CN213684559U - Aircraft spout oil source pump test bench - Google Patents
Aircraft spout oil source pump test bench Download PDFInfo
- Publication number
- CN213684559U CN213684559U CN202022568994.0U CN202022568994U CN213684559U CN 213684559 U CN213684559 U CN 213684559U CN 202022568994 U CN202022568994 U CN 202022568994U CN 213684559 U CN213684559 U CN 213684559U
- Authority
- CN
- China
- Prior art keywords
- oil
- pressure
- pump
- control
- oil tank
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Abstract
The utility model provides an aircraft spout oil source pump test bench, its includes control oil system, oil feeding system and return oil system, its characterized in that: the control oil system provides the fuel of steady pressure and temperature for spout oil source pump plunger pump control mouth, oil feeding system provides the fuel of steady pressure and temperature for spout oil source pump centrifugal pump import, oil return system and centrifugal pump export, the plunger pump import, plunger pump export and plunger pump oil drain port are connected, wherein the control oil system includes circulating oil tank and accuse pressure oil tank, the external compressed air of accuse pressure oil tank, circulating oil tank and accuse pressure oil tank separately arrange but the two is UNICOM each other, the oil circuit that comes out from circulating oil tank divide into two the tunnel, let in oil feeding system all the way, another passway leads to the control mouth of plunger pump. The test bench can be used for carrying out performance test on the airplane nozzle oil source pumps of various models, and is convenient to operate and maintain in later period.
Description
Technical Field
The utility model relates to an aircraft components and parts field of making especially relates to an aircraft spout oil source pump test bench.
Background
The airplane nozzle oil source pump is a booster pump at the front stage of an airplane boosting system fuel regulator and can provide a high-pressure fuel oil source for airplane boosting. The nozzle oil source pump is a key component of an airplane boosting system, so that the nozzle oil source pump is required to be tested and the performance is verified when the nozzle oil source pump is designed and maintained and then detected.
SUMMERY OF THE UTILITY MODEL
In order to solve the problem, the utility model provides an aircraft spout oil source pump test bench.
The technical scheme of the utility model as follows:
an aircraft nozzle oil source pump test bed comprises a control oil system, an oil supply system and an oil return system, wherein the control oil system provides fuel oil with stable pressure and temperature for a nozzle oil source pump plunger pump control port, the oil supply system provides fuel oil with stable pressure and temperature for a nozzle oil source pump centrifugal pump inlet, the oil return system is connected with a centrifugal pump outlet, a plunger pump inlet, a plunger pump outlet and a plunger pump oil discharge port, the control oil 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, an oil path from the circulating oil tank is divided into two paths, one path is introduced into the oil supply system, and the other path is communicated with the control port of the plunger pump; the control oil system further comprises an oil supply pump, a pressure regulating valve, a safety valve, a filter, a pressure sensor and a temperature sensor, the oil supply system comprises a heater, a heat exchanger, an oil filter, the temperature sensor, the pressure sensor and a quick connector, and the oil return system comprises the pressure regulating valve, the safety valve, the filter, the pressure sensor, a flowmeter and the temperature sensor.
Preferably, the pressure control oil tank is arranged at a position higher than that of the circulation oil tank.
Preferably, the circulating oil tank is provided with a temperature sensor, the pressure control oil tank is provided with a liquid level sensor and a pressure sensor, and the sensors are in communication connection with an upper computer interface.
Preferably, the test bed adopts two modes of air pressurization and pump pressurization to regulate the inlet pressure of the centrifugal pump, and the oil supply system is provided with a three-way reversing valve and a booster pump; when the pump is used for pressurizing, the three-way reversing valve is used for reversing, the booster pump works, the pressure regulation is realized through the proportional flow regulating valve, and the heater is arranged at the outlet of the booster pump, so that the heating of the oil supply pressure can be realized; when the air is pressurized, the three-way reversing valve does not reverse, and at the moment, compressed air with required pressure is introduced into the pressure control oil tank, so that the pipeline pressurization is realized.
