JPH0941990A - Pump unit of jet engine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To feed priming water automatically to a pump suction side even when a attitude of an airplane, for instance, is restored after a fluid runout has occurred by an attitude variation or the like. SOLUTION: A priming water tank 5 is installed in a pipeline 2 at the suction side of a liquid supplying pump 4 so as to make it be situated more upward than the pipeline. In addition, a partition wall 6, partitioning an inner part of this tankto both downstream and upstream sides, is installed in this priming water tank so as to leave a clearance 7 between a bottom surface 5a and a ceiling part 5d rising upward from the bottom of the tank. Then an orifice 8 is installed beneath the partition wall.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a jet engine pump device.

[0002]

2. Description of the Related Art In a lubricating oil line of a jet engine, for example, a lubricating oil is pumped by an oil pump in order to lubricate and cool bearings and lubricate various gears. Used.

[0003]

In a positive displacement pump such as a gear pump, a phenomenon occurs in which fluid is temporarily cut off and the air does not function when a certain amount of air is replaced. In jet aircraft, the oil tank may be turned upside down due to changes in posture (for example, rear flight). In this case, air may replace lubricating oil in the lubricating oil line, and lubricating oil may not be supplied as desired. There is. When the air is replaced in the lubricating oil line in this way, it is necessary to perform a work of supplying priming water or the like to the suction side of the oil pump, which hinders continuous operation of the lubricating oil system.

The present invention has been made in view of the above circumstances, and is capable of automatically supplying priming water to the pump suction side even when the posture returns after the fluid has been cut off due to a change in posture or the like. It is an object of the present invention to provide a pump device of the above.

[0005]

In order to achieve the above object, in the invention according to claim 1, a suction tank of a liquid supply pump is provided with a priming tank so as to be located above the piping. The priming water tank is characterized in that a partition wall for partitioning the inside of the tank into a downstream side and an upstream side is provided so as to rise upward from the bottom surface of the tank and leave a gap between the tank and the ceiling.

According to a second aspect of the invention, an orifice is provided in the lower portion of the partition wall.

The invention according to claim 3 is characterized in that the partition wall is provided on the side opposite to the liquid supply pump so that the volume on the fuel supply pump side is large.

<Operation> In the invention described in claim 1, for example, when performing a rear flight due to a change in posture, air may be temporarily replaced by the pump, but the supply liquid remains in the priming tank, The supply liquid remaining in the priming tank flows into the suction side of the pump when the flight attitude returns to the original position, and functions as priming. Therefore,
The continuous operation of the pump can be performed without any special work such as supplying priming water to the suction side of the pump.

Further, if the orifice is provided in the lower portion of the partition wall, the air will pass through the orifice without passing through the gap in the ceiling portion of the priming tank during the back flight as described above. It is possible to avoid a situation in which the liquid remaining in the priming tank is pushed to the pump side by the air as the air passes through the gap in the ceiling of the priming tank.

[0010]

Embodiments of the present invention will be described.
FIG. 1 shows an example in which the present invention is applied to a lubricating oil line of a jet engine, where reference numeral 1 is an oil tank,
2 is a pipe for supplying lubricating oil, which extends from the oil tank 1 to each device 3 that requires lubricating oil for the jet engine, and 4 is a pipe 2
It is a gear pump for lubricating hydraulic transmission, which is installed inside. In the pipe 2 on the suction side of the gear pump 4, a tank 5 for priming water
Is interposed.

The tank 5 for priming water is arranged so as to be located above the pipe on the suction side of the gear pump 4. In the priming tank 5, a partition wall 6 that partitions the inside into a downstream side and an upstream side, in other words, a partition wall 6 extending in a direction substantially orthogonal to the flowing direction of the liquid rises upward from the bottom surface 5a of the tank, and the ceiling portion It is provided so as to leave a gap 7 between it and 5b. Further, the partition wall 6 is provided closer to the oil tank 1 side than the center so that the volume on the gear pump 4 side in the tank 5 is larger than the volume on the other side. An orifice 8 is formed below the partition wall 6.

