CN213516303U - Aircraft fuel pump regulator test bench - Google Patents
Aircraft fuel pump regulator test bench Download PDFInfo
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- CN213516303U CN213516303U CN202022505356.4U CN202022505356U CN213516303U CN 213516303 U CN213516303 U CN 213516303U CN 202022505356 U CN202022505356 U CN 202022505356U CN 213516303 U CN213516303 U CN 213516303U
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Abstract
The utility model provides an aircraft fuel pump regulator test bench, including oil feeding system and oil return system, connect the fuel pump regulator of treating the experiment between oil feeding system and the oil return system, oil feeding system includes circulating oil tank and accuse pressure oil tank, accuse pressure oil tank external compressed air, circulating oil tank and accuse pressure oil tank separately arrange and communicate each other, set up the filter on the pipeline that gets into accuse pressure oil tank from circulating oil tank, the oil circuit that comes out from circulating oil tank supplies oil to the gear pump import of aircraft fuel pump regulator after passing through the heater heating, set up the heat exchanger on the oil return pipeline that gets back to circulating oil tank or accuse pressure oil tank; the oil return system comprises three oil return pipelines which are respectively a gear pump outlet pipeline, a guide outlet pipeline and a regulator outlet pipeline, and the three oil return pipelines are communicated with the circulating oil tank and the pressure control oil tank.
Description
Technical Field
The utility model relates to an aircraft engine technical field especially relates to an aircraft fuel pump regulator test bench.
Background
The fuel pump regulator is used for accurately controlling the fuel supply quantity of the combustion chamber of the aircraft engine, is a vital component in an aircraft engine system, and has the performance directly related to the performance of the aircraft engine. When the fuel pump regulator is designed and maintained for detection, the fuel pump regulator needs to be tested to verify whether the performance of the fuel pump regulator meets the requirements. In the prior art, a self-circulation filtering system of an aircraft fuel pump regulator test bed can only filter oil of a circulating oil tank, and cannot filter a pressure control oil tank, and the existing aircraft fuel pump regulator test bed adopts a heating mode that heat conduction oil is heated through a mold temperature controller, and then the heat conduction oil and fuel oil are heated in a heat exchange mode, wherein the heating mode firstly drives the heat conduction oil to be heated, and then the fuel oil is heated, so that energy waste can be caused.
To above problem, the utility model provides a can filter the aircraft fuel pump regulator test bench of the waste that reduces the energy to accuse pressure oil tank.
SUMMERY OF THE UTILITY MODEL
An embodiment of the utility model provides an aircraft fuel pump regulator test bench to solve the defect among the prior art problem.
In order to achieve the purpose, the utility model adopts the following technical scheme.
The utility model provides a following scheme:
an aircraft fuel pump regulator test stand comprising: the fuel pump regulator to be tested is connected between the oil supply system and the oil return system;
the oil supply system comprises a circulating oil tank and a pressure control oil tank, the pressure control oil tank is externally connected with compressed air, the circulating oil tank and the pressure control oil tank are separately arranged but are mutually communicated, a filter is arranged on a pipeline entering the pressure control oil tank from the circulating oil tank and is used for carrying out self-circulation filtration on oil liquid in the circulating oil tank and the pressure control oil tank, an oil way from the circulating oil tank is heated by a heater and then supplies oil to a gear pump inlet of an aircraft fuel pump regulator, and a heat exchanger is arranged on an oil return pipeline returning to the circulating oil tank or the pressure control oil tank and is used for cooling the oil;
the oil return system comprises three oil return pipelines which are respectively a gear pump outlet pipeline, a guide outlet pipeline and a regulator outlet pipeline, and the three oil return pipelines are communicated with a circulating oil tank and a pressure control oil tank.
Preferably, the pressure control oil tank is at a high level, and the circulating oil tank is at a low level.
Preferably, the pressure control oil tank and the circulating oil tank are made of stainless steel materials, and the pressure control oil tank and the circulating oil tank are of detachable closed structures.
Preferably, the circulating oil tank is provided with a temperature sensor, and the pressure control oil tank is provided with a liquid level sensor and a pressure sensor.
