JPH04279730A - Emergency oil feeding device of gas turbine - Google Patents

Abstract

PURPOSE:To contrive a simple structure, a compact size, and a light weight, by providing an oil reservoir to feed an oil for lubrication in a normal condition at a position higher than the main bearing of an engine, and dropping the oil in the oil reservoir spontaneously to feed to the main bearing from the inside of a rotating shaft, in an emergency. CONSTITUTION:In a normal condition, an oil pressured by an oil pump 12 is injected from an oil jet nozzle 4 in a rotating shaft 9, from an oil reservoir 1. And the oil flows along plural grooves at the inner surface of the internal hole of the rotating shaft 9, it is injected from holes provided to a wall body by the function of centrifugal force, and fed to a main bearing 5. On the other hand, in an emergent condition, the oil in the oil reservoir 1 is lowered to the level 11 of an oil feeding part. In this case, the oil led from the bottom of the oil reservoir 1 is dropped in the rotating shaft 9 from an exhaust oil feeding nozzle 7 by a spontaneous dropping, and then it is fed to the main bearing 5 in the same way of the above condition. This oil feeding is continued until the oil in the oil reservoir 1 is eliminated.

Description

[Detailed description of the invention]

0001

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an emergency refueling system for an aircraft gas turbine engine.

0002

2. Description of the Related Art In a conventional aircraft gas turbine engine equipped with an emergency refueling system, as shown in FIG. In addition to forcibly supplying oil to the main bearings 5a, 5b, 5c, etc., an emergency oil reservoir 2 is installed, and when the oil supply pump 12 loses its function, the emergency oil jet 7 is supplied from the same oil reservoir.
A system has been adopted in which oil is introduced into the bearings, and oil mist 8a, 8b, 8c generated by the atomizing action of separately introduced compressed air 6 is sprayed onto the bearings for lubrication.

0003

The conventional emergency refueling system has the following drawbacks. (1) In addition to the oil reservoir for normal lubrication, an oil reservoir for use only in emergencies is required, resulting in an increase in weight. (2) Compressed air must be introduced to generate oil mist. (3) Multiple devices are required to generate and spray oil mist to multiple locations that require lubrication in an emergency.

The present invention aims to overcome the drawbacks of the prior art described above and provide an emergency refueling system that is simple in structure, small in size, lightweight, and low in cost.

[0005]

[Means for Solving the Problems] The present invention has solved the above-mentioned problems by installing an oil reservoir that supplies lubricating oil in normal conditions at a higher position than the main bearing of the engine, and In an emergency, the oil remaining in the oil reservoir below the lowest oil level that can be consumed is guided from the lower part of the oil reservoir by gravity to the inner hole of the rotating shaft supported by the main bearing at the front of the engine. means, a plurality of axial grooves provided on the inner surface of the inner hole for axially moving oil dripped into the inner hole, and openings from the bottom of each groove to the outer surface through the wall of the rotating shaft. The present invention relates to an emergency oil supply system for an aircraft gas turbine engine, characterized in that an oil hole is provided for supplying oil in the groove to the main bearing.

[0006]

[Operation] In an emergency, for example, if the oil supply pipe is damaged, the oil in the oil reservoir will immediately drop to the lowest oil level under normal conditions, that is, the level of the oil filler port, but the oil led from the bottom of the oil reservoir will fall naturally. The oil fell from the emergency oil supply nozzle into the rotating shaft, and oil spouted out from the hole in the rotating shaft wall due to the action of centrifugal force along the multiple grooves in the inner hole of the rotating shaft and onto the main bearing. Refuel. This refueling continues until the oil reservoir is completely depleted, allowing the engine to continue operating for several minutes, which is necessary for an emergency landing.

[0007]

DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 is a perspective view of a first embodiment of an emergency refueling system according to the present invention. In the figure, 1 is an oil reservoir provided at a higher position than the oil chamber for the main bearing of the engine, 3 is an oil sump, 4 is an oil jet nozzle connected to the side of the oil reservoir 1, 5 is a main bearing,
7 is an emergency refueling nozzle connected to the bottom of oil reservoir 1, 9
10 is a rotating shaft rotatably held by the main bearing 5, and 10 is an oil reservoir 1 and an oil jet nozzle 4.
11 is the opening of the oil supply pipe 10 into the oil reservoir 1, that is, at the level of the oil supply port; 12 is the oil supply pump provided in the oil supply pipe 10; 13 is the oil supply pipe provided in the oil supply pipe 10; An oil drain pump 14a installed in an oil drain pipe leading from the oil sump to the upper part of the oil reservoir 1
, 14b are oil strainers provided at each oil filler port.

