CN102192065A - Device for detecting function of oil fuel booster pump of civil aircraft - Google Patents
Device for detecting function of oil fuel booster pump of civil aircraft Download PDFInfo
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- CN102192065A CN102192065A CN2010101272679A CN201010127267A CN102192065A CN 102192065 A CN102192065 A CN 102192065A CN 2010101272679 A CN2010101272679 A CN 2010101272679A CN 201010127267 A CN201010127267 A CN 201010127267A CN 102192065 A CN102192065 A CN 102192065A
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Abstract
The invention relates to a device for detecting the function of an oil fuel booster pump of a civil aircraft. The device comprises a main fuel tank, an auxiliary fuel tank, a fuel oil liquid indicator, a fuel oil liquid regulating valve, a flow (pressure) regulating valve, a turbine flowmeter, a precision pressure gauge, an electric motor pump assembly, an oil suction filter, an oil return filter, a blocking alarm, a flow quantity display meter, a shutoff valve, a medium frequency amperemeter, an operation table, a cooler and a thermometer. In the device, the alternative test oil of which the oil flash value is much higher than that of aviation fuel oil RP-3 is adopted, so that the risk of combustion explosion under the factory condition is reduced; the main fuel tank and the auxiliary fuel tank do not turn over, and the oil leakage is avoided; rapid and accurate regulation on the height of liquid level is ensured by an oil well pump and the liquid regulating valve; more quick and stable regulation on the flow of the outlet of a tested pump is realized by an electric control precision throttling valve; and the temperature of a fuel oil tank is stabilized within the ranges of setting temperature +/-2 DEG C because the opening of a proportion water valve is matched with the temperature of the fuel tanks. The whole equipment system has a compact structure, safe and practical performance and attractive appearance, and is efficiency and convenience in operation.
Description
Technical field
What the present invention relates to is a kind of detection device, and what be specifically related to is a kind of detection device of aircarrier aircraft oil fuel booster pump test function.
Background technique
Be used to detect the testing apparatus of the every function of aircarrier aircraft oil fuel booster pump, be whether to meet the design code scope, thereby judge whether this pump performance is qualified, whether reaches the seaworthiness safety standard and the use of installing by simulating the various performance parameters of this pump.
Abroad, follow the development of aircarrier aircraft flight and systems technology, oil fuel booster pump has had the use history of good decades.At US and European, oil fuel booster pump detection technique and equipment are widely adopted.
Also there is the detection facility of the similar functions finished in China for satisfying army's civil aircraft oil fuel booster pump product seaworthiness and safety requirement.But the test oil of the fuel pump testing apparatus that China adopts is fuel oil, and is inflammable at the bottom of the fuel oil flash-point, and the burn-proof and explosion prevention safety installations between test carriage require high; Equipment adopts upset fuel tank mode mostly, when tested pump promptly is installed, need forward the mounting flange of fuel tank more than the liquid level of fuel tank top to, not only operation inconvenience, and to fuel tank up and down each junction plane sealability require very high, otherwise leakage of oil easily; Liquid level height is fixed, and can not satisfy the different requirement of different fuel pump requirement liquid level height.
Summary of the invention
At the deficiency on the prior art, the present invention seeks to be to provide a kind of fuel pump device for testing functions that satisfies restriction multiple different fuel pump test conditions, that be not subjected to environmental conditions, convenient operating maintenance, high working efficiency.
To achieve these goals, the technical solution used in the present invention is: the detection device of aircarrier aircraft oil fuel booster pump test function, adopt a kind of and RP-3 Aviation Fuel at 0～50 ℃ of temperature range lower density test replacement oil all identical with viscosity, adopt major and minor two fuel tanks, tested oil fuel booster pump is installed on the main fuel tank, has been avoided the fuel tank upset; Adopt electric-motor pump to the collaborative liquid level of regulating of main fuel tank oil pumping and Liquid level adjusting valve.
Described main fuel tank is communicated with drop tank by oil feed line, is provided with one-way valve in the described oil feed line, to prevent the main fuel tank fuel oil drop tank that flows backwards back; Also being provided with the test oil that filter comes drop tank in oil feed line filters clean; Precision pressure gauge, big turbine flowmeter, little turbine flowmeter, accurate throttle valve and tubular cooler also are installed on the export pipeline of described tested oil fuel booster pump outlet end.