Preferably, the pressure control oil tank is designed and produced according to the national standard 150 steel pressure vessel standard, so that the upper limit of the inlet pressure of each stage of pump is more than or equal to 1 MPa.
Preferably, the oil supply pipeline is further provided with a booster pump, and the booster pump is connected with the heater in series and used as a circulating pump when the pipeline is preheated.
Preferably, the booster pump is driven by a variable frequency motor.
Preferably, the maximum range of the flow of the ejection outlet pipeline is 40-3100L/h, and the maximum range of the flow of the regulator outlet pipeline is 40-2180L/h.
Preferably, the injection outlet pipeline adopts two flowmeters connected in series, and the measuring ranges of the two flowmeters are respectively: 113.4-3510L/h and 40-684L/h.
Preferably, the outlet pipeline of the regulator is connected in series by two flowmeters, and the ranges of the two flowmeters are respectively: 113.4-3510L/h and 40-684L/h.
By the above technical scheme of the utility model, can see out, the utility model discloses an aircraft fuel pump regulator test bench can carry out the capability test to the aircraft fuel pump regulator of multiple model, both can realize testing the fuel pump regulator performance of aircraft turboshaft engine, can test the pump head performance of fuel pump regulator again, the jet orifice flowmeter of aircraft fuel pump regulator test bench both can measure the jet orifice flow when testing the fuel pump regulator, also can measure the oil return flow of gear pump when testing the pump head performance; the flow and pressure measuring range of the aircraft fuel pump regulator test bed is large, and the temperature control effect is stable; the test bed for the aircraft fuel pump regulator can save energy to a great extent, improve the regulation precision of oil supply pressure and prolong the service life.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
FIG. 1 is a schematic diagram of an aircraft fuel pump regulator test stand according to an embodiment of the present invention;
FIG. 2 is a schematic view showing the flow direction of the piping during self-circulation;
FIG. 3 is a schematic diagram of the system during operation of the booster pump;
FIG. 4 is a schematic view of the flow direction of the outlet conduits and the regulator outlet conduit;
FIG. 5 is a schematic diagram of a pipeline for measuring a large flow rate;
FIG. 6 is a schematic diagram of a pipeline for measuring small flow rates;
FIG. 7 is a schematic diagram of the flow direction of the piping during independent testing of the pump head;
fig. 8 is a schematic view of a pressure control oil tank.
Description of reference numerals:
1001-magnetic turning plate liquid level transducer
1002-pressure sensor
1003-pressure control oil tank
1004-welded ball valve
1005-circulation oil tank
1006-temperature sensor
1007-welding type ball valve
1008-pneumatic three-way ball valve
1009-booster pump
1010-explosion-proof heater
1011-filter
1012-overflow valve
1013-pressure sensor
1014-overflow valve
1015-temperature sensor
1016-pressure sensor
1017-nozzle
1018-temperature sensor
1019-pressure sensor
1020-pneumatic ball valve
1021-temperature sensor
1022-pressure sensor
1023-filter
1024-temperature sensor
1025-turbine flowmeter
1026-temperature sensor
1027 pressure sensor
1028-pneumatic ball valve
1029 relief valve
1030-three-way change valve
1031-simulation nozzle
1032-proportional flow regulating valve
1033-proportional flow regulating valve
1034-Filter
1035-temperature sensor
1036-turbine flowmeter
1037-turbine flowmeter
1038-pneumatic ball valve
1039-pneumatic ball valve
1040-turbine flowmeter
1041-pneumatic ball valve
1042-turbine flowmeter
1043-temperature sensor
1044-Filter
1045 proportional flow control valve
1046-proportional flow control valve
1047-simulation nozzle
1048-three-way change valve
1049-relief valve
1050-flow switch
1051-flow switch
1052-pressure sensor
1053-temperature sensor
1054-pressure sensor
1055-pressure sensor
1056-pressure sensor
1057-pressure sensor
1058-pressure sensor
1059-pressure sensor
1060-pressure sensor
1061-flow switch
1062-flow switch
1063-pneumatic control ball valve
1064-pneumatic control proportional overflow valve
1065-flow divider
1066-heat exchanger
1067-temperature sensor
1068-hand ball valve
1069-relief valve
1070-one-way valve
1071-Filter
1072-Filter
1073 Filter
1074 turbine pump
1075-hand operated ball valve
1076-welded ball valve
1077-welded ball valve
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below by referring to the drawings are exemplary only for explaining the present invention, and should not be construed as limiting the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. It will be understood that when an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may also be present. Further, "connected" or "coupled" as used herein may include wirelessly connected or coupled. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
For the convenience of understanding the embodiments of the present invention, the following description will be given by taking specific embodiments as examples with reference to the accompanying drawings, and the embodiments are not limited to the embodiments of the present invention.
