KR200345962Y1 - Air cooling apparatus for turbo engine - Google Patents

Abstract

The present invention provides a compressor housing portion having a rotatable blade stacked on a rotating shaft, a bearing member rotatably supporting the rotating shaft, and a first portion of compressed air formed on a rotating shaft proximate the blade to flow therein. A plurality of sealing members, a turbine portion provided on a rotating shaft corresponding to the compressor housing portion, a second sealing member provided in proximity to the front and rear of the bearing member, and a plurality of rotary shafts, the compressor housing portion and the turbine portion, respectively. 1. An air cooling apparatus of a turbo engine having two air passages, the plurality of air passages being formed on a rotating shaft, one of which is led to a turbine without passing through a bearing member supporting the rotating shaft, and the other is a rotating shaft. It flows along and flows after cooling a bearing member. Accordingly, the pressure drop in the axial direction of the rotating shaft can be reduced to the maximum, thereby reducing the load on the bearing, thereby greatly improving the stability of the bearing member, and further extending the life of the turbo engine. have.

Description

Air cooling apparatus for turbo engine

The present invention relates to an air cooling apparatus of a turbo engine, and more particularly, to an air cooling apparatus of a turbo engine having an improved air passage structure on a rotating shaft.

In general, a turbo engine is used as an aircraft engine or an industrial engine and the like, and a propulsion force or power is obtained by mixing and then combusting fuel with air compressed by a compressor. Such a turbo engine cools the air by passing it on the bearing member in order to cool the frictional heat of the bearing member during rotation of the rotary shaft.

1 schematically illustrates a portion of a conventional turbo engine 10.

Referring to the drawings, the turbo engine 10 is provided with a rotating shaft 11, and one side of the rotating shaft 11 is provided with a compressor housing part 12 having a plurality of blades 12a. The compressor housing part 12 is provided with an air outlet 12b for discharging the multi-stage compressed air to the combustion chamber 13 side.

The combustion chamber 13 is installed adjacent to the air outlet 12c, and a turbine portion 14 is installed behind the combustion chamber 13. A disk 14a is coupled to the rotary shaft 11 in the turbine portion 14, and a blade 14b is mounted on an outer circumferential surface of the disk 14a.

In addition, an air inlet hole 17a is formed between the blades 12a of the compressor so as to supply a part of air compressed in the stage to the rotary shaft 11. In addition, a sealing member 15 to which the air can move is installed on the rotating shaft 11 adjacent to the blade 12a. The sealing member 15 is a labyrinth type packing structure, and may flow along the axial direction of the rotating shaft 11 in a state where the pressure is dropped in multiple stages.

On the other hand, a bearing member 16 is provided on the rotary shaft 11 to rotatably support the rotary shaft 11.

In the conventional turbo engine 10 having the structure as described above, as the rotary shaft 11 rotates, the blade 12a coupled to the rotary shaft 11 simultaneously rotates at a high speed. When the stacked blades 12a rotate at a high speed, air compressed in multiple stages flows to the combustion chamber 13 through the air outlet 12b.

Subsequently, air introduced into the combustion chamber 13 is mixed with fuel injected from the combustion chamber 12 and ignited to generate gas. This gas is installed on the outer circumferential surface of the disk 14a of the turbine portion 14 and expands rapidly while passing through the blade 14b which rotates at high speed.

Here, the air inlet hole (17a) is provided between the compressor side blade (12a) is a portion of the compressed air flows along the rotary shaft 11, the air exits the air inlet hole (17a) Flow to (11). That is, the air passes along the space between the rotary shaft 11 and the compressor housing part 12 after a predetermined pressure drop occurs while passing through the sealing member 15. The flowed air cools the bearing member 16 which the rotation shaft 11 rotatably supports.

Subsequently, it exits through the air outlet hole 17b formed between the blades 14b of the turbine portion 14.

By the way, the conventional turbo engine 10 is a bearing that rotates at a high speed, while the air compressed from the compressor-side blade (12a) is introduced into the rotating shaft 11 along the air inlet hole (17a) in a relatively high pressure state Cooling air passing through the member 16 prevents significant pressure drop.

Due to this, a significant difference in pressure drop occurs on the rotating shaft 11 and an excessive load acts in the axial direction, which greatly hinders the stability of the bearing member 16 when rotating. As a result, the life of the turbo engine 10 is greatly damaged.

