CN110939495A - Aviation piston engine lubricating oil pre-filling device and using method thereof - Google Patents
Aviation piston engine lubricating oil pre-filling device and using method thereof Download PDFInfo
- Publication number
- CN110939495A CN110939495A CN201911221913.5A CN201911221913A CN110939495A CN 110939495 A CN110939495 A CN 110939495A CN 201911221913 A CN201911221913 A CN 201911221913A CN 110939495 A CN110939495 A CN 110939495A
- Authority
- CN
- China
- Prior art keywords
- oil
- stainless steel
- port
- oil tank
- pipeline
- 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.)
- Pending
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
- F01M11/00—Component parts, details or accessories, not provided for in, or of interest apart from, groups F01M1/00 - F01M9/00
- F01M11/04—Filling or draining lubricant of or from machines or engines
- F01M11/0458—Lubricant filling and draining
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
- F01M11/00—Component parts, details or accessories, not provided for in, or of interest apart from, groups F01M1/00 - F01M9/00
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
- F01M11/00—Component parts, details or accessories, not provided for in, or of interest apart from, groups F01M1/00 - F01M9/00
- F01M11/03—Mounting or connecting of lubricant purifying means relative to the machine or engine; Details of lubricant purifying means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
- F01M11/00—Component parts, details or accessories, not provided for in, or of interest apart from, groups F01M1/00 - F01M9/00
- F01M11/10—Indicating devices; Other safety devices
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a lubricating oil pre-filling device for an aviation piston engine. It comprises a stainless steel oil tank; the method is characterized in that: the electric heating device also comprises a trolley, an electric heater, a motor, a gear pump, an electromagnetic reversing valve and a communicating pipeline; the motor, the gear pump and the electromagnetic reversing valve are all arranged on the trolley; the electric heater is positioned in the stainless steel oil tank; the motor is connected with the gear pump; the gear pump is communicated with the stainless steel oil tank through a communication pipeline; the electromagnetic directional valve is respectively communicated with the gear pump and the stainless steel oil tank through a communicating pipeline. The invention has the advantages of detecting whether the oil passage in the engine is blocked or not and providing sufficient lubrication for each part in the engine when the engine is started for the first time. The invention also discloses a use method of the aviation piston engine lubricating oil pre-filling device.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a lubricating oil pre-filling device for an aviation piston engine. The invention also relates to a using method of the aviation piston engine lubricating oil pre-filling device.
Background
After the aviation piston engine is assembled, the aviation piston engine needs to be subjected to test run. To avoid excessive wear of engine components due to lack of lubrication during initial start-up, a layer of lubricating oil is applied to the mating surfaces of the components during engine assembly. However, in the actual working process, it is found that since the internal oil passage of the engine is filled with air and has no lubricating oil just after the engine is repaired, the time required for conveying the lubricating oil in the oil pan to each component of the engine through the internal oil passage after the lubricating oil is pressurized by the lubricating oil pump is long, about 10 to 20 seconds, and the lubricating oil smeared on the matching surface of each component during assembly is consumed within 2 to 3 seconds after the engine is started. Thus, the components are in a state of lack of lubrication for at least about 7 seconds, during which time the components may wear excessively. And when the engine is subjected to the first test run, a large amount of fine metal chips are found in the lubricating oil filter by checking the lubricating oil filter.
The lack of lubrication during initial engine start can reduce the useful life of certain engine components, such as the camshaft, the tappet body, the crankshaft bushing, etc. And metal chips generated by abrasion can block an oil passage in the engine, and in turn, some positions of the engine are lack of lubrication, so that vicious circle is formed, and the performance and the service life of the engine are seriously influenced.
Therefore, there is a need to develop a device that can detect whether the internal oil passage of the engine is blocked and can provide sufficient lubrication to the mating surfaces of the various components in the engine when the engine is started for the first time.
Disclosure of Invention
The invention aims to provide the lubricating oil pre-filling device of the aviation piston engine, which has a safe and reliable structure and is easy to disassemble, assemble and maintain; the device can fill lubricating oil into the engine through the oil duct process holes (namely oil duct oil filling holes) of the engine when the engine is not started, exhaust air in each oil duct, detect whether the oil duct in the engine is blocked or not, and provide sufficient lubrication for the matching surfaces of all parts in the engine when the engine is started for the first time; and the problem that parts are damaged due to lack of lubrication during initial starting of the engine is avoided.
The second purpose of the invention is to provide a using method of the aviation piston engine lubricating oil pre-filling device; the temperature, the pressure and the flow of the lubricating oil during the normal operation of the engine can be simulated, so that the oil duct in the engine is full of the lubricating oil, whether the oil duct in the engine is blocked or not can be detected, and sufficient lubrication can be provided for each part in the engine when the engine is started for the first time.