Preferably, the centrifugal pump and the plunger pump are provided with safety valves at the back of the outlet.
Preferably, one way of the oil return system connected with the oil discharge port of the plunger pump is an oil discharge system, and the oil discharge system comprises a pressure regulating valve, a sampling port, a filter, a temperature sensor, a pressure sensor, a flowmeter and a safety valve.
The utility model discloses an aircraft spout oil source pump class test bench, its integrated degree is high, and flow and pressure's measuring range is big, can provide the medium of super wide temperature range, can carry out the capability test to the aircraft spout oil source pump of multiple model, and it is convenient to be equipped with operation and later maintenance.
Drawings
Fig. 1 and 2 are schematic structural diagrams of an aircraft nozzle oil source pump test stand according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of pump pressurization;
FIG. 4 is a schematic view of gas pressurization.
In the figure:
1001-liquid level transducer
1002-pressure transmitter
1003-pressure measuring joint
1004-needle valve
1005-pressure control oil tank
1006-stainless steel ball valve
1007-circulation oil tank
1008-temperature sensor
1009-stainless steel ball valve
1010-plate heat exchanger
1011-plunger pump
1012-pneumatic control proportional overflow valve
1013-silencer
1014-Filter
1015-relief valve
1016-pressure transmitter
1017-temperature sensor
1018-temperature sensor
1019-temperature sensor
1020 pressure transmitter
1021-pressure transmitter
1022-safety valve
1023-Siemens electric control valve
1024-siemens electric regulating valve
1025-Filter
1026-turbine flowmeter
1027-Filter
1028-turbine flowmeter
1029 relief valve
1030-pressure transmitter
1031-pressure transmitter
1032-turbine flowmeter
1033-Siemens electric regulating valve
1034 relief valve
1035-turbine flowmeter
1036-filter
1037-temperature sensor
1038-pressure transmitter
1039-turbine flowmeter
1040-flowmeter
1041-three-way change valve
1042-overflow valve
1043-Filter
1044-pneumatic cut-off valve
1045-heater
1046 electric siemens adjusting valve
1047 centrifugal pump
1048-pneumatic three-way change valve
1049-oppositely clamped flange stainless steel ball valve
1050-heat exchanger
1051-hand operated 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.
As shown in FIG. 1, the utility model discloses an aircraft spout oil source pump test bench includes control oil system, oil feeding system and oil return system. The oil supply system provides fuel oil with stable pressure and temperature for a centrifugal inlet of the nozzle oil source pump and comprises a heater, a heat exchanger, an oil filter, a temperature sensor, a pressure sensor, a quick connector and other components.
Oil supply temperature range: (-40-140) DEG C, and the control precision is +/-3 ℃; in order to realize the control of low temperature of 40 ℃ below zero, the oil return pipeline is provided with a heat exchanger, refrigeration is realized through a liquid nitrogen tank, and the refrigeration temperature is realized by controlling the on-off mode of the liquid nitrogen tank and the heat exchanger. The high-temperature fuel oil is directly heated by the pipeline heater.
Adjustable pressure range of the inlet: (-0.1 to 0.5) MPa. The system pressure supply adopts two modes, one mode is air pressure boost, and the other mode is pump pressure boost. The pump pressurization can only realize positive pressure pressurization, and the negative pressure can only be realized through a pneumatic pressurization mode. When the pump is pressurized, the pressure of the oil return pipeline is basically 0, and when the pump is pressurized, the pressure of the oil return pipeline and the pressure of oil supply are completely the same due to the communication of the pipelines. The selection of air pressurization and pump pressurization is realized by a three-way reversing valve.