The present invention was devised to solve the above problems, and the cooling of the bearing supporting the rotating shaft and at the same time to reduce the axial load generated in the rotating shaft air cooling of the turbo engine of the turbo engine has been changed The purpose is to provide a device.

1 is a cross-sectional view schematically showing a part of a conventional turbo engine,

2 is a cross-sectional view schematically showing a part of a turbo engine according to an embodiment of the present invention.

<Brief description of symbols for the main parts of the drawings>

10,20. Turbo engine11,21. Axis of rotation

12,22. Compressor housing parts 12a, 22a. blade

12b, 22b. Air outlet13,23. combustion chamber

14,24. Turbine section 14a, 24a. disk

14b, 24b. Blade 15. Sealing member

16,26. Bearing member 17a. Air inlet

17b. Air outlet hole 25a. First sealing member

25b. Second sealing member 27a. 1st air inlet hole

27b. First air outlet hole 27c. 2nd air outlet

28a. Second air inlet hole 28b. Third air outlet

28c. 4th air outlet

The air cooling device of the turbo engine having the above structure includes a rotation shaft; A compressor housing part installed on the rotating shaft and having a plurality of blades capable of rotating at high speed; A bearing member rotatably supporting the rotating shaft; A first sealing member formed on a rotation axis close to the blade and into which a part of compressed air flows; A turbine unit provided on a rotating shaft corresponding to the compressor housing and having a disk on which a plurality of blades are installed on an outer circumferential surface thereof; A second sealing member installed near the front and rear of the bearing member; And a plurality of air passage portions formed in the rotary shaft, the compressor housing portion, and the turbine portion, respectively.

The air passage portion may include a first air passage portion through which a portion of the air compressed from the compressor side blades flows out into the turbine portion without passing through the bearing member, and a portion of the air compressed from the compressor side blades along the rotating shaft. And a second air passage portion flowing through the member to the turbine portion.

Here, the first air passage portion is a first air inlet hole formed between the compressor side blades, a first air outlet hole formed in the upper compressor housing part of the bearing member, and a second air outlet hole formed between the turbine side blades. And a second air inlet hole formed between the compressor side blades, a third air outlet hole formed in a predetermined portion of a rotation shaft adjacent to the bearing member, and a fourth air gap formed between the turbine side blades. It is characterized by having an air outlet hole.

Hereinafter, an air cooling apparatus of a turbo engine according to an exemplary embodiment of the present invention will be described in detail with reference to the accompanying drawings.

2 schematically shows a part of the turbo engine 20 according to the present invention.

Referring to the drawings, the turbo engine 20 is provided with a rotation shaft 21. One side of the rotating shaft 21 is provided with a compressor housing 22. The compressor housing 22 is provided with a multi-stage blade 22a that is coupled to the rotating shaft 21 and capable of high speed rotation. The blade 22a is provided with an air outlet 22b for sending the multi-stage compressed air to the combustion chamber 23 side.

The combustion chamber 23 is installed close to the air outlet 22b to generate gas by mixing inhaled air and fuel. At the rear of the combustion chamber 23, a turbine 24 for expanding the gas supplied from the combustion chamber 23 to high temperature and high pressure is provided. The turbine portion 24 includes a disk 24a coupled to the rotating shaft 21 and a plurality of blades 24b installed on an outer circumferential surface of the disk 24a.

On the other hand, a first sealing member 25a is provided on the rotary shaft 21 adjacent to the compressor-side blade 22a, and a second sealing member 25b is provided on the rotary shaft 21 adjacent to the turbine 24. . The first sealing member 25a serves to supply air along the rotating shaft 21 by dropping the air flowing from the compressor-side blade 22a to a predetermined pressure in multiple stages, and the second sealing member 25b. The air is to seal the air flowing in the air passage to be described later to play a role to flow independently of the low pressure and high pressure air.

According to a feature of the present invention, a plurality of air passages are formed between the rotating shaft 21 and the blades (22a, 24b). The air passage portion includes a first air passage portion through which some of the air compressed from the compressor side blade 22a flows into the rotating shaft 21 without passing through the bearing member 26, and air introduced from the blade 22a. And a second air passage portion flowing out through the bearing member 26.

That is, the first air passage part is provided between the compressor side blades 22a to form a first air inlet hole 27a through which compressed air flows into the rotating shaft 21. A first air outlet hole 27b is formed in the upper compressor housing part 22 of the bearing member 26. Then, a second air outlet hole 27c is formed between the turbine side blades 24b so that the air exiting the first air outlet hole 27b can be discharged to the turbine portion 24 side.