In order to achieve the first object of the present invention, the technical solution of the present invention is: the aviation piston engine lubricating oil pre-filling device comprises a stainless steel oil tank; the method is characterized in that: the electric heating device also comprises a trolley, an electric heater, a motor, a gear pump, an electromagnetic reversing valve and a communicating pipeline; the motor, the gear pump and the electromagnetic reversing valve are all arranged on the trolley;
the electric heater is positioned in the stainless steel oil tank;
the motor is connected with the gear pump;
the gear pump is communicated with the stainless steel oil tank through a communication pipeline;
the electromagnetic directional valve is respectively communicated with the gear pump and the stainless steel oil tank through a communicating pipeline.
In the technical scheme, the stainless steel oil tank comprises a first stainless steel oil tank for filling lubricating oil and a second stainless steel oil tank for storing and heating anti-corrosion oil;
the first stainless steel oil tank and the second stainless steel oil tank are both arranged on the trolley.
In the above technical solution, the communication pipeline includes a first communication pipeline, a second communication pipeline and a third communication pipeline;
the two ends of the first communicating pipeline are positioned in the first stainless steel oil tank and are respectively positioned at the two sides of the first stainless steel oil tank, and the middle part of the first communicating pipeline is sequentially connected with the gear pump and the electromagnetic directional valve in series;
the second communication pipeline is arranged on the first communication pipeline and is positioned between the gear pump and the electromagnetic directional valve;
the third communicating pipeline is arranged on the first communicating pipeline, one end of the third communicating pipeline is connected to the gear pump and the communicating pipeline between the electromagnetic directional valves, and the other end of the third communicating pipeline is connected to the electromagnetic directional valves and the communicating pipeline between the first stainless steel oil tanks.
In the technical scheme, the device also comprises a pressure gauge switch and a stainless steel high-temperature-resistant pressure gauge;
the pressure gauge switch and the stainless steel high-temperature-resistant pressure gauge are both arranged on the second communicating pipeline.
In the technical scheme, the device further comprises a pipeline filter and a superposition type one-way valve;
the pipeline filter and the superposed one-way valve are sequentially arranged on the first communication pipeline and are both positioned between the gear pump and the electromagnetic reversing valve;
one end of the second communicating pipeline is connected to the communicating pipeline between the gear pump and the pipeline filter, and the other end of the second communicating pipeline is connected to the superposed one-way valve and the communicating pipeline between the electromagnetic reversing valves.
In the technical scheme, the device also comprises a liquid level thermometer, an oil absorption filter, an air filter, a temperature sensor, an overflow valve, a heat insulation protection plate and a hose of an oil outlet of the pump;
the overflow valve is arranged on the third communicating pipeline;
the liquid level thermometer of the trolley is arranged on the side wall of the first stainless steel oil tank;
the oil suction filter is positioned in the first stainless steel oil tank and is positioned at the lubricating oil inlet end of the first communication pipeline;
the air filter is positioned on the first stainless steel oil tank;
the temperature sensor is positioned at the bottom end of the first stainless steel oil tank;
one end of a hose of an oil outlet of the pump is connected with the electromagnetic directional valve;
the heat insulation protection plate is arranged on the outer side of the first stainless steel oil tank.
In the above technical solution, the electromagnetic directional valve includes an opening a, an opening B, an opening P and an opening T; the port A and the port B are arranged on one side of the electromagnetic directional valve at intervals, and the port P and the port T are arranged on the other side of the electromagnetic directional valve at intervals;
one end of the hose of the oil outlet of the pump is detachably connected with the port A;
the port P and the port T are both positioned on the first communication pipeline; the port P and the port T are in a normally open state.
In the technical scheme, the device further comprises an operating bench; the operating rack is fixed on the trolley and is positioned between the first stainless steel oil tank and the second stainless steel oil tank;
an oil absorption filter and an electric heater are arranged in the second stainless steel oil tank; a liquid level thermometer is arranged on the side wall of the second stainless steel oil tank; an air filter is arranged at the upper part of the second stainless steel oil tank and is communicated with the second stainless steel oil tank;
a temperature sensor is arranged on the side wall of the second stainless steel oil tank;
the gear pump is located on the operating bench.
In order to achieve the second object of the present invention, the technical solution of the present invention is: the application method of the aviation piston engine lubricating oil pre-filling device is characterized in that: comprises the following steps of (a) carrying out,
an oil duct oil filling port is arranged on the engine; the oil passage oil filling port comprises a first oil passage oil filling port and a second oil passage oil filling port;
the first oil passage oil filling port and the second oil passage oil filling port are correspondingly arranged on two sides of the engine;
one end of a pump oil outlet hose is detachably connected with the port A, and the other end of the pump oil outlet hose is detachably connected with the first oil duct oil filling port or the second oil duct oil filling port;
the method comprises the following steps: supplying power to an aviation piston engine lubricating oil pre-filling device: AC 380V (voltage is 380V of alternating current), 50Hz (current changes 50 times/second);
step two: after no alarm signal is confirmed, pressing down a lubricating oil heating button to heat the lubricating oil in the first stainless steel oil tank (16.1) to 70 ℃;
when the temperature of the lubricating oil reaches 70 ℃, the electric heater is automatically powered off;
step three: adjusting the oiling pressure to 90 psi;
when the stainless steel high-temperature-resistant pressure gauge displays that the oil injection pressure reaches 90psi, the switch of the pressure gauge is automatically closed;
step four: when the P port and the T port of the electromagnetic directional valve are in a communicated state, the gear pump works to enable the lubricating oil in the first stainless steel oil tank to be internally circulated, so that the lubricating oil in the first stainless steel oil tank is uniformly heated;
step five: when the oil temperature reaches 70 ℃ and the oil injection pressure reaches 90psi, an oil outlet button is pressed, the electromagnetic directional valve is reversed to enable the port P to be communicated with the port A, and the heated lubricating oil is injected into the first oil channel oil injection port or the second oil channel oil injection port through the pump oil outlet hose through the port A;
when lubricating oil uniformly flows out from the second oil passage oil filling port or the first oil passage oil filling port, oil filling is stopped, the oil passages in the engine are not blocked, and the lubricating oil is filled in all the oil passages in the engine;
and when no lubricating oil flows out from the second oil passage oil filling port or the first oil passage oil filling port or only a small amount of lubricating oil flows out from the first oil passage oil filling port, whether the internal oil passage of the engine is blocked is checked.