The utility model discloses in adopted two oil tanks, the left side is accuse pressure oil tank 1001, and the right side is circulating oil tank 1007. The circulating oil tank 1007 and the pressure control oil tank 1001 are made of stainless steel materials; the capacity of the oil tank fully considers the performance characteristics of the pump and a certain margin is left. Two oil tanks all adopt enclosed construction, but can dismantle and be convenient for wash. The pressure control oil tank is communicated with compressed air through an A1 port; the circulating oil tank 1007 and the pressure control oil tank 1001 are separately arranged but communicated with each other, so that the pressure control oil tank can transmit pressure to the circulating oil tank 1007 when the air is pressurized. The pressure control oil tank 1001 is at a high position, the circulating oil tank 1007 is at a low position, the part participating in circulation in the whole test process is ensured to be filled with fuel, and the pressure control oil tank 1001 does not participate in circulation of the oil line under a normal working state, so that the volume of the pressure control oil tank is not considered for heating and cooling the oil line. By the design, the heating and refrigerating power of the mold temperature controller can be greatly reduced, so that the waste of energy is reduced; the accurate control of the oil return pressure can be realized through an A1 port; the port A1 can be communicated with atmosphere through a large-caliber shutoff valve to ensure that the air pressure in the oil tank is rapidly balanced with the external air pressure.
The circulating oil tank 1007 is provided with a temperature sensor, the pressure control oil tank 1001 is provided with a liquid level sensor and a pressure sensor, and the data are collected into an upper computer interface. The pressure control oil tank is designed and produced according to the standard of a national standard 150 steel pressure container due to the existence of gas, and the upper limit of the inlet pressure of each stage of pump is ensured: not less than 0.5MPa (relative pressure).
When the pump is pressurized, the three-way reversing valve 1048 reverses, the centrifugal pump 1047 works, pressure regulation is realized through the Siemens electric regulating valve 1046, and the outlet of the centrifugal pump is provided with the heater 1045, so that heating of oil supply pressure can be realized. When the pressure is increased, the pneumatic three-way reversing valve 1048 does not reverse, and at this time, compressed air with required pressure is introduced into the pressure control oil tank 1005, so that the pipeline pressure increase is realized.
The control oil system provides fuel oil with stable pressure for a control cavity of the nozzle oil source pump. The device consists of a control oil tank, an oil supply pump, a pressure regulating valve, a safety valve, a filter, a pressure sensor, a temperature sensor and other components. The control oil system is provided with a die temperature controller and a heat exchanger, so that the automatic control of the fuel oil temperature can be realized, and the fuel oil temperature is kept at 25 +/-5 ℃; the distance between the installation position of the temperature sensor and the outlet position of the tested product is less than or equal to 150mm, the measurement range is (-55-150) DEG C, and the measurement precision is as follows: 1 ℃ C. Controlling the oil pressure to be within the range of (0-12) +/-0.05 MPa to realize automatic control; the pressure sensor has a measuring range (0-15) MPa, and the measuring precision is 0.1 grade; the control oil system is provided with a safety valve; the control oil system has fuel oil pressurization capacity and booster pump flow rate 1680L/h.
The oil return system is used for establishing outlet pressure of tested products and metering corresponding flow, pressure and temperature. The oil return system is composed of high and low temperature resistant components such as a pressure regulating valve, a safety valve, a filter, a pressure sensor, a flowmeter, a temperature sensor and the like.