The capacity of the tank 5 for priming water includes the length of the pipe 2 from the oil tank 1 to the tank 5 for priming water, the diameter of the pipe 2, and the time when the posture is changed (for example, the time of rear flight). The lubricating oil remaining in the priming tank 5 flows toward the gear pump 4 and functions as priming when the flight returns from the rear flight to the normal attitude, and the oil can be continuously supplied by the gear pump 4 without any trouble. It is decided to the extent. In addition, 10 is an oil tank 1 from each device 3 that requires the lubricating oil of the jet engine.
It is a pipe for returning the lubricating oil which extends to the pipe 10. A pump for recovering the lubricating oil is interposed in the pipe 10 as necessary.

Next, the operation will be described. When the aircraft is in a normal flight state, the lubricating oil recovered in the oil tank 1 is sucked into the pipe 2 through the opening 2a of the pipe 2 which is immersed in the oil tank 1, and passes through the tank 5 for priming water. To the gear pump 4, and is pumped from there to supply the lubricating oil of the jet engine to each device 3 that requires it.

When the lubricating oil passes through the priming tank 5, the passage resistance of the orifice 8 is large, so that the lubricating oil mainly passes through the gap 7 above the priming tank 5 as shown by the arrow in FIG. It will be. Therefore, the tank 5 for priming water
Air does not easily accumulate in the upper part of the inside, and the tank 5 passes with the lubricating oil filled.

Due to the change in posture, for example, when performing a rear flight, the top and bottom are reversed as shown in FIG. 2, and therefore the opening 2a of the pipe 2 arranged in the oil tank 1 is exposed to the air. The air temporarily enters from here. When the invaded air passes through the priming water tank 5, since it is a gas, the passage resistance of the orifice 8 is extremely small. Therefore, the air mainly passes through the orifice 8 instead of the gap 7, and the inside of the priming water tank 5 Lubricating oil remains in the.

After that, when the posture is changed back to the original state, the lubricating oil remaining in the priming tank 5 flows into the suction side of the gear pump 4 as shown in FIG. 3 and functions as priming. Therefore, without performing special work such as supplying priming water to the suction side of the gear pump 4,
The gear pump 4 can be continuously operated. The gear pump 4
When the lubricating oil is pressure-fed by the operation of, the lubricating oil passes through the gap in the upper part of the priming tank 5 as shown in FIG. 4, and the air remaining in the priming tank 5 is quickly transmitted to the device 3 side by the gear pump 4. Is pushed to.

The present invention is not necessarily applied to the lubricating oil line of the jet engine, but can be applied to other liquid supply lines such as fuel supply lines.

[0018]

According to the invention as set forth in claim 1, even if the posture is restored after the air is temporarily replaced by the pump due to the posture change, the priming water is supplied to the suction side of the pump. The continuous operation of the pump can be performed without performing the work.

According to the second aspect of the present invention, since the orifice is provided in the lower portion of the partition wall, the air can pass through the orifice without passing through the gap in the ceiling portion of the priming tank during a back flight. Therefore, it is possible to avoid a situation in which the liquid remaining in the priming tank is pushed to the pump side by the air as the air passes through the gap in the ceiling of the priming tank.

According to the third aspect of the invention, since the partition wall is provided close to the side opposite to the liquid supply pump so that the volume on the fuel supply pump side is large, for example, from the rear flight. When returning to the original posture, a large amount of the liquid remaining in the priming tank can be supplied to the suction side of the pump, and the tank has a small capacity and has an excellent effect of not impairing the priming function.

[Brief description of drawings]

FIG. 1 is a schematic configuration diagram of a pump device for a jet engine showing an embodiment of the present invention.

FIG. 2 is a view for explaining the operation of the jet engine pump device.

FIG. 3 is a diagram for explaining the operation of the jet engine pump device.

FIG. 4 is a view for explaining the operation of the jet engine pump device.

[Explanation of symbols]

 1 Oil Tank 2 Piping 3 Equipment 4 Gear Pump 5 Priming Tank 5a Bottom 5b Ceiling 6 Partition Wall 7 Gap 8 Orifice

Claims (3)

[Claims] 1. A pipe on a suction side of a liquid supply pump,
A priming water tank is provided so as to be positioned above the pipe, and a partition wall that partitions the inside of the tank into a downstream side and an upstream side is provided between the bottom surface of the tank and the ceiling portion. A jet engine pump device characterized by being provided so as to leave a gap. 2. The jet engine pump device according to claim 1, wherein an orifice is provided in a lower portion of the partition wall. 3. The jet engine pump device according to claim 2, wherein the partition wall is provided on the side opposite to the liquid supply pump so that the volume on the liquid supply pump side is large. And a jet engine pump device.