In the above technical solution, in the fourth step, the internal circulation of the lubricant in the first stainless steel oil tank specifically comprises: the gear pump sucks the lubricating oil out of one side in the first stainless steel oil tank, and the lubricating oil returns to the other side of the first stainless steel oil tank after passing through a port P of the electromagnetic directional valve to a port T.
The invention has the following advantages:
(1) the invention is used for detecting whether all oil passages in the engine are blocked before the engine is started so as to avoid great loss caused by trial run when the oil passages are blocked;
(2) before the engine is started, the internal oil duct of the engine is filled with lubricating oil; the excessive abrasion of the inner part in the initial running stage is avoided;
(3) the invention is provided with the oil filter (such as an oil absorption filter), so that impurities in lubricating oil can be prevented from entering the engine to influence the use effect of the engine;
(4) the invention is provided with the heat insulation protection plate, so that the safety is high; the scalding of workers can be avoided;
(5) the invention heats the lubricating oil in the oil tank to a specified temperature, after the maximum pressure is adjusted, the electric pump and the electromagnetic valve are started, the lubricating oil is injected into the engine from the oil duct process hole at one end of the engine, and the oil duct in the engine is filled with the lubricating oil, so that whether the oil duct of the engine is blocked is checked, and each part in the engine can be fully lubricated, and the parts are ensured not to be excessively worn when the engine is started for the first time; the invention can prolong the service life of the engine and improve the overall performance of the engine;
(6) the oil tank is provided with the second stainless steel oil tank which is used for storing and heating the anti-corrosion oil and has a closed structure, the oil tank can heat the anti-corrosion oil to ensure that the anti-corrosion oil has good fluidity, and is convenient to subsequently spray the anti-corrosion oil into an engine cylinder by adopting compressed nitrogen, so that the operation is simple and convenient, the structure is compact, the space is saved, and the working efficiency is improved; the defects that the heating device is arranged in an open container filled with the anti-corrosion oil, the operation is complex and the anti-corrosion oil is easily polluted in the prior art are overcome;
(7) the lubricating device is high in applicability, is suitable for lubricating and detecting an aviation piston engine, and is convenient for lubricating and detecting the engine which is subjected to first trial run after overhaul; the defects that in the prior art, the service life of certain parts of the engine, such as a camshaft, a tappet body, a crankshaft bearing bush and the like, is shortened due to lack of lubrication during the initial starting of the engine, and metal chips generated by abrasion block oil passages in the engine, so that certain positions of the engine lack of lubrication, a vicious circle is formed, and the performance and the service life of the engine are seriously influenced are overcome.
Drawings
Fig. 1 is a schematic diagram of the filling principle of the invention.
Fig. 2 is an exploded view of an engine employing the lubrication and testing of the present invention.
Fig. 3 is a schematic front view of the present invention.
FIG. 4 is a schematic top view of the present invention.
FIG. 5 is a schematic side view of the present invention.
FIG. 2 is a view for illustrating a port of an oil passage through which oil is injected into an engine and a port of another oil passage through which the presence or absence of outflow of oil is observed; if the first oil passage oil filling port of the engine is used for filling oil by adopting the invention, and the second oil passage oil filling port is used for observing whether lubricating oil flows out or not, the engine can be lubricated and detected.
In fig. 1, a denotes a port a of the electromagnetic directional valve; b represents a port B of the electromagnetic directional valve; p represents a port P of the electromagnetic directional valve; t denotes a T port of the electromagnetic directional valve.
In the figure, 1-a liquid level thermometer, 2-a trolley, 3-an oil absorption filter, 4-an air filter, 5-an electric heater, 6-a temperature sensor, 7-a motor, 8-a gear pump, 9-a pipeline filter, 10-a superposition type one-way valve, 11-a pressure gauge switch, 12-a stainless steel high temperature resistant pressure gauge, 13-an overflow valve, 14-an electromagnetic directional valve, 15-a heat insulation protection plate, 16-a stainless steel oil tank, 16.1-a first stainless steel oil tank, 16.2-a second stainless steel oil tank, 17-an oil channel oil filling port, 17.1-a first oil channel oil filling port, 17.2-a second oil channel oil filling port, 18-a communication pipeline, 18.1-a first communication pipeline, 18.2-a second communication pipeline, 18.3-a third communication pipeline, 19-a pump-out hose, 20-engine, 21-operation bench.
