CN211924319U - Turbocharger lubricating device of aviation piston engine - Google Patents
Turbocharger lubricating device of aviation piston engine Download PDFInfo
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- CN211924319U CN211924319U CN202020520626.6U CN202020520626U CN211924319U CN 211924319 U CN211924319 U CN 211924319U CN 202020520626 U CN202020520626 U CN 202020520626U CN 211924319 U CN211924319 U CN 211924319U
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Abstract
The utility model discloses an aviation piston engine turbo charger lubricating arrangement, include the oil pipe that advances of being connected with turbo charger's inlet port, with advance the oil union coupling and with the one-way valve that ends that the engine main oil duct is connected, with turbo charger's oil gallery connection's lubricating oil storage tank, with the oil pipe that returns that the lubricating oil storage tank is connected and with the scavenge pump that returns the oil union coupling. The utility model discloses an aviation piston engine turbo charger lubricating arrangement can guarantee that turbo charger's lubrication is reliable.
Description
Technical Field
The utility model belongs to the technical field of the engine, specifically speaking, the utility model relates to an aviation piston engine turbo charger lubricating arrangement.
Background
The turbocharger of the engine for the conventional vehicle is generally arranged on the side surface of the engine, the turbocharger is directly connected with a main oil duct of the engine through an oil inlet pipe to realize lubrication, and gravity oil return is adopted for oil return of lubricating oil. However, in the aviation piston engine, because of the arrangement requirement of an airplane, the turbocharger is positioned at the lower side of the engine, and the height of the oil level of the lubricating oil tank is higher than the axis of the turbocharger, gravity oil return cannot be realized by adopting a conventional supercharger oil inlet and return structure; meanwhile, the oil inlet pipe is directly communicated with the main oil duct, the height of the main oil duct is higher than that of an oil inlet hole of the supercharger, and residual engine oil in the main oil duct can continuously flow into a turbocharger intermediate body after the supercharger is stopped and directly flows into a supercharger turbine and a gas compressor through an opening area of a sealing ring to cause the oil leakage when the supercharger is stopped; because the residual engine oil in the main oil gallery leaks, the oil pressure is established for a long time when the engine is restarted, which is not beneficial to the lubrication of the engine body and the turbocharger.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides an aviation piston engine turbo charger lubricating arrangement, the purpose improves turbo charger's lubricated reliability.
In order to realize the purpose, the utility model discloses the technical scheme who takes does: the lubricating device for the turbocharger of the aviation piston engine comprises an oil inlet pipe connected with an oil inlet hole of the turbocharger, a one-way check valve connected with the oil inlet pipe and connected with a main oil duct of the engine, a lubricating oil storage tank connected with an oil return hole of the turbocharger, an oil return pipe connected with the lubricating oil storage tank and an oil return pump connected with the oil return pipe.
The lubricating oil storage tank is located below the turbocharger, and the oil inlet pipe is located above the turbocharger.
The utility model discloses an aviation piston engine turbo charger lubricating arrangement can guarantee that turbo charger's lubrication is reliable.
Drawings
The description includes the following figures, the contents shown are respectively:
FIG. 1 is a schematic structural diagram of a turbocharger lubricating device of an aviation piston engine according to the present invention;
labeled as: 1. a one-way check valve; 1-1, oil inlet end; 1-2, oil outlet end; 2. an oil inlet pipe; 3. a turbocharger; 3-1, oil inlet holes; 3-2, oil return holes; 4. a lubricating oil storage tank; 4-1, oil inlet end; 4-2, an oil return end; 5. an oil return pipe; 6. and a return pump.
Detailed Description
The following detailed description of the embodiments of the present invention will be given with reference to the accompanying drawings, for the purpose of helping those skilled in the art to understand more completely, accurately and deeply the conception and technical solution of the present invention, and to facilitate its implementation.
As shown in fig. 1, the utility model provides an aviation piston engine turbo charger lubricating arrangement, include the oil pipe 2 that advances of being connected with turbo charger 3's inlet port, with advance oil pipe 2 and be connected and the one-way stagnant flow valve 1 of being connected with the engine main oil gallery, with turbo charger 3's oil return opening be connected the lubricating oil storage tank 4, with the oil return pipe 5 that lubricating oil storage tank 4 is connected and with the scavenge oil pump 6 that oil pipe 5 is connected. When the oil return pump 6 operates, negative pressure can be formed in the oil return pipe 5, the negative pressure is used for guiding lubricating oil collected in the lubricating oil storage tank 4 to the oil return pump 6, and then the lubricating oil is pumped to an engine lubricating oil tank by the oil return pump 6, so that oil return is realized.
