Spilled oil recovery system for ventilation tank of large aircraft inverted dihedral wing fuel system

A technology of oil spill recovery and fuel system, which is applied to aircraft parts, aircraft power units, power unit fuel supply, etc., can solve the problems of low reliability, poor economy, complex structure, etc., and achieve high reliability, simple structure, The effect of ensuring flight safety

Inactive Publication Date: 2015-10-28
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide an improvement of the oil spill recovery system for the breather tank of the lower anti-wing fuel system of a large aircraft, so as to solve the problems of the current oil spill recovery system such as complex structure, heavy weight, low reliability, and poor economy

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  • Spilled oil recovery system for ventilation tank of large aircraft inverted dihedral wing fuel system

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Embodiment Construction

[0014] Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings.

[0015] Such as figure 1 As shown, a kind of large-scale aircraft anti-wing fuel system breather tank overflow recovery system provided by the present invention includes a breather box 1, a main fuel tank 6 and an oil return injection pump 3 inside the breather box 1 and the main fuel tank 6 and Electric oil supply pump5.

[0016] The oil return ejector pump 3 is a variety of known suitable ejector pumps, and usually has a flow port 3a, an oil suction port 3b and an oil outlet port 3c, and the specific ejection principle will not be repeated here. The oil return ejector pump 3 is arranged inside the breather box 1, and its oil outlet 3c communicates with the main oil tank 6 through a pipeline.

[0017] The electric oil supply pump 5 can be various known suitable oil pumps, and usually includes an oil inlet and an oil outlet. The electric...

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Abstract

The invention relates to a spilled oil recovery technology for a ventilation tank of an aircraft fuel system, in particular to an improvement on a spilled oil recovery system for the ventilation tank of a large aircraft inverted dihedral wing fuel system. The spilled oil recovery system for the ventilation tank of the large aircraft inverted dihedral wing fuel system is designed to solve problems of the traditional spilled oil recovery system such ascomplicated structure, heavy weight, low reliability, poor economic efficiency. In the spilled oil recovery system for the ventilation tank of the large aircraft inverted dihedral wing fuel system, a scavenge oil ejector pump is arranged in the ventilation tank; and an electric oil supply pump in a main oil tank is used as a moving flow source of the scavenge oil ejector pump so that spilled oil in the ventilation tank is conveyed into the main oil tank; therefore, unavailable oil quantity of an aircraft can be reduced, the oil loss is avoided and the flight safety is assured; and moreover, the whole recovery system has the advantages of simple structure, light weight and high reliability.

Description

technical field [0001] The invention relates to an oil overflow recovery technology for an aircraft fuel system vent box, in particular to an improvement of an oil overflow recovery system for a large aircraft lower anti-wing fuel system vent box. Background technique [0002] The breather box of the lower anti-wing fuel system of a large aircraft is generally located outside the main fuel tank, and its position is lower than the main fuel tank. When the aircraft maneuvers, the fuel in the main fuel tank may overflow into the breather box. The design method of oil overflow recovery from the breather box of the lower anti-wing fuel system of the traditional large aircraft is to install a fuel level indicator in the breather box, and install an electric booster pump and its control system. When the fuel in the breather box reaches the oil level indicator , the oil level signaler sends out a signal, automatically or manually turns on the electric booster pump of the breather bo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D37/00
Inventor 林厚焰刘苏彦何明余鹏
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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