Detailed Description
The embodiments of the present invention will be described in detail with reference to the accompanying drawings, which are not intended to limit the present invention, but are merely exemplary. While the advantages of the invention will be clear and readily understood by the description.
With reference to the accompanying drawings: the aviation piston engine lubricating oil pre-filling device comprises a stainless steel oil tank 16; the electric heating trolley further comprises a trolley 2, an electric heater 5, a motor 7, a gear pump 8, an electromagnetic directional valve 14 and a communicating pipeline 18;
the motor 7, the gear pump 8 and the electromagnetic directional valve 14 are all arranged on the trolley 2; the electric heater 5 is positioned in the stainless steel oil tank 16, and the electric heater 5 is used for heating the lubricating oil in the stainless steel oil tank 16; when heating the oil, the required oil temperature can be set;
the motor 7 is connected with the gear pump 8, and the motor 7 provides power for the gear pump 8;
the gear pump 8 is communicated with the stainless steel oil tank 16 through a communication pipeline, and the gear pump 8 sucks lubricating oil out of the stainless steel oil tank 16;
the electromagnetic directional valve 14 is respectively communicated with the gear pump 8 and the stainless steel oil tank 16 through communication pipelines (as shown in fig. 1, 3, 4 and 5); the electromagnetic directional valve 14 is used for adjusting the trend of the lubricating oil in the stainless steel oil tank 16 in the pre-filling device.
Further, the stainless steel oil tank 16 comprises a first stainless steel oil tank 16.1 and a second stainless steel oil tank 16.2; the first stainless steel oil tank 16.1 is used for filling lubricating oil; the second stainless steel oil tank 16.2 can heat the anti-corrosive oil to ensure that the anti-corrosive oil has good fluidity, so that the anti-corrosive oil can be conveniently sprayed into an engine cylinder by compressed nitrogen in the follow-up process.
Further, the communication line 18 comprises a first communication line 18.1, a second communication line 18.2 and a third communication line 18.3;
the two ends of the first communication pipeline 18.1 are both positioned in the first stainless steel oil tank 16.1 and are respectively positioned at the two sides of the first stainless steel oil tank 16.1, and the middle part of the first communication pipeline is sequentially connected with the gear pump 8 and the electromagnetic directional valve 14 in series; the first communication pipeline 18.1 provides a path for internal circulation of lubricating oil in the first stainless steel oil tank 16.1;
the second communication pipeline 18.2 is arranged on the first communication pipeline 18.1 and is positioned between the gear pump 8 and the electromagnetic directional valve 14; the second communication duct 18.2 provides a path for adjusting the filling pressure;
the third communicating pipeline 18.3 is arranged on the first communicating pipeline 18.1, one end of the third communicating pipeline is connected to the communicating pipeline between the gear pump 8 and the electromagnetic directional valve 14, and the other end of the third communicating pipeline is connected to the communicating pipeline between the electromagnetic directional valve 14 and the first stainless steel oil tank 16.1; the third communication line 18.3 is used to return excess oil to the first stainless steel reservoir 16.1.
Further, the device also comprises a pressure gauge switch 11 and a stainless steel high-temperature-resistant pressure gauge 12;
the pressure gauge switch 11 and the stainless steel high-temperature-resistant pressure gauge 12 are both arranged on the second communication pipeline 18.2; the pressure gauge switch 11 is used for adjusting the pressure of the first communication pipeline 18.1; the stainless steel high temperature resistant pressure gauge 12 is used for displaying the pressure of the first communication pipeline 18.1; and adjusting the maximum pressure of the injected lubricating oil to simulate the state of the lubricating oil when the engine runs normally.
Further, the device also comprises a pipeline filter 9 and a superposition type one-way valve 10; the line filter 9 is used for filtering the lubricating oil passing through the first communication line 18.1; impurities in the lubricating oil are prevented from entering the interior of the engine; the superposition type check valve 10 is used for controlling the flow direction of lubricating oil in the first communication pipeline 18.1;
the pipeline filter 9 and the superposed one-way valve 10 are sequentially arranged on the first communication pipeline 18.1 and are both positioned between the gear pump 8 and the electromagnetic directional valve 14; the pipeline filter 9 is positioned between the gear pump 8 and the superposition type one-way valve 10; the superposition type one-way valve 10 is positioned between the pipeline filter 9 and the electromagnetic directional valve 14;
one end of the second communicating pipeline 18.2 is connected to the communicating pipeline between the gear pump 8 and the pipeline filter 9, and the other end is connected to the communicating pipeline between the stacked one-way valve 10 and the electromagnetic directional valve 14; the second communication pipeline 18.2 is used for adjusting the pressure of the pipeline filter 9 and the superposition type one-way valve 10 on the first communication pipeline 18.1 in series.