In addition, the second air passage portion is formed in the blade (22a) of the compressor is formed with a second air inlet hole (28a) for introducing the multi-stage compressed air onto the rotary shaft (21). In addition, a third air outlet hole 28b is formed in a predetermined portion of the rotating shaft 21 adjacent to the bearing member 26 so that the air exiting the gap portion of the disk 24a of the turbine part 24 is discharged. A fourth air outlet hole 28c is formed between the blades 24b.

The operation of the air cooling device of the turbo engine 20 according to the present invention configured as described above is as follows.

As the rotating shaft 21 rotates, the blade 22a of the compressor rotates at a high speed. When the multi-stage blades 22a are rotated at high speed, the air compressed in the multistage flows to the combustion chamber 23 side through the compressor-side air outlet 22b.

Subsequently, air introduced into the combustion chamber 23 is mixed with fuel injected from the combustion chamber 22 and ignited to generate gas. The gas expands rapidly while passing through the blade 24b provided on the outer circumferential surface of the disk 24a of the turbine portion 24.

Here, the rotating shaft 21 is subjected to a significant axial load on the bearing member 26 supporting it. Air is supplied from a separate air passage to cool the heat generated by the bearing member 26 due to this load.

That is, the air flowing from the first air inlet hole 27a of the blade 22a passes through the first sealing member 25a and is provided with a predetermined pressure reinforcement, so that the rotary shaft 21 and the compressor housing part 22 are provided. It flows through the space between them. The flowed air exits through the first air outlet hole 27b without passing through the bearing member 26 and is discharged to the second air outlet hole 27c. As a result, the pressure drop is reduced to the maximum at both ends of the rotary shaft 21.

Meanwhile, air passing through the second air inlet hole 28a formed in the blade 22a to cool the bearing member 26 flows along the rotation shaft 21 and is installed at a predetermined portion of the rotation shaft 21. It passes through the third air outlet hole 28b.

Air then passes through the bearing member 26 to cool the bearing member 26 in a high temperature state. The air passing through the bearing member 26 exits to the fourth air outlet hole 28c along the through hole formed in the disk 24a of the turbine portion 24.

As described above, the air cooling device of the turbo engine of the present invention makes a plurality of air passage portions on the rotation shaft, one of which is led to the turbine portion without passing through the bearing member supporting the rotation shaft, and the other is along the rotation shaft. While flowing, the bearing member is cooled and then flowed. Accordingly, the pressure drop in the axial direction of the rotating shaft can be reduced to the maximum, thereby reducing the load on the bearing, thereby greatly improving the stability of the bearing member, and further extending the life of the turbo engine. have.

Although the present invention has been described with reference to one embodiment shown in the drawings, this is merely exemplary, and it will be understood by those skilled in the art that various modifications and equivalent other embodiments are possible. Therefore, the true technical protection scope of the present invention should be defined by the technical spirit of the appended claims.

Claims (3)

Rotation axis; A compressor housing part installed on the rotating shaft and having a plurality of blades capable of rotating at high speed; A bearing member rotatably supporting the rotating shaft; A first sealing member formed on a rotating shaft proximate to the blade and configured to supply pressure along the rotating shaft by dropping air introduced from the blade into multiple stages; A turbine unit provided on a rotating shaft corresponding to the compressor housing unit and having a disk having a plurality of blades installed on an outer circumferential surface thereof; The rotary shaft, the compressor housing part, and the turbine part, respectively; A first air passage portion providing a passage through which some of the compressed air from the compressor-side blade flows out into the turbine portion without passing through the bearing member; and some of the compressed air from the compressor-side blade along the rotating shaft. An air passage portion consisting of a second air passage portion for providing a passage through which the turbine portion flows out; And And a second sealing member installed close to the front and rear of the bearing member and sealing air flowing in the air passage part to induce low and high pressure air to flow independently. The method of claim 1, The first air passage part includes a first air inlet hole formed between the compressor side blades, a first air outlet hole formed in an upper compressor housing part of the bearing member, and a second air outlet hole formed between the turbine side blades. Air cooling device of a turbo engine, characterized in that. The method of claim 1, The second air passage portion may include a second air inlet hole formed between the compressor side blades, a third air outlet hole formed in a predetermined portion of the rotating shaft adjacent to the bearing member, and a fourth air outlet hole formed between the turbine side blades. Air cooling device for a turbo engine, characterized in that provided.