JPS6044199B2 - electric pump - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to an improvement in an electric pump that is attached to an aircraft fuel tank by being immersed in the fuel therein, and particularly relates to improving the ability to supply fuel during inverted flight of an aircraft.

1 and 2 show a conventional electric pump of this type,
The figures show normal flight and inverted flight of the aircraft, respectively.

In the figure, reference numeral 1 denotes a sup tank, from which fuel 3 is supplied through a fuel supply pipe 2 either above the sup tank or from a main tank (not shown).

If the air in the main tank enters the sap tank, use the exhaust hole (not shown) provided at the top of the sap tank.
Air is returned to the main tank through the tank. 4
is an electric pump housing whose interior is divided into a seal chamber 5 and a pump chamber 6, and has a discharge port (not shown) at the outlet of the spiral chamber 7, and several screws 8 at the bottom of the sup tank 1. is fixed.

A casing 9 houses an electric motor (not shown) and is fixed to the housing 4.

Reference numeral 10 denotes a substantially vertical shaft rotatably driven by an electric motor, which passes through the seal chamber 5 and projects into the pump chamber 6.

11 is an impeller, 12 is a key, and 13 is a nut. The impeller 11 is fixed to the downwardly downward end of the shaft 10 with the key 12 and the nut 13, and rotates together with the shaft 10.

14 is a throat fixed to the housing 4 with several screws 15, which forms an opening 16 of the electric pump;
A sealing O-ring 17 is attached to the fitting portion with the housing 4.

A pair of sealing devices 18 include a rotating slip ring 19 and a stationary slip ring 20. The rotating slip ring 19 is fixed to the impeller 11 and rotates together with the impeller 11 and the shaft 10.

Reference numeral 21 denotes a spring which presses the fixed slip ring 20 against the rotating slip ring 19 at a predetermined pressure to maintain a sealed state inside and outside the seal chamber 5.

22 and 23 are O-rings for sealing, 24 is a gasket,
25 is an inlet portion of the electric pump.

26 is the air in the main tank that has entered the sup tank 1.

In the conventional electric pump having the above configuration, when the electric motor in the casing 9 is driven by an external power input and the impeller 11 rotates in a predetermined direction together with the shaft 10, the oil is pumped from the main tank through the oil supply pipe 2 into the sup tank 1. The fuel 3 supplied to the inlet 25 of the electric pump
The air is sucked through the opening 16 and is pumped to the aircraft engine via the spiral chamber 7 in the pump chamber 6 and the discharge port (not shown). At this time, the rotating slip ring 19, which is fixed to the impeller 11 and rotates integrally with the shaft 10, is in sliding contact with the fixed slip ring 20 and the spring 21 under a predetermined pressure, so that the inside and outside of the rotating slip ring 19 are kept sealed.
The fuel in the seal chamber 5 does not enter the electric motor side.
However, according to this method, when the aircraft is flying normally, the fuel in the main tank is 3.
is naturally supplied into the sump tank 1 by gravity through the fuel supply pipe 2, and the air in the main tank does not enter the sump tank 1, so the electric pump pumps the fuel 3 to the aircraft engine at a predetermined pressure. However, when the aircraft flies inverted, etc., the main tank and sump tank 1 are reversed as shown in Figure 2, so the air 26 in the main tank gradually enters the sump tank 1 through the fuel supply pipe 2. This will quickly cover the opening 16 of the electric pump.

For this reason, the electric pump could no longer pump the fuel 3 in the sump tank 1 to the aircraft engine, which had a drawback that could lead to a serious accident. The present invention takes the above facts into account,
The purpose is to provide an electric pump that can stably pump fuel in the sump tank to the aircraft engine for a certain period of time even when the aircraft is inverted. By providing a partition wall integral with the conventional one, the disadvantages of the conventional method are overcome.

An embodiment of the electric pump according to the present invention will be described in detail below with reference to FIGS. 13 and 4.

3 and 4 are side partial sectional views showing one embodiment of the present invention, and since numerals 1 to 26 are the same as those of the conventional device, their explanation will be omitted. Reference numeral 27 denotes a partition integral with the housing 4 that is provided around the inlet portion 25 of the electric pump at regular intervals, 28 refers to the suction port of the electric pump formed by the partition 27, and 29 refers to the partition wall of the partition. This is the end.

The electric pump according to the present invention is constructed as described above, and its effects will be explained next. 4 When the aircraft is flying normally, the sump tank 1 is sufficiently supplied with fuel 3 from the main tank through the fuel supply pipe 2 as shown in Figure 3, so the electric pump supplies the fuel 3 at a predetermined pressure.
Similar to conventional electric pumps, it can pump air into aircraft engines. Next, when the aircraft flies inverted, the air 26 in the main tank gradually enters the sump tank 1 through the fuel supply pipe 2, as shown in FIG.
Air 26, which has a much lighter specific gravity than the fuel 3, is in the housing 4.
The partition wall 27 prevents the particles from entering the pump chamber, and they accumulate on the outside of the partition wall 27.

On the other hand, in the pump chamber, due to the continuous rotation of the impeller 11 that rotates integrally with the shaft 10, the air flows from the suction port 28 of the electric pump made by the partition wall of the housing 4, through the inlet portion 25, the opening portion 16, and the spiral chamber 7. Since a continuous flow path for the fuel 3 leading to the discharge port (not shown) is formed, the electric pump keeps the fuel 3 at a predetermined level until the air 26 that has entered the sump tank 1 reaches the end 29 of the bulkhead. It can be stably supplied to aircraft engines under pressure. In the above description, an electric pump that is installed by being immersed in an aircraft fuel tank has been described, but it goes without saying that it can also be used for pumps for various fluids other than aircraft.

As explained above, the present invention provides a bulkhead that is integrated with the housing around the inlet of the electric pump, so that even when the electric pump is operated in the reverse position such as during inverted flight of an aircraft, the inside of the sump tank can be maintained. The partition wall prevents air from entering the pump chamber, and within the partition wall, a continuous flow path is formed from the suction port to the discharge port of the electric pump. Fuel can be supplied to the aircraft engine at a predetermined pressure until it reaches the end, and has an excellent practical effect in that the aircraft can fly safely during this period.

[Brief explanation of drawings]

FIGS. 1 and 2 are side partial sectional views of a conventional electric pump, showing the states during normal flight and inverted flight of an aircraft, respectively. FIGS. 3 and 4 are side partial sectional views showing one embodiment of the present invention, showing the aircraft in normal flight and inverted flight, respectively. In the figure, 1 is a sump tank, 2 is a fuel supply pipe, 3 is fuel, 4 is a housing, 6 is a pump chamber, 10 is a shaft, 11 is an impeller, 25 is an electric pump inlet, 26 is air, 27 is a partition, 28 is a suction port,
29 is the end of the partition.

Claims (1)

[Claims] 1. In an electric pump, an impeller fixed to rotate together with a shaft protruding into a pump chamber of a housing is driven by an electric motor, and rotates at high speed to pump fuel from the suction port to the discharge port of the pump. , a partition wall integrated with the housing is provided around the inlet of the pump,
An electric pump characterized by separating the inlet part of the pump from the outside.