Furthermore, the device also comprises a liquid level thermometer 1, an oil absorption filter 3, an air filter 4, a temperature sensor 6, an overflow valve 13, a heat insulation protection plate 15 and a pump outlet hose 19;
the overflow valve 13 is arranged on the third communication pipeline 18.3; returning excess lubricant to the first stainless steel reservoir 16.1;
the liquid level thermometer 1 is arranged on the side wall of the first stainless steel oil tank 16.1; the liquid level thermometer 1 is used for monitoring the liquid level and the temperature of lubricating oil in the first stainless steel oil tank 16.1; when the liquid level thermometer 1 detects that the lubricating oil in the oil tank is insufficient, the liquid level thermometer 1 gives an alarm, and the electric pump is disconnected, so that air is prevented from being injected into an oil channel of the engine;
the oil suction filter 3 is positioned in the first stainless steel oil tank 16.1 and is positioned at the lubricating oil inlet end of the first communication pipeline 18.1; the oil absorption filter 3 is used for filtering the lubricating oil entering the first communication pipeline 18.1; impurities in the lubricating oil are prevented from entering the interior of the engine;
the air filter 4 is positioned on the first stainless steel oil tank 16.1 and is communicated with the first stainless steel oil tank 16.1; the air filter 4 is used for filtering out air in the first stainless steel oil tank 16.1 and preventing the air from being injected into an oil duct of the engine;
the temperature sensor 6 is positioned in the first stainless steel oil tank 16.1, positioned at the bottom end of the first stainless steel oil tank 16.1 and communicated with the first stainless steel oil tank 16.1; when the lubricating oil is heated, a temperature sensor in the first stainless steel oil tank 16.1 detects the actual temperature of the lubricating oil, and a heating controller determines the on-off state of a heater by comparing the actual temperature of the lubricating oil with a preset temperature so as to ensure the proper temperature of the lubricating oil;
one end of a pump oil outlet hose 19 is connected with the electromagnetic directional valve 14, and the other end of the pump oil outlet hose is detachably connected with an engine oil duct fabrication hole according to requirements; the electromagnetic directional valve 14 injects lubricating oil into the engine oil duct fabrication hole through the pump oil outlet hose 19;
the first stainless steel oil tank 16.1 is arranged on the trolley 2; the first stainless steel oil tank 16.1 is convenient to move according to the requirement;
the heat insulation protection plate 15 is arranged on the outer side of the first stainless steel oil tank 16.1; avoid the staff scald.
Furthermore, the electromagnetic directional valve 14 includes a port a, a port B, a port P and a port T; the port A and the port B are arranged on one side of the electromagnetic directional valve 14 at intervals, and the port P and the port T are arranged on the other side of the electromagnetic directional valve 14 at intervals;
one end of the pump oil outlet hose 19 is detachably connected with the port A, and the other end of the pump oil outlet hose is detachably connected with an engine oil duct process hole according to requirements;
the port P and the port T are both positioned on the first communication pipeline 18.1; the P port and the T port are in a normal open state, and lubricating oil is circulated in the first stainless steel oil tank 16.1 through a first communication pipeline 18.1; the electromagnetic directional valve 14 is reversed to enable the port P to be communicated with the port A, and the heated lubricating oil is injected into an oil channel oil injection port 17 (shown in figures 1 and 3) of an engine 20 through a pump oil outlet hose 19 through the port A.
Further, an operation table 21 is also included; the operating platform is fixed on the trolley 2 and is positioned between the first stainless steel oil tank 16.1 and the second stainless steel oil tank 16.2 (as shown in fig. 3, 4 and 5);
an oil absorption filter 3 and an electric heater 5 are arranged in the second stainless steel oil tank 16.2; the liquid level thermometer 1 is arranged on the side wall of the second stainless steel oil tank 16.2; an air filter 4 is arranged at the upper part of the second stainless steel oil tank 16.2 and is communicated with the second stainless steel oil tank 16.2; the oil absorption filter 3 is used for filtering lubricating oil and preventing impurities in the lubricating oil from entering the interior of the engine; the air filter 4 is used for filtering air and preventing the air from being injected into an oil duct of the engine; the electric heater 5 is used for lubricating oil, and when heating the lubricating oil, a desired lubricating oil temperature can be set. A temperature sensor 6 is arranged on the second stainless steel oil tank 16.2 and is communicated with the second stainless steel oil tank 16.2 (as shown in figure 1); the temperature sensor 6 is used for detecting the actual temperature of the lubricating oil, and the heating controller determines the on-off of the heater by comparing the actual temperature of the lubricating oil with a preset temperature so as to ensure the proper temperature of the lubricating oil; the anti-corrosion oil in the second stainless steel oil tank 16.2 can be automatically heated to the working temperature, the operation is simple and convenient, and the working efficiency is improved;
the gear pump 8 is located on the operating table 21 (shown in fig. 3).