The main reasons why lubrication is interrupted during normal operation are as follows. (1) Oil loss due to damage to the oil supply pump and oil supply system or oil supply interruption (2) Oil loss due to damage to the oil supply pump and oil drainage system (3) Oil loss from the oil chamber containing the bearing (4)
Oil loss due to damage to the oil reservoir Normally, in order to improve the separation of air bubbles in the oil, it is designed not to use oil below approximately one-third of the capacity of the oil reservoir, that is, the level of the oil filler port of the oil reservoir. Therefore, in the cases (1), (2), and (3) above, it is possible to use the residual oil below the level of the oil filler port as emergency oil. Case (4) is considered to be ignored because it is extremely unlikely and the possibility cannot be excluded even if a conventional emergency oil reservoir is used. Next, it is assumed that oil supply in an emergency is not circulated, that is, it is leaked to the outside, so it is important to efficiently distribute a small amount of oil to multiple parts. This embodiment was proposed based on this idea.

In FIG. 1, during normal operation, oil reservoir 1
The oil pressurized by the oil supply pump 12 is injected from the oil jet nozzle 4 into the rotating shaft 9, travels along a plurality of grooves provided on the inner surface of the inner hole of the rotating shaft, and is pushed against the wall by the action of centrifugal force. The main bearing 5 is supplied with oil from a hole provided in the main bearing 5. In an emergency, for example, if the oil supply pipe 10 is damaged, the oil in the oil reservoir 1 will immediately drop to the level 11 at the oil filler port, but the oil led from the bottom of the oil reservoir 1 will naturally fall from the emergency oil supply nozzle 7 to the rotating shaft. The lubricant drops into the shaft, travels along a plurality of grooves provided on the inner surface of the inner hole of the rotating shaft, and is ejected from a hole provided in the wall under the action of centrifugal force to supply the main bearing 5 with oil. This refueling continues to function until the oil in the oil reservoir 1 is completely exhausted, so that the engine can continue to operate for several minutes required for an emergency landing.

FIG. 2 is a cross-sectional view of a second embodiment of the present invention, in which the above-mentioned oil supply system is applied to a front bearing chamber of an aircraft gas turbine engine. 9a is a rotating shaft connected to the gas generator, 9b is a rotating shaft of an output shaft, 9c is a rotating shaft connected to an output gear, 5a, 5b are roller bearings of the main bearing, 5c is a ball bearing of the main bearing, 15a, 15b
15c is an oil supply hole for the roller bearing, 15c is an oil supply hole for the ball bearing, and 16 is an oil scoop nut. Since the other members correspond to the members of the first embodiment, they are given the same reference numerals and the description thereof will be omitted. In this embodiment, the upper part of the gearbox is designed to be integrated with the oil reservoir, thereby eliminating the possibility of oil loss due to damage to piping, etc.

Each of the embodiments detailed above brings about the following effects. (1) The emergency oil reservoir that was conventionally required is no longer necessary, reducing weight and cost. (2) The multiple emergency oil nozzles that were previously required can be reduced to one. (3) Pressurized air for the emergency oil mist that was conventionally required is no longer required, and the breather system for releasing air from the oil chamber can be downsized.

0012

Effects of the Invention In the emergency refueling system for an aircraft gas turbine engine of the present invention, an oil reservoir that supplies lubricating oil during normal times is installed at a higher position than the main bearing of the engine, and the oil reservoir supplies lubricating oil during normal times. means for guiding the oil remaining in the oil reservoir below the lowest oil level that can be carried out from the lower part of the oil reservoir to the inner hole of the rotating shaft supported by the main bearing at the front of the engine by gravity in an emergency; A plurality of axial grooves are provided on the inner surface of the inner hole and allow oil dripped into the inner hole to move in the axial direction, and the grooves penetrate the wall of the rotating shaft from the bottom of each groove and open to the outer surface. There is an oil hole that supplies the oil inside to the main bearing, so the structure is simple.
It is possible to provide a small, lightweight, and low-cost emergency refueling device.

[Brief explanation of the drawing]

FIG. 1 is a perspective view of a first embodiment of the present invention.

FIG. 2 is a sectional view of a second embodiment of the invention.

FIG. 3 is a perspective view of a conventional emergency refueling device.

[Explanation of symbols]

1 Oil reservoir 2 Emergency oil reservoir 3
oil sump 4
Oil jet nozzles 5a, 5b, 5c
Main bearing 6 Compressed air 7 Emergency oil supply nozzle 7X Emergency oil jet nozzle 8a, 8b, 8c
Oil mist 9, 9a, 9b, 9c Rotating shaft

Claims (1)

[Claims] Claim 1: An oil reservoir that supplies lubricating oil during normal operation is installed at a higher position than the main bearing of the engine,
In an emergency, the oil remaining in the oil reservoir below the lowest oil level that can normally be consumed in the oil reservoir is dropped by gravity to the rotating shaft supported by the main bearing at the front of the engine. A means for guiding the oil into the inner hole, a plurality of axial grooves provided on the inner surface of the inner hole to move the oil dripped into the inner hole in the axial direction, and a means for passing through the wall of the rotating shaft from the bottom of each groove. 1. An emergency oil supply system for an aircraft gas turbine engine, characterized in that an oil hole is provided which opens to the outside of the groove and supplies oil in the groove to the main bearing.