Engine oil metering system suitable for rotor engine of low-altitude aircraft
By combining an electronic oil pump and a metering system, the output of oil in the cylinder of the rotor engine of the low-altitude aircraft is precisely controlled, which solves the problem of excessive oil combustion and improves the stability and environmental performance of the engine.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-27
- Publication Date
- 2026-03-10
AI Technical Summary
Existing technologies make it difficult to precisely control the output of oil in the cylinders of low-altitude aircraft rotor engines, leading to excessive oil combustion, which affects engine stability and environmental performance.
The metering system consists of an electronic oil pump, an oil metering valve, an oil pressure sensor, and a one-way nozzle. It precisely regulates the oil output through ECU control and engine pulse frequency signals, and achieves stable oil pressure and precise injection by combining hoses and metal pipelines.
It achieves precise control of the in-cylinder oil output of the rotary engine, alleviates excessive oil combustion, meets lubrication needs, reduces consumption, and extends maintenance intervals.
Smart Images
Figure CN121630552A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the technical field of oil draining devices for low-altitude aircraft rotor engines, specifically relating to an oil metering system suitable for low-altitude aircraft rotor engines. Background Technology
[0002] To meet the demands of low-altitude economics, the development trend of miniaturized aircraft rotary engines is increasing. To address the in-cylinder rotor lubrication requirements of rotary engines, an electronically controlled oil metering system has been developed to precisely control the in-cylinder oil output, effectively ensuring stable rotor operation. Simultaneously, this technology can effectively reduce oil consumption, improve environmental performance, and extend maintenance intervals. Summary of the Invention
[0003] The purpose of this invention is to precisely control the oil output within the cylinder of a rotary engine, meeting the rotor's lubrication requirements while alleviating engine oil burning. Precise control of the oil intake within the cylinder under different operating conditions effectively mitigates excessive oil combustion within the cylinder. The technical solution is as follows: An oil metering system for a low-altitude aircraft rotor engine is characterized by comprising: an electronic oil pump 2, an oil metering valve 3 connected to the oil outlet of the oil pump 2, an oil pressure sensor 4 connected to the oil outlet of the oil metering valve 3, a pressure nozzle 5 connected to the oil pressure sensor 4, an engine rotor cylinder 1 fixedly connected to the nozzle 5, the oil pressure sensor 4 being controlled by an ECU for the electronic oil pump 3, the oil metering valve 3 being controlled by a pulse frequency signal, the pressure nozzle 5 being a one-way nozzle, a hose connected to the oil inlet and outlet of the oil metering valve 3, and a metal pipe connected to the oil inlet and outlet of the pressure sensor 4.
[0004] The beneficial effects of this invention are: it can accurately control the oil output in the cylinder of the rotary engine, meet the lubrication requirements of the rotor, and alleviate the oil burning phenomenon of the engine; it can accurately control the oil intake in the cylinder of the rotary engine under different working conditions, and effectively alleviate the excessive combustion of oil in the cylinder. Attached Figure Description
[0005] Figure 1 This is a schematic diagram of the overall structure of the present invention; In the diagram: 1. Engine rotor cylinder; 2. Electronic oil pump; 3. Oil metering valve; 4. Oil pressure sensor; 5. Pressure nozzle. Detailed Implementation
[0006] Reference Figure 1The oil metering system for a low-altitude aircraft rotor engine is characterized by comprising: an electronic oil pump 2; an oil metering valve 3 connected to the oil outlet of the oil pump 2; an oil pressure sensor 4 connected to the oil outlet of the oil metering valve 3; a pressure nozzle 5 connected to the oil pressure sensor 4; an engine rotor cylinder 1 fixedly connected to the nozzle 5; the oil pressure sensor 4 is controlled by an ECU to the electronic oil pump 3; the oil metering valve 3 is controlled by a pulse frequency signal; the pressure nozzle 5 is a one-way nozzle; a hose is connected to the oil inlet and outlet of the oil metering valve 3; a metal pipe is connected to the oil inlet and outlet of the pressure sensor 4; and the oil metering valve 3 is installed in the oil line after the oil pump 2, allowing for either one-way oil inlet and outlet or one-way oil outlet. The oil inlet and outlet are multi-channel, which can be adjusted according to different lubrication requirements in the engine rotor cylinder 1. The oil metering valve 3 is a switch valve with a fixed oil output each time the valve core is opened and closed. It works in conjunction with the oil pressure sensor 4. The oil pressure sensor built into the electronic oil pump before the oil metering valve 3 can control the electronic oil pump 3 to maintain a stable oil pressure at the valve front end, thus ensuring a stable oil output from the oil metering valve 3. The ECU on the oil pressure sensor 4 after the valve controls the working frequency of the oil metering valve 3 to stably output oil. The oil metering valve 3 is controlled by the pulse frequency signal. Then, the oil passes through the one-way oil pressure nozzle 5 on the cylinder head, spraying a fixed amount of oil into the engine rotor cylinder 1. The oil inlet and outlet of the oil metering valve 3 are connected to hoses, and the oil inlet and outlet of the pressure sensor 4 are connected to metal pipes.
[0007] Of course, the above description is not intended to limit the present invention, and the present invention is not limited to the examples given above. Any changes, modifications, additions or substitutions made by those skilled in the art within the scope of the present invention should also fall within the protection scope of the present invention.
Claims
1. An oil metering system for a low altitude aircraft rotor engine, characterized by: Including electronic oil pump (2), the oil pump (2) oil outlet is connected with oil metering valve (3), the oil metering valve (3) oil outlet is connected with oil pressure sensor (4), the oil pressure sensor (4) is connected with pressure nozzle (5), the nozzle on the pressure nozzle (5) is fixedly connected with engine rotor cylinder (1).
2. An oil metering system for a rotor engine of a low altitude aircraft according to claim 1, characterized in that: The oil pressure sensor (4) is controlled by ECU to the electronic oil pump (3).
3. An oil metering system for a rotor engine of a low altitude aircraft as defined in claim 1 wherein: The oil metering valve (3) is controlled by engine pulse frequency signal.
4. An oil metering system for a rotor engine of a low altitude aircraft as defined in claim 1 wherein: The pressure nozzle (5) is a one-way nozzle.
5. An oil metering system for a rotor engine of a low altitude aircraft as defined in claim 1 wherein: The oil inlet and outlet of the oil metering valve (3) are connected with a hose.
6. An oil metering system for a rotor engine of a low altitude aircraft according to claim 1, characterized in that: The oil inlet and outlet of the pressure sensor (4) are connected with a metal pipe.