With reference to the accompanying drawings: the application method of the aviation piston engine lubricating oil pre-filling device comprises the following steps,
the engine 20 is provided with an oil passage oil filling port 17; the oil passage oil filling port 17 is an engine oil passage process hole;
the oil passage oil filling ports 17 comprise a first oil passage oil filling port 17.1 and a second oil passage oil filling port 17.2;
the first oil passage oil filling port 17.1 and the second oil passage oil filling port 17.2 are correspondingly arranged on two sides of the engine 20; the first oil passage fueling port 17.1 is used for fueling, and the first oil passage fueling port 17.1 is used for observation (as shown in fig. 2); the first oil passage oil filling port 17.1 and the second oil passage oil filling port 17.2 are equivalent, wherein one oil filling port is used for filling oil, and the other oil filling port can be used for observation;
one end of a pump oil outlet hose 19 is detachably connected with the port A, and the other end of the pump oil outlet hose is detachably connected with the first oil channel oil filling port 17.1 or the second oil channel oil filling port 17.2;
the method comprises the following steps: supplying power to an aviation piston engine lubricating oil pre-filling device: AC 380V, 50 Hz;
step two: after confirming that no alarm signal exists, pressing a lubricating oil heating button to heat the lubricating oil in the first stainless steel oil tank 16.1 to 70 ℃ (the lubricating oil temperature is 60-118 ℃ when the engine is required to normally run in a 60294-7 handbook);
when the temperature of the lubricating oil reaches 70 ℃, the electric heater 5 is automatically powered off; when the oil temperature is lower than 70 ℃, the electric heater 5 can be automatically electrified;
step three: adjusting the maximum pressure of oil injection to 90psi (the pressure of lubricating oil is 55-90 psi when the engine is required to normally run in a 60294-7 handbook); adjusting the maximum pressure of the injected lubricating oil, and simulating the state of the lubricating oil when the engine normally runs;
when the stainless steel high-temperature-resistant pressure gauge 12 displays that the maximum oil injection pressure reaches 90psi, the pressure gauge switch 11 is automatically closed; when the high-temperature-resistant pressure gauge 12 for the rust steel displays that the maximum oil injection pressure is less than 90psi, the pressure gauge switch 11 is automatically started;
step four: when the port P and the port T of the electromagnetic directional valve 14 are in a communicated state, the gear pump 8 works to cause the lubricating oil in the first stainless steel oil tank 16.1 to be internally circulated, so that the lubricating oil in the first stainless steel oil tank 16.1 is uniformly heated;
step five: when the oil temperature reaches 70 ℃, an oil outlet button is pressed, the electromagnetic directional valve 14 is reversed to enable the port P to be communicated with the port A, and the heated lubricating oil is injected into the first oil channel oil filling port 17.1 or the second oil channel oil filling port 17.2 through the pump oil outlet hose 19 through the port A;
when lubricating oil flows out uniformly from the second oil passage oil filling port 17.2 or the first oil passage oil filling port 17.1, oil filling is stopped, the oil passages in the engine are not blocked, and the lubricating oil is filled in all the oil passages in the engine;
when no lubricating oil flows out from the second oil passage oil filling port 17.2 or the first oil passage oil filling port 17.1 or only a small amount of lubricating oil flows out, whether the internal oil passage of the engine is blocked is checked; the operation is simple.
Furthermore, in step four, the internal circulation of the lubricant in the first stainless steel oil tank 16.1 in step four is specifically as follows: the gear pump 8 sucks the lubricating oil out of one side in the first stainless steel oil tank 16.1, and the lubricating oil returns to the other side of the first stainless steel oil tank 16.1 after passing through a port P of the electromagnetic directional valve 14 to a port T; the temperature distribution of the lubricating oil in the first stainless steel oil tank 16.1 is ensured to be uniform.
In order to more clearly illustrate the advantages of the aviation piston engine lubricating oil pre-filling device and the using method thereof in comparison with the prior art, the two technical schemes are compared by workers, and the comparison results are as follows:
compared with the prior art, the aviation piston engine lubricating oil pre-filling device and the using method thereof can provide sufficient lubrication for internal parts when the engine is started for the first time, reduce metal chips generated by abrasion, detect whether an internal oil passage of the engine is blocked or not, and have high working efficiency.
Other parts not described belong to the prior art.
Claims (10)
1. The aviation piston engine lubricating oil pre-filling device comprises a stainless steel oil tank (16); the method is characterized in that: the electric heating trolley further comprises a trolley (2), an electric heater (5), a motor (7), a gear pump (8), an electromagnetic directional valve (14) and a communicating pipeline (18); the motor (7), the gear pump (8) and the electromagnetic directional valve (14) are all arranged on the trolley (2);
the electric heater (5) is positioned in the stainless steel oil tank (16);
the motor (7) is connected with the gear pump (8);
the gear pump (8) is communicated with the stainless steel oil tank (16) through a communication pipeline (18);
the electromagnetic directional valve (14) is respectively communicated with the gear pump (8) and the stainless steel oil tank (16) through a communication pipeline (18).