The pressure regulating valve at the outlet of the centrifugal pump can realize continuous adjustment of the pressure difference range (0.64-1.1) MPa of the inlet and the outlet, and the control precision is 0.01 MPa; the pressure regulating valve of the outlet of the plunger pump can realize the stepless regulation of outlet flow (0-12000) L/h and the stepless regulation of outlet pressure (1-22) MPa, and the outlet pressure fluctuation is less than or equal to +/-5 percent; the outlet pressure regulating valve is an electric regulating valve with high and low temperature resistance, high pressure resistance and high precision of Siemens. The working range of (0-24) MPa is in the linear working range of the valve. Each electric component of electric pressure regulating valve all possesses explosion-proof or flame proof measure, and plunger pump export pressure regulating valve quantity: one for use and one for standby;
safety valves are arranged behind the outlet of the centrifugal pump and the outlet of the plunger pump, and the opening pressures of the safety valves are respectively 2MPa and 29 MPa;
the position of the pressure measuring point is less than or equal to 150mm away from the outlet of the tested product, the pressure measuring point is provided with two pressure sensors, the measuring ranges are (0-30) MPa and (0-2) MPa respectively, and the measuring precision is 0.1 grade;
the outlet flowmeter of the centrifugal pump is positioned at the downstream of the filter, is easy to disassemble, adopts a conical surface sealing connection mode, has the metering range of (147.6-21576) L/h and the measurement precision of 0.5 grade;
the outlet flowmeter of the plunger pump is positioned at the downstream of the filter, is easy to disassemble, adopts a conical surface sealing connection mode, has the metering range of (147.6-21576) L/h and the measuring precision of 0.5 grade;
the oil discharge system can realize the oil discharge function of the oil discharge port of the tested product, establish the pressure of the oil discharge port and measure the corresponding flow, temperature and pressure. The device consists of a pressure regulating valve, a sampling port, a filter, a temperature sensor, a pressure sensor, a flowmeter, a safety valve and other components.
In the range of oil discharge flow (100-2000) L/h, the oil discharge pressure is continuously adjustable in the range of (0.04-0.6) MPa, and the control precision is +/-0.01 MPa; the opening pressure of the safety valve is 0.7 MPa; the distance between the installation position of the temperature sensor and the outlet position of the tested product is less than or equal to 150mm, the measurement range is (-55-150) DEG C, and the measurement precision is as follows: 1 ℃ C. The position of the pressure measuring point is less than or equal to 150mm away from the outlet of the tested product, the measuring range (0-1) MPa of the pressure sensor is obtained, and the measuring precision is 0.1 level; the oil discharge system flowmeter is positioned at the downstream of the filter and is easy to disassemble, a plane sealing connection mode is adopted, the metering range is (90.6-2157) L/h, and the measurement precision is 0.5 grade; the control oil system is provided with a sampling port, so that the oil cleanliness can be conveniently sampled and detected.
Although the embodiments of the present invention have been described in detail, it will be understood by those skilled in the art that the present invention is not limited to the embodiments disclosed, and that various changes, modifications and substitutions can be made therein by those skilled in the art without departing from the scope of the present invention as defined by the appended claims.
Claims (6)
1. The utility model provides an aircraft spout oil source pump test bench, its includes control oil system, oil feeding system and return oil system, its characterized in that: the control oil system provides fuel oil with stable pressure and temperature for a nozzle oil source pump plunger pump control port, the oil supply system provides fuel oil with stable pressure and temperature for a nozzle oil source pump centrifugal pump inlet, and the oil return system is connected with a centrifugal pump outlet, a plunger pump inlet, a plunger pump outlet and a plunger pump oil discharge port; the control oil system further comprises an oil supply pump, a pressure regulating valve, a safety valve, a filter, a pressure sensor and a temperature sensor, the oil supply system comprises a heater, a heat exchanger, an oil filter, the temperature sensor, the pressure sensor and a quick connector, and the oil return system comprises the pressure regulating valve, the safety valve, the filter, the pressure sensor, a flowmeter and the temperature sensor.
2. The aircraft nozzle oil source pump test stand of claim 1, wherein the pressure control oil tank is disposed at a position higher than that of the circulation oil tank.
3. The aircraft nozzle oil source pump test bed according to claim 1, wherein the circulating oil tank is provided with a temperature sensor, the pressure control oil tank is provided with a liquid level sensor and a pressure sensor, and the sensors are in communication connection with an upper computer interface.
4. The aircraft nozzle oil source pump test stand of claim 1, wherein a relief valve is provided after each of the centrifugal pump and the plunger pump outlet.
5. The aircraft nozzle oil source pump test bed of claim 1, wherein one way of the oil return system connected with the plunger pump oil discharge port is an oil discharge system, and the oil discharge system comprises a pressure regulating valve, a sampling port, a filter, a temperature sensor, a pressure sensor, a flow meter and a safety valve.
