to six test port,, turn-off valve and No. three needle-valves No. seven of serial connection successively by line branches;
Another road of being told by the outlet side of system's selector valve is connected in series a shutoff valve, No. two regulators, No. five shutoff valve, No. two tensimeters successively by pipeline; Between No. five shutoff valve and No. two tensimeters, pass through line branches, link to each other with No. two test ports, and No. six shutoff valve and No. two needle-valves also communicate with No. two test ports by pipeline.
Described No. two regulators are connected by pipeline and No. three test ports.
It is to take following technical scheme further to realize that the utility model solves its technical matters:
Aforementioned aircraft engine bleed air system detector, wherein, described high-pressure air feed assembly is made of adaptive high-pressure gas cylinder and gas cylinder gas filling mean.
Aforementioned aircraft engine bleed air system detector, wherein, the gas transmission end deploy switch device of described high-pressure gas cylinder; The porch configuration air strainer of the inflation of aforesaid gas cylinder gas filling mean.
Aforementioned aircraft engine bleed air system detector, wherein, described each instrument be installed in first the device panel on, but described each test port and controlling element be installed in first the device panel be opening-closing tectonics second the device panel on, constitute portable casing.
Aforementioned aircraft engine bleed air system detector wherein, disposes the inflation adapter that is complementary with aforementioned gas cylinder gas filling mean in the described casing.
Aforementioned aircraft engine bleed air system detector, wherein, described box body device is expert in the mule carriage.
Aforementioned aircraft engine bleed air system detector, wherein, described walking car has the vibration damping groove of device box, device damping internal layer in this groove.
Aforementioned aircraft engine bleed air system detector, wherein, four road wheels of described walking car install stop motion mechanism respectively.
Aforementioned aircraft engine bleed air system detector, wherein, described principal pressure table is 200 pounds/square inch, and a tensimeter, No. two tensimeters are 60 pounds/square inch, and differential pressure indicator is 25 inches of mercury, and the high-pressure gas cylinder capacity is 4 liters.
The utility model compared with prior art has significant advantage and beneficial effect.
By above technical scheme as can be known, under its excellent structural arrangements, has following advantage at least: the reasonable structure of high-precision instrument and instrument and control gas element in the utility model, can make instrument carry out also can realizing carrying out anti-current test at the aircraft engine bleed air system rapidly and accurately in wing test; Because the utility model has disposed gas cylinder at random, thereby has constituted the active test macro that self contains source of the gas; Owing to disposed the gas cylinder gas filling mean, can realize the tonifying Qi of the gas cylinder aeration mouth " bottle is to bottle " of tester, active property is combined with tonifying Qi operation easily, can guarantee source of the gas, the air feed operation; Inflation porch at the gas cylinder gas filling mean has disposed air strainer, is used for removing any impurity particle of nitrogen cylinder, to guarantee the accuracy of detection of instrument.
But the utility model is installed in each instrument and each test port and controlling element on the device panel that is opening-closing tectonics, constitutes portable casing, and dispose the inflation adapter in casing, has realized convenience, the purpose that can take;
The utility model has anti-quaking structure walking car in conjunction with one, has further realized safe and reliable, movable technical purpose.
Embodiment of the present utility model is provided in detail by following examples and accompanying drawing thereof.
Description of drawings
Fig. 1 is the utility model test system structure principle schematic;
Fig. 2 is the utility model one-piece construction synoptic diagram.
Embodiment
Below in conjunction with preferred embodiment, to according to embodiment provided by the invention, feature and effect thereof, describe in detail as after; For simple and purpose clearly, hereinafter appropriate omission the description of known technology, in order to avoid those unnecessary details influences are to the description of the technical program.
Aircraft B737 engine bleed air system is from 5 grades in engine or 9 grades or APU air feed, its outlet provides the power source of temperature and pressure through overregulating, to after the air-conditioning, wing and the radome fairing that connect hot anti-icing, the High Temperature High Pressure air with uniform temperature and pressure is provided in the supercharging of water and hydraulic system and the engine starting process.