2. The aviation piston engine oil prefill device of claim 1, wherein: the stainless steel oil tank (16) comprises a first stainless steel oil tank (16.1) for filling lubricating oil and a second stainless steel oil tank (16.2) for storing and heating anti-corrosive oil;
the first stainless steel oil tank (16.1) and the second stainless steel oil tank (16.2) are arranged on the trolley (2).
3. The aviation piston engine oil prefill device of claim 2, wherein: the communication pipeline (18) comprises a first communication pipeline (18.1), a second communication pipeline (18.2) and a third communication pipeline (18.3);
two ends of the first communication pipeline (18.1) are positioned in the first stainless steel oil tank (16.1) and are respectively positioned at two sides of the first stainless steel oil tank (16.1), and the middle part of the first communication pipeline is sequentially connected with the gear pump (8) and the electromagnetic directional valve (14) in series;
the second communication pipeline (18.2) is arranged on the first communication pipeline (18.1) and is positioned between the gear pump (8) and the electromagnetic directional valve (14);
the third communicating pipeline (18.3) is arranged on the first communicating pipeline (18.1), one end of the third communicating pipeline is connected to a communicating pipeline between the gear pump (8) and the electromagnetic directional valve (14), and the other end of the third communicating pipeline is connected to a communicating pipeline between the electromagnetic directional valve (14) and the first stainless steel oil tank (16.1).
4. An aviation piston engine oil prefill device according to claim 3, wherein: the pressure meter also comprises a pressure meter switch (11) and a stainless steel high-temperature-resistant pressure meter (12);
the pressure gauge switch (11) and the stainless steel high-temperature-resistant pressure gauge (12) are both arranged on the second communicating pipeline (18.2).
5. The aviation piston engine oil prefill device of claim 4, wherein: the device also comprises a pipeline filter (9) and a superposition type one-way valve (10);
the pipeline filter (9) and the superposed one-way valve (10) are sequentially arranged on the first communication pipeline (18.1) and are both positioned between the gear pump (8) and the electromagnetic directional valve (14);
one end of the second communicating pipeline (18.2) is connected to the communicating pipeline between the gear pump (8) and the pipeline filter (9), and the other end of the second communicating pipeline is connected to the communicating pipeline between the superposition type one-way valve (10) and the electromagnetic directional valve (14).
6. The aviation piston engine oil prefill device of claim 5, wherein: the device also comprises a liquid level thermometer (1), an oil absorption filter (3), an air filter (4), a temperature sensor (6), an overflow valve (13), a heat insulation protection plate (15) and a pump outlet hose (19);
the overflow valve (13) is arranged on the third communication pipeline (18.3);
the liquid level thermometer (1) is arranged on the side wall of the first stainless steel oil tank (16.1);
the oil suction filter (3) is positioned in the first stainless steel oil tank (16.1) and is positioned at the lubricating oil inlet end of the first communication pipeline (18.1);
the air filter (4) is positioned on the first stainless steel oil tank (16.1);
the temperature sensor (6) is positioned at the bottom end of the first stainless steel oil tank (16.1);
one end of a hose (19) at the oil outlet of the pump is connected with the electromagnetic directional valve (14);
the heat insulation protection plate (15) is arranged on the outer side of the first stainless steel oil tank (16.1).
7. The aviation piston engine oil prefill device of claim 6, wherein: the electromagnetic directional valve (14) comprises an A port, a B port, a P port and a T port; the port A and the port B are arranged on one side of the electromagnetic directional valve (14) at intervals, and the port P and the port T are arranged on the other side of the electromagnetic directional valve (14) at intervals;
one end of a hose (19) at the oil outlet of the pump is detachably connected with the port A;
the port P and the port T are both positioned on the first communication pipeline (18.1); the port P and the port T are in a normally open state.
8. The aviation piston engine oil prefill device of claim 7, wherein: also comprises an operating bench (21); the operating rack is fixed on the trolley (2) and is positioned between the first stainless steel oil tank (16.1) and the second stainless steel oil tank (16.2);
an oil absorption filter (3) and an electric heater (5) are arranged in the second stainless steel oil tank (16.2); a liquid level thermometer (1) is arranged on the side wall of the second stainless steel oil tank (16.2); an air filter (4) is arranged at the upper part of the second stainless steel oil tank (16.2) and is communicated with the second stainless steel oil tank (16.2);
a temperature sensor (6) is arranged on the side wall of the second stainless steel oil tank (16.2);
the gear pump (8) is positioned on the operating bench (21).