Fig. 1 is a schematic structural diagram of an aircraft fuel pump regulator test stand according to an embodiment of the present invention, referring to fig. 1, the test stand includes: the fuel pump regulator to be tested is connected between the oil supply system and the oil return system.
The oil supply system includes: a circulating oil tank 1005 and a pressure control oil tank 1003, wherein the pressure control oil tank 1003 is arranged on the left side, and the circulating oil tank 1005 is arranged on the right side. The pressure control oil tank 1003 is externally connected with compressed air, the circulating oil tank 1005 and the pressure control oil tank 1003 are separately arranged but are communicated with each other, and the pressure oil tank can transmit pressure to the circulating oil tank 1005 during air pressurization. The pressure control oil tank 1003 is at a high position, the circulating oil tank 1005 is at a low position, the part participating in circulation in the whole test process is full of fuel, and the pressure control oil tank 1003 does not participate in circulation of an oil way in a normal working state. The heating and cooling of the oil circuit thus does not take into account the volume of the pressure-controlled oil tank. Therefore, the heating power of the heater can be greatly reduced, and the waste of energy is reduced; the accurate control of the oil return pressure can be realized through the interface A01 of the external compressed air of the pressure control oil tank 1003, and the oil return pressure is communicated with the atmosphere through a large-caliber shutoff valve, so that the rapid balance between the air pressure in the oil tank and the external air pressure is ensured. Fig. 8 is a schematic view of the pressure control oil tank, and referring to fig. 8, an a01 interface is located at the upper part of the pressure control oil tank 1003. When in use, air pressure enters the oil tank through the opening, thereby providing pressure for the oil tank.
The pipeline entering the pressure control oil tank 1003 from the circulating oil tank 1005 is provided with filters (1071, 1072 and 1073) for performing self-circulation filtration on oil of the circulating oil tank and the pressure control oil tank, and the oil supply system can realize self-circulation filtration on the oil in the oil tank, namely, when the system does not operate, the system has an independent circulation filtration function. The direction of the line flow during self-circulation is shown in FIG. 2.
The pressure control oil tank 1003 and the circulating oil tank 1005 are made of stainless steel materials, and the pressure control oil tank 1003 and the circulating oil tank 1005 are of detachable sealing structures and convenient to clean. The capacity of the oil tank fully considers the performance characteristics of the pump and a certain margin is left.
The oil supply system further includes: temperature sensors, pressure sensors and filters; an oil path from the circulating oil tank is heated by the explosion-proof heater 1010 and then supplies oil to an inlet of a gear pump of an aircraft fuel pump regulator, a heat exchanger 1066 is arranged on an oil return pipeline returning to the circulating oil tank or a pressure control oil tank and used for cooling oil, and meanwhile, the oil path is cooled by adopting a cooling water heat exchange mode and used for ensuring that the heating time of the fuel oil in the main oil tank from the room temperature to 100 ℃ is not more than 30 minutes, and the time of the fuel oil in the main oil tank from 100 ℃ to the room temperature is not more than 20 minutes.
The circulating oil tank 1005 is provided with a temperature sensor 1006, and the pressure control oil tank 1003 is provided with a magnetic flap liquid level transmitter 1001 (liquid level sensor) and a pressure sensor 1002. And the acquired data is uploaded to an interface of an upper computer for processing.