6. The aircraft nozzle oil source pump test bed according to any one of claims 1 to 5, wherein the test bed adjusts the inlet pressure of a centrifugal pump by adopting two modes of air pressurization and pump pressurization, and a three-way reversing valve and a booster pump are arranged on the oil supply system; when the pump is used for pressurizing, the three-way reversing valve is used for reversing, the booster pump works, the pressure regulation is realized through the proportional flow regulating valve, and the heater is arranged at the outlet of the booster pump, so that the heating of the oil supply pressure can be realized; when the air is pressurized, the three-way reversing valve does not reverse, and at the moment, compressed air with required pressure is introduced into the pressure control oil tank, so that the pipeline pressurization is realized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022568994.0U CN213684559U (en) | 2020-11-09 | 2020-11-09 | Aircraft spout oil source pump test bench |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022568994.0U CN213684559U (en) | 2020-11-09 | 2020-11-09 | Aircraft spout oil source pump test bench |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213684559U true CN213684559U (en) | 2021-07-13 |
Family
ID=76729924
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022568994.0U Active CN213684559U (en) | 2020-11-09 | 2020-11-09 | Aircraft spout oil source pump test bench |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213684559U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114017305A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for detecting performance of oil source pump of aircraft engine |
-
2020
- 2020-11-09 CN CN202022568994.0U patent/CN213684559U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114017305A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for detecting performance of oil source pump of aircraft engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN211292297U (en) | Positive and negative pressure comprehensive test system | |
| CN107067918A (en) | The helium experimental loop device of fusion reactor | |
| CN213684559U (en) | Aircraft spout oil source pump test bench | |
| CN106523916A (en) | High-flow liquid medium combined supply system | |
| CN109557963A (en) | A kind of industry simulation test control system that can be precisely controlled flow and temperature | |
| CN213516303U (en) | Aircraft fuel pump regulator test bench | |
| CN204386715U (en) | For the thermostatically-controlled equipment of engine coolant | |
| CN108021159B (en) | Crystallization kettle temperature control system and control method | |
| CN110007702B (en) | High-pressure and automatic-control aviation fuel test bed oil supply system | |
| CN110823487B (en) | Multifunctional adjustable pressure test system | |
| CN110259765B (en) | Visual experiment table for hydraulic valve performance detection | |
| CN216894852U (en) | Experimental device for general type measures aviation fuel pump flow resistance characteristic | |
| CN110793599A (en) | High-pressure high-low temperature fuel flow measuring system | |
| CN212717420U (en) | EH oil supply device | |
| CN206221985U (en) | A kind of liquefied natural gas gasifying pressure regulation metering system | |
| CN213331489U (en) | Aircraft lubricating oil pump test bench | |
| CN104454119A (en) | Constant-temperature control device for engine cooling liquid and control method of constant-temperature control device | |
| CN115266116A (en) | Aircraft engine fuel oil feeding system | |
| CN209215967U (en) | A kind of industry simulation test control system that can be precisely controlled flow and temperature | |
| CN209892339U (en) | External lubricating oil tank and external lubricating oil cooling device of aircraft engine | |
| CN211085963U (en) | Internal pressure creep test system | |
| CN114088168A (en) | Liquid hydrogen pump driven mass method liquid hydrogen flow standard device | |
| CN111896237A (en) | Gas turbine fuel nozzle and blade integrated gas flow detection device | |
| CN110887683A (en) | Electrical heating type supersonic velocity ejector experiment system | |
| CN214954722U (en) | Air pressure adjusting device capable of measuring air flow |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230809 Address after: 101300 Building 5, No. 35, Juyuan East Road, Shunyi District, Beijing Patentee after: Beijing Hangshun Teda Technology Development Co.,Ltd. Address before: 101300 4 Juyuan East Road, Mapo Town, Shunyi District, Beijing Patentee before: BEIJING CRONDA AVIATION TECHNOLOGY Corp.,Ltd. |
|
| TR01 | Transfer of patent right |