Specifically, as shown in fig. 1, an oil inlet end 1-1 of the one-way check valve 1 is connected to an engine main oil gallery, an oil return end 1-2 of the one-way check valve 1 is connected to an oil inlet end of an oil inlet pipe 2, and an oil return end of the oil inlet pipe 2 is connected to an oil inlet end of a turbocharger 3. The one-way check valve 1 has a pressure opening function, when the pressure in the main oil duct of the engine reaches a preset value, namely the pressure in the main oil duct of the engine reaches the opening pressure of the one-way check valve 1, the one-way check valve 1 is opened, when the oil pressure in the main oil duct of the engine is lower than the preset pressure, the one-way check valve 1 is in a closed state, and the lubricating oil in the main oil duct of the engine cannot flow from the one-way check valve 1 to the oil inlet pipe 2, namely cannot flow to the turbocharger 3. The oil outlet end of the one-way check valve 1 is connected with the oil inlet hole 3-1 of the supercharger through the oil inlet pipe 2, and when the engine is started, high-pressure lubricating oil can enter the turbocharger 3 through the one-way check valve 1 and the oil inlet pipe 2 to realize lubrication.
As shown in fig. 1, the oil storage tank 4 is located below the turbocharger 3, and the oil inlet pipe 2 is located above the turbocharger 3. The oil inlet end of the oil return pipe 5 is connected with the oil return end of the lubricating oil storage tank 4, and the oil return end of the oil return pipe 5 is connected with the oil inlet end of the oil return pump 6. An oil inlet end 4-1 of the lubricating oil storage tank 4 is arranged on an oil return hole 3-2 of the turbocharger 3, lubricating oil return oil in the turbocharger 3 flows to the lubricating oil storage tank 4 under the action of gravity, and the oil return end 4-2 of the lubricating oil storage tank 4 is connected with an oil return pump 6 through an oil return pipe 5. When the oil return pump 6 works, a certain negative pressure is formed in the oil return pipe 5, and the negative pressure pumps the lubricating oil collected in the lubricating oil storage tank 4 to the lubricating oil tank of the engine, so that forced oil return of the turbocharger 3 is realized.
When the engine is stopped, the pressure of the lubricating oil in the main oil passage of the engine is reduced to normal pressure, and the residual lubricating oil in the main oil passage of the engine cannot be discharged out of the main oil passage of the engine through the one-way check valve 1 due to low pressure. Because a certain amount of lubricating oil remains in the main oil gallery of the engine, the oil pressure building time of the main oil gallery of the engine can be shortened when the engine is restarted, so that the reliable lubrication of the engine body and the turbocharger 3 is ensured. Meanwhile, when the engine is stopped, residual lubricating oil in the oil inlet pipe 2, the turbocharger 3 and the oil return pipe 5 flows back to the lubricating oil storage tank 4 with a certain volume under the action of gravity, and the volume of the lubricating oil storage tank 4 is not less than that of the residual lubricating oil in the oil inlet pipe 2, the turbocharger 3 and the oil return pipe 5, so that the condition of stopping and oil leakage caused by a large amount of residual engine oil in the turbocharger 3 can be avoided.
The invention has been described above by way of example with reference to the accompanying drawings. Obviously, the specific implementation of the present invention is not limited by the above-described manner. Various insubstantial improvements are made by adopting the method conception and the technical proposal of the utility model; or without improvement, the above conception and technical solution of the present invention can be directly applied to other occasions, all within the protection scope of the present invention.
Claims (2)
1. Aviation piston engine turbo charger lubricating arrangement which characterized in that: the device comprises an oil inlet pipe connected with an oil inlet hole of the turbocharger, a one-way check valve connected with the oil inlet pipe and connected with a main oil duct of the engine, a lubricating oil storage tank connected with an oil return hole of the turbocharger, an oil return pipe connected with the lubricating oil storage tank and an oil return pump connected with the oil return pipe.
2. An aviation piston engine turbocharger lubrication device according to claim 1, characterised in that: the lubricating oil storage tank is located below the turbocharger, and the oil inlet pipe is located above the turbocharger.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020520626.6U CN211924319U (en) | 2020-04-10 | 2020-04-10 | Turbocharger lubricating device of aviation piston engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020520626.6U CN211924319U (en) | 2020-04-10 | 2020-04-10 | Turbocharger lubricating device of aviation piston engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211924319U true CN211924319U (en) | 2020-11-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202020520626.6U Active CN211924319U (en) | 2020-04-10 | 2020-04-10 | Turbocharger lubricating device of aviation piston engine |
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| CN (1) | CN211924319U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115327027A (en) * | 2022-08-23 | 2022-11-11 | 芜湖钻石航空发动机有限公司 | Fireproof test device and method for oil return pipe of supercharger |
-
2020
- 2020-04-10 CN CN202020520626.6U patent/CN211924319U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115327027A (en) * | 2022-08-23 | 2022-11-11 | 芜湖钻石航空发动机有限公司 | Fireproof test device and method for oil return pipe of supercharger |
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