The pressure control oil tank 1003 is designed and produced according to the national standard 150 steel pressure container standard, so that the upper limit of the inlet pressure of each stage of pump is more than or equal to 1 MPa.
The fuel supply system provides fuel with stable pressure and flow for a fuel inlet of the fuel pump regulator, and the fuel supply temperature range is as follows: the temperature is controlled to be +/-3 ℃ at 20-100 ℃; the control range of the oil supply pressure is as follows: (-0.1-0.9) MPa is continuously adjustable; the oil supply flow is more than or equal to 6000L/h.
A booster pump 1009 is further arranged on the oil supply pipeline, the booster pump 1009 is connected in series with the heater 1010 and is used as a circulating pump when the pipeline is preheated before the test bench runs, and the system principle when the booster pump runs is shown in fig. 3.
The booster pump 1009 is driven by a variable frequency motor, and can reduce the overflow amount passing through the overflow valve to the maximum extent. Thereby saving energy to the maximum extent and increasing the service life of the booster pump 1009. In the actual use process, the rotating speed of the booster pump 1009 is adjusted according to the feedback value of the pressure sensor 1013 at the fuel inlet, so that the display value of the pressure transmitter is closer to the set value, and the adjustment precision of the fuel supply pressure is improved.
The oil return system comprises three oil return pipelines which are respectively a gear pump outlet pipeline, a guide ejection outlet pipeline and a regulator outlet pipeline, the flow of the three outlets is measured, the pressure of the guide ejection outlet and the pressure of the regulator outlet are regulated, and the three oil return pipelines are communicated with a circulating oil tank 1005 and a pressure control oil tank 1003. The oil return system comprises a nozzle, a filter, a pressure sensor, a flowmeter, a ball valve and a quick coupler;
the flow direction principle of the outlet pipes and the regulator outlet pipes is shown in fig. 4.
The maximum flow range of the outlet pipeline of the guide outlet is 40-3100L/h, and the maximum flow range of the outlet pipeline of the regulator is 40-2180L/h.
Because flow measurement demand scope is big, draw and penetrate the outlet pipeline and adopt two flowmeters to establish ties, two flowmeter ranges are respectively: 113.4-3510L/h, 40-684L/h; similarly, the outlet pipeline of the regulator adopts two flowmeters which are connected in series, and the measuring ranges of the two flowmeters are respectively as follows: 113.4-3510L/h and 40-684L/h. When measuring large flow, the pipeline principle is as shown in fig. 5, and the software interface displays the flow of the large-scale flowmeter. The pipeline principle when measuring small flows is shown in fig. 6, where the software interface displays the flow of the small range flow meter.
When the pump head of the fuel pump regulator needs to be independently tested, part of oil at the outlet of the gear stage of the pump needs to be led back to the inlet of the gear pump, and the other part of the oil returns to the oil tank. The flow direction principle of the pipeline is shown in figure 7.
In practical applications, the processing device may be disposed at other positions inside the test bed. The embodiment of the utility model provides an it is not restricted to above-mentioned processing apparatus's the concrete position of placing, and any mode of placing of above-mentioned processing apparatus in the test bench inside is all in the utility model discloses in the protection scope of the embodiment.
It will be appreciated by those skilled in the art that the number of various components shown in fig. 1 for simplicity only may be less than that in a practical test rig, but such omissions are clearly not to be considered as a prerequisite for a clear and complete disclosure of embodiments of the invention.