See also a kind of aircraft engine bleed air system detector shown in Fig. 1-2, comprise several test ports 51-56 and several tensimeters, the regulator that meet accuracy requirement, wherein, principal pressure table 81 and oil damping tensimeter 80 are connected on the low pressure and the high-pressure side of main decompressor 2 respectively, this main decompressor connects with a high-pressure air feed assembly 1 by pipeline, the low pressure end of this main decompressor is connected in series with air feed venting selector valve 41 and system's selector valve 42 successively, No. one needle-valve 91 is adorned with this air feed venting selector valve B termination, is used for venting; Described system selector valve 42 and a test port 51 are connected, and this road provides the output of 0-200 pound/square inch pressure, by main decompressor adjustment, by a test port output;
Output terminal D by system's selector valve 42 tells two-way, and the air pressure of adjusting through main decompressor via each regulator minute adjustment, by corresponding test port output, provides thus from 0-60 pound/square inch pressure and exports again, specifically:
Lead up to regulator 61 of pipeline serial connection by what the outlet side D of system's selector valve 42 told, the output terminal of this regulator is via tensimeter 83 of pipeline tipping, and this output terminal is simultaneously by pipeline and No. four test ports 54 connections;
Between regulator 61 and No. two tensimeters 83,, turn-off valve 73 successively for No. three of serial connection, turn-off valve 74 No. four, two turn-off between valve by pipeline and No. six test ports 56 connections at this by line branches;
The pipeline E place of turn-offing valve 73 and No. six test port 56 connections at No. three passes through line branches, turn-offs valve 72, differential pressure indicator 82 No. two of serial connection successively, and connects with No. five test ports 55;
Between described take-off line E place to six test port 56,, turn-off valve 77 and No. two needle-valves 93 No. seven of serial connection successively by line branches;
Another road of being told by the outlet side D of system's selector valve 42 is connected in series and turn-offs valve 71, No. two regulators 62 for No. one, turn-offs for No. five valve 75, No. two tensimeters 84 successively by pipeline; Between No. five shutoff valve 75 and No. two tensimeters 84, pass through line branches, link with No. two test ports 52, and No. six shutoff valve 76 and No. two needle-valves 92 also link by pipeline and No. two test ports 52.
Described No. two regulators 62 are connected by pipeline and No. three test ports 53;
Aforesaid high-pressure air feed assembly 1 is made of a high-pressure gas cylinder 11 and gas cylinder gas filling mean 10, and 12 is the switchgear of gas bomb 11; Device gas cylinder gas filling mean on the pipeline between gas bomb and the main decompressor can in time carry out the tonifying Qi operation to gas cylinder when high-pressure gas cylinder 11 tolerance are not enough, guarantee to detect the source of the gas supply of operation; The porch configuration air strainer of the inflation of aforesaid gas cylinder gas filling mean 10.
Aforementioned aircraft engine bleed air system detector, wherein each instrument is installed in device panel 21 No. one, but each test port and controlling element be installed in device panel and be on No. two of opening-closing tectonics device panels 22, constitute portable casing I; Dispose the inflation adapter that is complementary with aforementioned gas cylinder gas filling mean in the described annex casing;
Aforementioned aircraft engine bleed air system detector, wherein said casing I device is in having the walking car II of vibration damping groove 31, establish damping internal layer 311 in the damping groove, four road wheels 32 of walking car install stop motion mechanism 321 respectively, when preventing test jobs, testing tool moves under external force, causes the damaged in collision of aircraft or engine; The stop motion mechanism of described vibration damping groove and road wheel is known technology, will not give unnecessary details;
Aforementioned aircraft engine bleed air system detector, technology that can be known are given walking car configuration dust cover.
So far, the box body shape that aircraft engine bleed air system detector can be portable is combined into a movably unitary construction with the walking car, can move convenient working neatly in machine level ground or hangar.
The utility model can pass through three checkout procedures, the precooler of bleed air system is controlled valve, pressure adjusting and valve-off, bleed regulator, senior shutoff valve, senior regulator, 390 thermostats (giving cooler), 450 7 parts such as thermostat carry out testing at the wing;
Also anti-current test can be carried out according to reasonable disposition of the present utility model, and the fault isolation operation can be finished.
Below, at length narrate the utility model principle of work by the example of " detecting precooler control valve ".
Precooler control valve is that spring is carried in out (cold) position and pneumatic actuation arrives a control module that closes (heat) position.
At first check the original state of precooler control valve, the state when promptly not giving gas.If be initially in off-position, can judge precooler control valve fault, change it;
Import an air pressure by test port 54 of the present utility model to precooler control valve voltage supply mouth, regulating accurate decompressor 2 makes principal pressure table 81 be designated as (50 ± 5) pound/square inch, because its reading of test job that carries out with this tester all has error range, so it is the test instrumentation of a metering type.Regulate regulator 61 and make tensimeter 83 indication (12.0 ± 2.0) pound/square inches, precooler control this moment valve should be in 30 ° of scopes of complete shut-down position.If not in this scope, need to check 390 ° of thermostats, big wing hot gas puts the ice solenoid and whether related joint and pipeline has seepage, inspection method is: import 10.0 pounds of/square inch pressure by test port 54 of the present utility model to precooler control valve sensor port, if there is not seepage, can confirm that precooler control valve has fault, will change it.
If check out seepage and repair, from air pressure of precooler control valve controlled pressure mouth input, principal pressure table 81 indication (95.0 ± 2.0) pound/square inch, this pressure is supplied with by test port 51 of the present utility model, and the sensor port that precooler is controlled valve connected a testing tube to test port 56 of the present utility model, should confirm that precooler control valve position indicator is within 30 ° of scopes of complete shut-down position this moment, slowly open then and turn-off valve 72, confirm that differential pressure indicator 82 indications are (20.5 ± 2.0) inches of mercury, keeping under the supply gas pressure permanence condition, slowly adjust the venting needle-valve 93 that is connected with test port 56 and regulate differential pressure indicator 82 indications, as differential pressure indicator indication (16+0,-1) during the inch of mercury, should be corresponding to " minimum pressure that precooler control valve begins to open ".And when differential pressure indicator indication (7.0) inch of mercury, precooler control valve should be full-gear.If do not satisfy the pressure limit of above-mentioned unlatching of presenting and standard-sized sheet, will change precooler control valve.
Obviously, what final step was measured is the full control function of precooler control valve, has provided from just being opened to the pressure limit of full open mode.
After the preferred embodiment that describes in detail, being familiar with this technology personage can clearly understand, can carry out various variations and modification not breaking away under described claim and the spirit, and the utility model also is not subject to the embodiment of illustrated embodiment in the instructions.
Claims (9)
1. an aircraft engine bleed air system detector comprises test port and the tensimeter, the regulator that meet accuracy requirement, it is characterized in that:
One main decompressor (2) high-pressure side connects with a high-pressure air feed assembly (1) by pipeline, main decompressor (2) has its high pressure of demonstration and low-pressure side reading one an oil damping tensimeter (80) and a principal pressure table (81), the low pressure end of this main decompressor is connected in series with air feed venting selector valve (41) and system's selector valve (42) successively, a needle-valve (91) and this air feed venting selector valve one end (B) tipping; Described system selector valve one end (C) is connected with a test port (51);
Another outlet side, road (D) by system's selector valve (42) is connected in series a regulator (61) by pipeline, and the output terminal of this regulator is via a pipeline tipping tensimeter (83), and this output terminal is connected by pipeline and No. four test ports (54) simultaneously;
Between a regulator (61) and a tensimeter (83),, be connected in series successively and turn-off valve (73) for No. three, turn-off valve (74) No. four, between this two shutoffs valve, connect by pipeline and No. six test ports (56) by line branches;
Turn-off valve (73) at No. three and locate by line branches, turn-off valve (72), differential pressure indicator (82) No. two of serial connection successively, and connect with No. five test ports (55) with the pipeline (E) that No. six test ports (56) are connected;
Locate to pass through between No. six test ports (56) line branches at described take-off line (E), turn-off valve (77) and No. three needle-valves (93) No. seven of serial connection successively;
Another road of being told by the outlet side (D) of system's selector valve (42) is connected in series successively by pipeline and turn-offs valve (71), No. two regulators (62) for No. one, turn-offs valve (75), No. two tensimeters (84) No. five; Turn-offing for No. five between valve (75) and No. two tensimeters (84), link to each other with No. two test ports (52), and No. six shutoff valve (76) and No. two needle-valves (92) also communicate with No. two test ports by pipeline by line branches.
Described No. two regulators (62) are connected by pipeline and No. three test ports (53).
2. aircraft engine bleed air system detector according to claim 1 is characterized in that, aforementioned high-pressure air feed assembly (1) is made of adaptive high-pressure gas cylinder (11) and gas cylinder gas filling mean (10).
3. aircraft engine bleed air system detector as claimed in claim 2 is characterized in that, the gas transmission end deploy switch device of aforesaid high-pressure gas cylinder (11); The porch configuration air strainer of the inflation of aforesaid gas cylinder gas filling mean (10).
4. as the described aircraft engine bleed air system of one of claim 1-3 detector, it is characterized in that, described each instrument is installed on the first device panel (21), but described each test port and controlling element are installed in the first device panel and are on the second device panel (22) of opening-closing tectonics, constitute portable casing (I).
5. aircraft engine bleed air system detector as claimed in claim 4 is characterized in that, disposes the inflation adapter that is complementary with aforementioned gas cylinder gas filling mean (10) in the described casing.
6. aircraft engine bleed air system detector as claimed in claim 5 is characterized in that, described casing (I) device is expert in the mule carriage (II).
7. aircraft engine bleed air system detector as claimed in claim 6 is characterized in that, described walking car has the vibration damping groove (31) of device box, device damping internal layer (311) in this groove.
8. as claim 6 or 7 described aircraft engine bleed air system detectors, it is characterized in that four road wheels (32) of described walking car install stop motion mechanism (321) respectively.
9. as the described aircraft engine bleed air system of one of claim 1-3 detector, it is characterized in that described principal pressure table is 200 pounds/square inch, a tensimeter, No. two tensimeters are 60 pounds/square inch, differential pressure indicator is 25 inches of mercury, and the high-pressure gas cylinder capacity is 4 liters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420056825 CN2788164Y (en) | 2004-12-16 | 2004-12-16 | Airplane engine gas directing system detector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420056825 CN2788164Y (en) | 2004-12-16 | 2004-12-16 | Airplane engine gas directing system detector |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2788164Y true CN2788164Y (en) | 2006-06-14 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200420056825 Expired - Fee Related CN2788164Y (en) | 2004-12-16 | 2004-12-16 | Airplane engine gas directing system detector |
Country Status (1)
| Country | Link |
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| CN (1) | CN2788164Y (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101738296B (en) * | 2008-11-17 | 2013-06-19 | 北京卫星环境工程研究所 | Method for detecting leakage of spacecraft cabin by differential pressure |
| CN103439115A (en) * | 2013-09-13 | 2013-12-11 | 中国南方航空工业(集团)有限公司 | Air entrainment detection device of aero-engine |
| CN104236891A (en) * | 2014-09-29 | 2014-12-24 | 北京飞机维修工程有限公司 | On-wing testing device for temperature control valves of aircrafts |
| CN104343538A (en) * | 2013-07-25 | 2015-02-11 | 波音公司 | Bleed air systems for use with aircrafts and related methods |
| CN105957418A (en) * | 2016-04-29 | 2016-09-21 | 中国民航大学 | Aircraft engine bleed air system fault simulation device |
| CN106054955A (en) * | 2016-05-18 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Multi-air source system flow balance controlling apparatus |
| CN106124237A (en) * | 2016-08-17 | 2016-11-16 | 中国商用飞机有限责任公司 | transient fluid thermal power test device |
| CN113074948A (en) * | 2021-03-31 | 2021-07-06 | 西安翔迅科技有限责任公司 | Aeroengine air-entraining test equipment and test method |
-
2004
- 2004-12-16 CN CN 200420056825 patent/CN2788164Y/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101738296B (en) * | 2008-11-17 | 2013-06-19 | 北京卫星环境工程研究所 | Method for detecting leakage of spacecraft cabin by differential pressure |
| CN104343538B (en) * | 2013-07-25 | 2017-10-03 | 波音公司 | Blow-off system and correlation technique for aircraft |
| CN104343538A (en) * | 2013-07-25 | 2015-02-11 | 波音公司 | Bleed air systems for use with aircrafts and related methods |
| CN103439115B (en) * | 2013-09-13 | 2016-08-17 | 中国南方航空工业(集团)有限公司 | The air entrainment detection device of aero-engine |
| CN103439115A (en) * | 2013-09-13 | 2013-12-11 | 中国南方航空工业(集团)有限公司 | Air entrainment detection device of aero-engine |
| CN104236891A (en) * | 2014-09-29 | 2014-12-24 | 北京飞机维修工程有限公司 | On-wing testing device for temperature control valves of aircrafts |
| CN104236891B (en) * | 2014-09-29 | 2017-01-25 | 北京飞机维修工程有限公司 | On-wing testing device for temperature control valves of aircrafts |
| CN105957418A (en) * | 2016-04-29 | 2016-09-21 | 中国民航大学 | Aircraft engine bleed air system fault simulation device |
| CN106054955A (en) * | 2016-05-18 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Multi-air source system flow balance controlling apparatus |
| CN106054955B (en) * | 2016-05-18 | 2019-05-24 | 中国航空工业集团公司西安飞机设计研究所 | A kind of multiple air supply system flow balance controller |
| CN106124237A (en) * | 2016-08-17 | 2016-11-16 | 中国商用飞机有限责任公司 | transient fluid thermal power test device |
| CN106124237B (en) * | 2016-08-17 | 2018-08-03 | 中国商用飞机有限责任公司 | Transient fluid thermal power test device |
| CN113074948A (en) * | 2021-03-31 | 2021-07-06 | 西安翔迅科技有限责任公司 | Aeroengine air-entraining test equipment and test method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20060614 Termination date: 20100118 |