Described accurate throttle valve is automatically controlled throttle valve, and is fast to the speed of Flow-rate adjustment, precision is high, flow is more stable.
The liquid level of main fuel tank utilizes fluid level control valve to open, and is adjusted to specified value by bleeding off some oil; Before tested oil fuel booster pump powers up work, each valve of tested pump discharge is reached maximum; Behind the tested pump work, slowly turn down accurate throttle valve, the flow value and the force value of flowmeter and record precision pressure gauge; When flow is turned big turbine flowmeter down and can not accurately be reflected in the pipeline real traffic data, close shut-off valve, read the numerical value of this stage flowmeter and precision pressure gauge; In the tested pump discharge pipeline tubular cooler is installed, cooler makes the whole test system oil liquid temperature constant with cooling tower (workshop equipment) water cooling, and thermometer is installed in main fuel tank and drop tank place; It is clean to guarantee main fuel tank fluid that the oil return filter also is installed in the tested pump discharge pipeline;
For making system more stable, main fuel tank and drop tank are respectively equipped with first air respiratorresuscitator and second air respiratorresuscitator; For easy to maintenance, the fuel outlet valve that liquid level is regulated usefulness is installed between main fuel tank and drop tank, described fuel outlet valve comprises first fuel outlet valve, second fuel outlet valve and the 3rd fuel outlet valve.
Described oil fuel booster pump function detection device is with the fuel flow of the tested pump discharge of automatically controlled accurate throttle valve adjustment.
What described tubular cooler adopted is cooling tower, also is provided with thermometer at described main fuel tank and drop tank place, and the ratio water valve of automatic control oil temperature is installed at cooling water channel.
Working procedure of the present invention: tested pump (aircraft is adorned) is installed on the flange of the positive side of fuel tank, with oil well pump the filler opening of tested pump is submerged in (requiring according to the technical data that possesses product) behind certain liquid level, the medium-frequency power (providing as required) of certain 28V direct current or 400HZ is provided for the test pump, tested pump high speed rotating and then the fuel oil in the fuel tank pumped, regulate the opening aperture of fuel pressurization pump discharge, after the pump discharge flow reaches predetermined range, with accurate flowmeter survey and write down pump discharge pressure and whether reach the technical data claimed range; Change rate of discharge, measure and write down new outlet pressure.Continue to detect all other regulation performance parameters and with the specified data contrast, thereby with the every performance of the tested pump of data display whether in acceptability limit.The entire equipment system architecture is rationally compact, and performance is safe and practical, and it is efficiently convenient to operate, and beautiful shape is generous.
Beneficial effect of the present invention:, thereby reduced the danger of oil inflame blast under the factory condition because native system adopts alternative test oil flash value more much higher than RP-3 Aviation Fuel; Major and minor two fuel tanks need not overturn and avoid leakage of oil danger; Oil well pump and Liquid level adjusting valve have guaranteed that the liquid level adjusting accurately fast; The Flow-rate adjustment that automatically controlled accurate throttle valve makes tested pump discharge is faster and stable; The temperature of ratio water valve aperture and fuel tank adapts, and guarantees that fuel oil fuel tank temperature stabilization is in ℃ scope of setting temperature ± 2; The entire equipment system architecture is rationally compact, and performance is safe and practical, and it is efficiently convenient to operate, and beautiful shape is generous.
Description of drawings
Fig. 1 is a structure principle chart of the present invention.
Among the figure: 1, drop tank; 2, fuel outlet valve; 3, thermometer; 4, air respiratorresuscitator; 5, fuel outlet valve; 6, oiling electric-motor pump assembly; 7, one-way valve; 8, accurate filter; 9, fluid level control valve; 10, main fuel tank; 11, fuel outlet valve; 12, thermometer; 13, level meter; 14, air respiratorresuscitator; 15, compacting pressure table; 16, turbine flowmeter (greatly); 17, shut-off valve; 18, turbine flowmeter (little); 19, accurate throttle valve; 20, tubular cooler; 21, oil return filter, 22, tested oil fuel booster pump.
Embodiment
For technological means, creation characteristic that the present invention is realized, reach purpose and effect is easy to understand, below in conjunction with embodiment, further set forth the present invention.
With reference to figure 1, as shown in Figure 1, this oil fuel booster pump function detection device adopts and a kind ofly fuel pump is detected at 0～50 ℃ of temperature range lower density test replacement oil all identical with viscosity with the RP-3 Aviation Fuel, has reduced the danger of oil inflame blast under the factory condition; It comprises the main fuel tank 10 that is used to install tested oil fuel booster pump 22; As the electric-motor pump assembly 6 of dynamical element to the main fuel tank fuel feeding; With the useless unprecedented arrangement drop tank 1 in test bench bottom, this main fuel tank 10 is communicated with drop tank 1 by oil feed line; The fuel oil of main fuel tank 10 is taken out from drop tank 1 by electric-motor pump assembly 6, its integral device compact structure, and beautiful shape is generous.
In the present embodiment, described main fuel tank 10 and drop tank 1 are two oil tank systems of installing up and down, and main fuel tank 10 is last, and drop tank 1 is at following (the fuel tank bottom is concordant with mounting base).The setting height(from bottom) of tested pump testing just in time is to be grown up to stand to be convenient to install the height of pump, and the mounting or dismounting of pump on test bench before and after the test are all very convenient.
In main fuel tank 10 and oil feed line that drop tank 1 is connected, be provided with one-way valve 7, to prevent the main fuel tank 10 fuel oils drop tank that flows backwards back; It also is provided with the test oil that filter 8 comes drop tank 1 and filters clean; The liquid level of main fuel tank 10 utilizes fluid level control valve 9 to open, and is adjusted to specified value by bleeding off some oil.
Precision pressure gauge 15, big turbine flowmeter 16, little turbine flowmeter 18 and accurate throttle valve 19 also are installed on the export pipeline of described tested oil fuel booster pump 22 outlet end successively; Described big turbine flowmeter 16 and little turbine flowmeter 18 adopts the tandem mounting structures, is that two flowmeters are installed on the straight tube, and the pipeline length that is used for flux test can be accomplished the shortest and flow measuring data is accurate, disturbs few.
In the present embodiment, described accurate throttle valve 19 is automatically controlled throttle valve, and is fast to the speed of Flow-rate adjustment, precision is high, flow is more stable.Before tested oil fuel booster pump powers up work, each valve of tested pump discharge is reached maximum; Behind the tested pump work, slowly turn down accurate throttle valve 19, the flow value and the force value of flowmeter 16 and record precision pressure gauge 15.
In the tested pump discharge pipeline tubular cooler 20 is installed, cooler makes the whole test system oil liquid temperature constant with cooling tower (workshop equipment) water cooling, and thermometer is installed in main fuel tank 10 and drop tank 1 place; It is clean to guarantee main fuel tank fluid that oil return filter 21 also is installed in the tested pump discharge pipeline; For making system more stable, main fuel tank 10 is provided with first air respiratorresuscitator 14, and drop tank 1 is provided with second air respiratorresuscitator 4; For easy to maintenance, the fuel outlet valve that liquid level is regulated usefulness is installed between main fuel tank 10 and drop tank 1, described fuel outlet valve comprises first fuel outlet valve 11, second fuel outlet valve 2 and the 3rd fuel outlet valve 5.
When the present invention uses, tested pump is installed on the flange of main fuel tank 10, being connected to flexible pipe of tested pump discharge detects on the oil circuit, checks whether each valve of main fuel tank, interface are blocked, and whether each sealing surface good seal; To electric-motor pump assembly 6 power supply starting electrical machinery pumps, the oil of drop tank be drawn into main fuel tank up to liquid level a little more than the data requirement liquid level; Open fluid level control valve 9, become the limit of draining the oil and observe the liquid level scale that main fuel tank fluid is presented at level meter, when liquid level just in time meets data requirement, fluid level control valve 9 tightened and close; Shut-off valve 17, accurate throttle valve 19 are turned on fully open position; By data requirement power line is connected in the power socket of tested oil fuel booster pump, starts tested oil fuel booster pump; Move after 1～2 minute, start cooling water valve and cooling tower, setting the fuel tank temperature is specified value; Slowly turn down accurate throttle valve 19, force value and the flow value and the record of record precision pressure gauge 15 and flowmeter 16.
When flow is turned big turbine flowmeter down and can not accurately be reflected in the pipeline real traffic data, close shut-off valve 17, read the numerical value and the record of this stage precision pressure gauge 15 and flowmeter 18; Repeat above test, the detected parameters and the performance parameter contrast of pump regulation of tested pump are judged whether this pump performance is qualified, otherwise test again after defective fuel pumping repair shop decomposed, cleans, detects, repairs, assembles.
The present invention adopts alternative test oil flash value more much higher than RP-3 Aviation Fuel, thereby has reduced the danger of oil inflame blast under the factory condition; Adopt major and minor two fuel tanks, fuel tank need not overturn thereby avoid leakage of oil danger; Adopt collaborative adjusting of oil well pump and Liquid level adjusting valve to guarantee the liquid level requirement; The Flow-rate adjustment that adopts automatically controlled accurate throttle valve to make tested pump discharge is faster and stable; Employing ratio water valve, the temperature of its water valve aperture and fuel tank adapts, and guarantees that fuel oil fuel tank temperature stabilization is in ℃ scope of setting temperature ± 2; The entire equipment system architecture is rationally compact, and performance is safe and practical, and it is efficiently convenient to operate, and beautiful shape is generous.
More than show and described basic principle of the present invention and major character and advantage of the present invention.The technician of the industry should understand; the present invention is not restricted to the described embodiments; that describes in the foregoing description and the specification just illustrates principle of the present invention; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements all fall in the claimed scope of the invention.The claimed scope of the present invention is defined by appending claims and equivalent thereof.
Claims (7)
1. the detection device of aircarrier aircraft oil fuel booster pump test function is characterized in that, it comprises that one is used to install the main fuel tank of tested oil fuel booster pump;
One as the electric-motor pump assembly of dynamical element to the main fuel tank fuel feeding;
One drop tank by oil feed line connection main fuel tank, the fuel oil of described drop tank is drawn into main fuel tank by the electric-motor pump assembly;
One adjusts the fluid level control valve of fuel liquid level height in the main fuel tank, and it is arranged on the main fuel tank;
In described oil feed line, be provided with one-way valve and filter, precision pressure gauge, big turbine flowmeter, little turbine flowmeter, accurate throttle valve and tubular cooler also are installed on the export pipeline of described tested oil fuel booster pump outlet end, described main fuel tank is provided with first air respiratorresuscitator, and described drop tank is provided with second air respiratorresuscitator.
2. according to the described aircarrier aircraft oil fuel booster pump of claim 1 function detection device, it is characterized in that: described main fuel tank and the drop tank two oil tank systems for installing up and down, described main fuel tank is arranged on the top of described drop tank.
3. according to the described aircarrier aircraft oil fuel booster pump of claim 1 function detection device, it is characterized in that: described big turbine flowmeter and little turbine flowmeter adopt the tandem mounting structure.
4. according to the described aircarrier aircraft oil fuel booster pump of claim 1 function detection device, it is characterized in that: described accurate throttle valve is automatically controlled throttle valve.
5. according to claim 1 or 2 described aircarrier aircraft oil fuel booster pump function detection devices, it is characterized in that: the fuel outlet valve that liquid level is regulated usefulness is installed between main fuel tank and drop tank, and described fuel outlet valve comprises first fuel outlet valve, second fuel outlet valve and the 3rd fuel outlet valve.
6. according to the described aircarrier aircraft oil fuel booster pump of claim 1 function detection device, it is characterized in that: the oil return filter also is installed in the described tested oil fuel booster pump export pipeline.
7. according to the described aircarrier aircraft oil fuel booster pump of claim 1 function detection device, it is characterized in that: what described tubular cooler adopted is cooling tower, also is provided with thermometer at described main fuel tank and drop tank place.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101272679A CN102192065A (en) | 2010-03-18 | 2010-03-18 | Device for detecting function of oil fuel booster pump of civil aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101272679A CN102192065A (en) | 2010-03-18 | 2010-03-18 | Device for detecting function of oil fuel booster pump of civil aircraft |
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| Publication Number | Publication Date |
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| CN102192065A true CN102192065A (en) | 2011-09-21 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2010101272679A Pending CN102192065A (en) | 2010-03-18 | 2010-03-18 | Device for detecting function of oil fuel booster pump of civil aircraft |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102996426A (en) * | 2012-11-19 | 2013-03-27 | 武汉航达航空科技发展有限公司 | Test system for main fuel pump of airplane |
| CN105020128A (en) * | 2015-07-06 | 2015-11-04 | 安徽精科检测技术有限公司 | Comprehensive performance test bed of fuel pumps |
| CN105781956A (en) * | 2016-01-13 | 2016-07-20 | 哈尔滨飞机工业集团有限责任公司 | Booster pump tester |
| CN108661837A (en) * | 2017-03-30 | 2018-10-16 | 中国船舶重工集团公司第七研究所 | Oil supply system |
| CN109654528A (en) * | 2018-12-14 | 2019-04-19 | 重庆军通汽车有限责任公司 | A kind of fuel system of smoke generator |
| CN111232231A (en) * | 2020-02-06 | 2020-06-05 | 陈志霖 | Wing built-in aviation oil tank pressurizing device |
| CN112555140A (en) * | 2020-10-30 | 2021-03-26 | 中国航发西安动力控制科技有限公司 | Calibration equipment and calibration method for gas-liquid ratio tester |
| CN113236544A (en) * | 2021-04-25 | 2021-08-10 | 成都成航车辆仪表有限责任公司 | Function detection device for fuel booster pump of airplane |
| CN115900861A (en) * | 2023-03-13 | 2023-04-04 | 西安成立航空制造有限公司 | Aero-engine nozzle flow testing device and method |
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| US4206634A (en) * | 1978-09-06 | 1980-06-10 | Cummins Engine Company, Inc. | Test apparatus and method for an engine mounted fuel pump |
| JP2002106446A (en) * | 2000-07-28 | 2002-04-10 | Robert Bosch Gmbh | Driving method for fuel metering system of direct injection internal combustion engine, fuel metering system for direct injection internal combustion engine, direct injection internal combustion engine, control device for direct injection internal combustion engine and adjusting element of control device for direct injection internal combustion engine |
| CN1737524A (en) * | 2004-08-20 | 2006-02-22 | 天津市天派工业自动化技术有限公司 | Automobile automatic gear box key component oil pump experimental bench |
| CN2856465Y (en) * | 2005-07-22 | 2007-01-10 | 贺启宇 | Automatic detection test bed for oil jetting pump |
| CN201635898U (en) * | 2010-03-18 | 2010-11-17 | 上海航新航宇机械技术有限公司 | Function detection device for civil airplane fuel oil booster pumps |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US4206634A (en) * | 1978-09-06 | 1980-06-10 | Cummins Engine Company, Inc. | Test apparatus and method for an engine mounted fuel pump |
| JP2002106446A (en) * | 2000-07-28 | 2002-04-10 | Robert Bosch Gmbh | Driving method for fuel metering system of direct injection internal combustion engine, fuel metering system for direct injection internal combustion engine, direct injection internal combustion engine, control device for direct injection internal combustion engine and adjusting element of control device for direct injection internal combustion engine |
| CN1737524A (en) * | 2004-08-20 | 2006-02-22 | 天津市天派工业自动化技术有限公司 | Automobile automatic gear box key component oil pump experimental bench |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102996426A (en) * | 2012-11-19 | 2013-03-27 | 武汉航达航空科技发展有限公司 | Test system for main fuel pump of airplane |
| CN102996426B (en) * | 2012-11-19 | 2015-08-26 | 武汉航达航空科技发展有限公司 | Test system for main fuel pump of airplane |
| CN105020128A (en) * | 2015-07-06 | 2015-11-04 | 安徽精科检测技术有限公司 | Comprehensive performance test bed of fuel pumps |
| CN105781956A (en) * | 2016-01-13 | 2016-07-20 | 哈尔滨飞机工业集团有限责任公司 | Booster pump tester |
| CN108661837A (en) * | 2017-03-30 | 2018-10-16 | 中国船舶重工集团公司第七研究所 | Oil supply system |
| CN108661837B (en) * | 2017-03-30 | 2024-08-20 | 中国船舶集团有限公司第七一一研究所 | Oil supply system |
| CN109654528A (en) * | 2018-12-14 | 2019-04-19 | 重庆军通汽车有限责任公司 | A kind of fuel system of smoke generator |
| CN111232231A (en) * | 2020-02-06 | 2020-06-05 | 陈志霖 | Wing built-in aviation oil tank pressurizing device |
| CN112555140A (en) * | 2020-10-30 | 2021-03-26 | 中国航发西安动力控制科技有限公司 | Calibration equipment and calibration method for gas-liquid ratio tester |
| CN113236544A (en) * | 2021-04-25 | 2021-08-10 | 成都成航车辆仪表有限责任公司 | Function detection device for fuel booster pump of airplane |
| CN115900861A (en) * | 2023-03-13 | 2023-04-04 | 西安成立航空制造有限公司 | Aero-engine nozzle flow testing device and method |
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Application publication date: 20110921 |