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Aircraft propeller feathering pump

A technology for feathering pumps and propellers, which is applied in the field of aircraft propeller design to achieve the effect of reducing control logic

Pending Publication Date: 2019-04-05
AVIC HUIYANG AVIATION PROPELLER
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Its defect is that a set of switching oil circuit solenoid valves is required to switch the valve and oil circuit to reduce the pitch and return the propeller

Method used

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  • Aircraft propeller feathering pump
  • Aircraft propeller feathering pump

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Experimental program
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Embodiment Construction

[0016] The specific implementation manners of the present invention will be further described below in conjunction with the accompanying drawings.

[0017] see figure 2 , in order to meet the needs of the feathering device of the present invention to realize feathering back, the two ports A and B of the gear pump are required to be able to feed oil from the fuel tank. Check valves are installed on ports B and B respectively.

[0018] Assume that when the output shaft of the driving motor rotates forward (assuming that it is facing the motor mounting seat, the motor output shaft rotates counterclockwise), the driving gear in the driving gear pump rotates, the lubricating oil enters from port B, and the gear pump pressurizes the lubricating oil to form a high pressure Lubricating oil, high-pressure lubricating oil flows out from A port, adjusts the pressure of the lubricating oil through the pressure reducing valve, enters the pitch control device, enters the pitch valve throu...

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Abstract

The invention belongs to the technology of aircraft propeller design and relates to the aircraft propeller feathering pump. The aircraft propeller feathering pump comprises a motor, a gear pump and apressure reducing valve and is characterized in that the motor is a motor capable of rotating in two directions; the motor drives the gear pump to rotate, and the gear pump pressurizes lubricating oilto obtain high-pressure lubricating oil; the oil can flow into two ports of the gear pump from an oil tank; and the two ports of the gear pump are provided with check valves, so that the high-pressure lubricating oil pressurized by the gear pump is prevented from entering the oil tank. An electromagnetic valve oil way switching process is omitted, through improved design of the feathering pump, the high-pressure lubricating oil of the feathering pump directly enters a small-pitch oil cavity of a propeller, and the weight of an aircraft and the control logic of propeller feathering blades arereduced.

Description

technical field [0001] The invention belongs to the aircraft propeller design technology and relates to an aircraft propeller feathering pump. Background technique [0002] In the propeller control system, when the engine is not started, in order to detect that the propeller pitch angle can change within the entire range, it is necessary to check the propeller pitch on the ground. Therefore, in the propeller control system, there is a set of devices for driving the feathering propeller to realize the inspection of the pitch angle of the propeller on the ground. [0003] The steps of traditional propeller driving feathering: drive the motor on the feathering pump to work, the motor drives the gear pump on the feathering pump to rotate, the gear pump pressurizes the lubricating oil to form high-pressure lubricating oil, and the high-pressure lubricating oil passes through the pitch control device It enters the large-pitch oil cavity of the propeller, which makes the propeller...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C11/38B64C11/30
CPCB64C11/385B64C11/30
Inventor 曾庆珏王宁刘松兰颖周艳红李艳红郭建祥曹德松史晓雪陈风张亮
Owner AVIC HUIYANG AVIATION PROPELLER
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