Those of ordinary skill in the art will understand that: the components in the devices in the embodiments may be distributed in the devices in the embodiments according to the description of the embodiments, or may be correspondingly changed in one or more devices different from the embodiments. The components of the above embodiments may be combined into one component, or may be further divided into a plurality of sub-components.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered by the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. An aircraft fuel pump regulator test stand, comprising: the fuel pump regulator to be tested is connected between the oil supply system and the oil return system;
the oil supply system comprises a circulating oil tank and a pressure control oil tank, the pressure control oil tank is externally connected with compressed air, the circulating oil tank and the pressure control oil tank are separately arranged but are mutually communicated, a filter is arranged on a pipeline entering the pressure control oil tank from the circulating oil tank and is used for carrying out self-circulation filtration on oil liquid in the circulating oil tank and the pressure control oil tank, an oil way from the circulating oil tank is heated by a heater and then supplies oil to a gear pump inlet of an aircraft fuel pump regulator, and a heat exchanger is arranged on an oil return pipeline returning to the circulating oil tank or the pressure control oil tank and is used for cooling the oil;
the oil return system comprises three oil return pipelines which are respectively a gear pump outlet pipeline, a guide outlet pipeline and a regulator outlet pipeline, and the three oil return pipelines are communicated with a circulating oil tank and a pressure control oil tank.
2. An aircraft fuel pump regulator test stand as claimed in claim 1, wherein said pressure control tank is in a high position and said circulating tank is in a low position.
3. An aircraft fuel pump regulator test stand as claimed in claim 1, wherein said pressure control fuel tank and said circulating fuel tank are stainless steel, and said pressure control fuel tank and said circulating fuel tank are removable enclosures.
4. An aircraft fuel pump regulator test stand as claimed in claim 1, wherein the circulating fuel tank is fitted with a temperature sensor, and the pressure control fuel tank is fitted with a level sensor and a pressure sensor.
5. An aircraft fuel pump regulator test stand according to claim 1, wherein the pressure control fuel tank is designed and produced according to the national standard 150 steel pressure vessel standard, so that the upper limit of the inlet pressure of each stage of pump is more than or equal to 1 MPa.
6. An aircraft fuel pump regulator test stand according to claim 1, wherein a booster pump is further provided on the oil supply system, the booster pump being connected in series with the heater for use as a circulation pump when preheating the pipeline.
7. An aircraft fuel pump regulator test stand as claimed in claim 6, wherein the booster pump is driven by a variable frequency motor.
8. The aircraft fuel pump regulator test stand of claim 1, wherein the maximum range of flow of the pilot outlet conduit is 40-3100L/h, and the maximum range of flow of the regulator outlet conduit is 40-2180L/h.
9. An aircraft fuel pump regulator test stand according to claim 1, wherein the outlet nozzle line employs two flow meters in series, the two flow meters respectively having: 113.4-3510L/h and 40-684L/h.
10. An aircraft fuel pump regulator test stand according to claim 1, wherein the regulator outlet line employs two flow meters in series, the two flow meters respectively having: 113.4-3510L/h and 40-684L/h.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022505356.4U CN213516303U (en) | 2020-11-03 | 2020-11-03 | Aircraft fuel pump regulator test bench |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022505356.4U CN213516303U (en) | 2020-11-03 | 2020-11-03 | Aircraft fuel pump regulator test bench |
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| Publication Number | Publication Date |
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| CN213516303U true CN213516303U (en) | 2021-06-22 |
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| CN202022505356.4U Active CN213516303U (en) | 2020-11-03 | 2020-11-03 | Aircraft fuel pump regulator test bench |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114278634A (en) * | 2021-12-16 | 2022-04-05 | 南京晨光集团有限责任公司 | High-temperature fuel servo flow metering characteristic test system |
| CN114526228A (en) * | 2022-02-18 | 2022-05-24 | 徐州圣邦机械有限公司 | Performance test bed and experimental method for internal gear pump |
-
2020
- 2020-11-03 CN CN202022505356.4U patent/CN213516303U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114278634A (en) * | 2021-12-16 | 2022-04-05 | 南京晨光集团有限责任公司 | High-temperature fuel servo flow metering characteristic test system |
| CN114278634B (en) * | 2021-12-16 | 2024-05-17 | 南京晨光集团有限责任公司 | High-temperature fuel servo flow metering characteristic test system |
| CN114526228A (en) * | 2022-02-18 | 2022-05-24 | 徐州圣邦机械有限公司 | Performance test bed and experimental method for internal gear pump |
| CN114526228B (en) * | 2022-02-18 | 2024-02-20 | 徐州圣邦机械有限公司 | Internal gear pump performance test bed and test method |
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