9. Use of an aviation piston engine oil pre-filling device according to any one of claims 1 to 8, characterised in that: comprises the following steps of (a) carrying out,
an oil passage oil filling port (17) is arranged on the engine (20); the oil passage oil filling port (17) comprises a first oil passage oil filling port (17.1) and a second oil passage oil filling port (17.2);
the first oil channel oil filling port (17.1) and the second oil channel oil filling port (17.2) are correspondingly arranged on two sides of the engine (20);
one end of a pump oil outlet hose (19) is detachably connected with the port A, and the other end of the pump oil outlet hose is detachably connected with a first oil channel oil filling port (17.1) or a second oil channel oil filling port (17.2);
the method comprises the following steps: supplying power to an aviation piston engine lubricating oil pre-filling device: AC 380V, 50 Hz;
step two: after no alarm signal is confirmed, pressing down a lubricating oil heating button to heat the lubricating oil in the first stainless steel oil tank (16.1) to 70 ℃;
when the temperature of the lubricating oil reaches 70 ℃, the electric heater (5) is automatically powered off;
step three: adjusting the oiling pressure to 90 psi;
when the stainless steel high-temperature-resistant pressure gauge (12) displays that the oil injection pressure reaches 90psi, the pressure gauge switch (11) is automatically closed;
step four: when the P port and the T port of the electromagnetic directional valve (14) are in a communicated state, the gear pump (8) works to enable the lubricating oil in the first stainless steel oil tank (16.1) to be internally circulated, so that the lubricating oil in the first stainless steel oil tank (16.1) is uniformly heated;
step five: when the oil temperature reaches 70 ℃ and the oil injection pressure reaches 90psi, an oil outlet button is pressed, an electromagnetic directional valve (14) is reversed to enable a port P to be communicated with a port A, and heated lubricating oil is injected into a first oil channel oil injection port (17.1) or a second oil channel oil injection port (17.2) through a pump oil outlet hose (19) through the port A;
when lubricating oil flows out uniformly from the second oil passage oil filling port (17.2) or the first oil passage oil filling port (17.1), oil filling is stopped, oil passages in the engine are not blocked, and all oil passages in the engine are filled with the lubricating oil;
and when no lubricating oil flows out or only a small amount of lubricating oil flows out from the second oil passage oil filling port (17.2) or the first oil passage oil filling port (17.1), whether the internal oil passage of the engine is blocked is checked.
10. The use of an aviation piston engine oil pre-fill apparatus as claimed in claim 8, wherein: in the fourth step, the internal circulation of the lubricating oil in the first stainless steel oil tank (16.1) is specifically as follows: the gear pump (8) sucks the lubricating oil from one side in the first stainless steel oil tank (16.1), and the lubricating oil returns to the other side of the first stainless steel oil tank (16.1) after passing through a port P to a port T of the electromagnetic directional valve (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911221913.5A CN110939495A (en) | 2019-12-03 | 2019-12-03 | Aviation piston engine lubricating oil pre-filling device and using method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911221913.5A CN110939495A (en) | 2019-12-03 | 2019-12-03 | Aviation piston engine lubricating oil pre-filling device and using method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110939495A true CN110939495A (en) | 2020-03-31 |
Family
ID=69908747
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911221913.5A Pending CN110939495A (en) | 2019-12-03 | 2019-12-03 | Aviation piston engine lubricating oil pre-filling device and using method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110939495A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113653791A (en) * | 2021-07-27 | 2021-11-16 | 山东中车风电有限公司 | Accurate oil injection device and method for wind turbine generator gearbox |
-
2019
- 2019-12-03 CN CN201911221913.5A patent/CN110939495A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113653791A (en) * | 2021-07-27 | 2021-11-16 | 山东中车风电有限公司 | Accurate oil injection device and method for wind turbine generator gearbox |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN202546199U (en) | Device for lubricating bearing | |
| MX2007015324A (en) | System and method for lubricating a transport device. | |
| CN100406728C (en) | Automatic balance and compensating device for refrigeration compressor oil level | |
| CN110939495A (en) | Aviation piston engine lubricating oil pre-filling device and using method thereof | |
| CN111961832B (en) | Processing technology of ultrahigh-strength spring steel wire | |
| CN103608575A (en) | Fuel system and method for reducing fuel leakage from a fuel system | |
| CN100578000C (en) | Common rail fuel injection system with fuel circulation device for a large two-stroke diesel engine | |
| CN201944356U (en) | Plunger type safety valve | |
| CN211343066U (en) | Aviation piston engine lubricating oil pre-filling device | |
| CN201133557Y (en) | Body-building equipment lubrication air pressure type oil supplier | |
| CN102287524A (en) | Speed reducer lubrication system | |
| KR102468205B1 (en) | Method of testing an injector valve for liquid gas | |
| CN109488869B (en) | Oil mist oil supplementing device | |
| CN202215718U (en) | A reduction box lubricating system | |
| WO2013136961A1 (en) | Cylinder oiling device | |
| CN111878694A (en) | Mobile lubricating oil filling and recycling integrated device | |
| CN216223849U (en) | Mechanical fluid proportioning and conveying equipment | |
| CN113893768A (en) | Mechanical fluid proportioning and conveying equipment | |
| CN200958681Y (en) | Diluted-oil pump station | |
| CN208653784U (en) | Free-standing compressor lubrication system detection platform | |
| CN203770999U (en) | Automatic lubricating device of filter press | |
| CN102877890B (en) | Lubrication system of single-screw expansion engine and control method of lubrication system | |
| CN208502996U (en) | A kind of main steam isolation valve air driven pump and relief valve suppress integrated apparatus offline | |
| CN207245906U (en) | Diesel fuel system leak detecting device | |
| CN211626929U (en) | Engine oil loading injection experimental device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |