CN106321166A - Gas turbine supporting column cooling structure - Google Patents

Abstract

The invention relates to the technical field of gas turbine air and cooling systems, in particular to a gas turbine support column cooling structure. The gas turbine support column cooling structure includes a support column, an outer cylinder and an inner cylinder, the support column passes through the outer cylinder and the inner cylinder, one end of the support column is connected to the bearing seat, and the other end is connected to the outer cylinder , the outside of the support column is sequentially sleeved with a first heat insulation sleeve and a second heat insulation sleeve, and a first cooling passage is formed between the first heat insulation sleeve and the support column, and the first heat insulation sleeve and the second heat insulation sleeve The second cooling channel is formed between the sleeves, through the two cold air channels, the heat transfer from the hot gas channel to the support column can be effectively reduced, the temperature of the support column can be reduced, the working environment of the support column can be improved, the service life of the support column can be improved, and at the same time, the intrusion can be reduced. The gas temperature in the bearing seat cavity improves the working environment of the instruments, lubricating oil and bearings in the bearing seat, and improves the operating life and safety of the gas turbine.

Description

A gas turbine support column cooling structure

technical field

The invention relates to the technical field of gas turbine air and cooling systems, in particular to a gas turbine support column cooling structure.

Background technique

Industrial gas turbines mainly include three major components: compressor, combustor and turbine. After the air enters the compressor, it is compressed into high-temperature and high-pressure air, which is supplied to the combustion chamber for fuel combustion, and the high-temperature and high-pressure gas generated expands in the turbine to perform work. Among them, the disc, moving blade, shaft and the attached rotating parts are collectively called the rotor, and other non-rotating parts are collectively called the stator. The rotor is supported on the bearing housing through radial bearings, and the bearing housing is directly or indirectly supported on the external cylinder block of the gas turbine through supporting columns. Finally the external cylinder is supported on the foundation by support columns.

Due to the requirements of the rotor design of mainstream gas turbines in the world today, one of the radial support bearings is generally designed near the turbine outlet, so the support column here must inevitably pass through the hot gas passage with a higher temperature, and the temperature of the support column Too high will affect its strength and service life, and ultimately affect the operation safety and economy of the entire gas turbine. With the development of gas turbine technology, the airflow temperature near the turbine outlet is getting higher and higher. At present, the turbine outlet temperature of mainstream "F" class gas turbines in the world has reached about 600°C. Therefore, how to reduce the temperature of the support column has become an urgent problem. The problem.

Contents of the invention

(1) Technical problems to be solved

The purpose of the present invention is to provide a gas turbine support column cooling structure that can further reduce the temperature of the support column, reduce the heat transfer from the hot gas channel to the support column, and solve the problem that the existing gas turbine support column has a high temperature that affects the strength and use of the support column The question of longevity.

(2) Technical solution

In order to solve the above technical problems, the present invention provides a gas turbine support column cooling structure, including a support column, an outer cylinder and an inner cylinder, the support column passes through the outer cylinder and the inner cylinder, and one end of the support column It is connected to the bearing seat, and the other end is connected to the outer cylinder. The outer side of the support column is sequentially provided with a first heat insulation sleeve and a second heat insulation sleeve, and a first heat insulation sleeve and a support column are formed between the first heat insulation sleeve and the support column. A cooling channel, a second cooling channel is formed between the first heat insulation sleeve and the second heat insulation sleeve.

Preferably, the inner cylinder includes an inner cylinder inner wall and an inner cylinder outer wall, a third cooling passage is formed between the inner cylinder inner wall and the inner cylinder outer wall, and the third cooling passage communicates with the second cooling passage, The third cooling channel communicates with the hot gas channel through the second air hole.

Preferably, the first cooling channel communicates with a bearing seat cavity for accommodating a bearing seat, and the bearing seat cavity communicates with the hot gas channel through a first vent hole.

Preferably, one end of the first heat insulation sleeve is connected to the outer cylinder, and the other end is connected to the inner wall of the inner cylinder.

Preferably, one end of the second heat insulation sleeve is connected to the outer cylinder, and the other end is connected to the outer wall of the inner cylinder.

Preferably, the outer cylinder is provided with a first air supply port and a second air supply port, and the first air supply port communicates with the first cooling channel, and the second air supply port communicates with the The second cooling channels are connected.

Preferably, the second air hole, the first air hole, the first air supply hole and the second air supply hole are all provided with a flow regulating device.

(3) Beneficial effects

The above-mentioned technical solution of the present invention has the following advantages: the gas turbine support column cooling structure provided by the present invention includes a support column, an outer cylinder and an inner cylinder, the support column passes through the outer cylinder and the inner cylinder, and the support column One end is connected to the bearing seat, and the other end is connected to the outer cylinder. The outer side of the support column is successively provided with a first heat insulation sleeve and a second heat insulation sleeve, and the first heat insulation sleeve and the support column form a first Cooling channel, the second cooling channel is formed between the first heat insulation sleeve and the second heat insulation sleeve, through the two cold air channels, the heat transfer from the hot gas channel to the support column can be effectively reduced, the temperature of the support column can be reduced, and the stability of the support column can be improved. Improve the working environment and improve the service life of the support column.

The first cooling channel communicates with the bearing seat cavity for accommodating the bearing seat, reduces the temperature of the gas entering the bearing seat cavity, improves the working environment of the bearing, and increases the service life and safety of the unit.

Description of drawings

Fig. 1 is a schematic longitudinal sectional view of a gas turbine support column cooling structure according to an embodiment of the present invention;

Fig. 2 is a sectional view along A-A of Fig. 1 .

Wherein, the direction of the arrow in FIG. 1 represents the direction of cooling gas flow.

In the figure: 1: outer cylinder; 2: support column; 3: first heat insulation sleeve; 31: first cooling channel; 4: second heat insulation sleeve; 41: second cooling channel; 5: inner cylinder; 51: Inner wall of inner cylinder; 52: Outer wall of inner cylinder; 53: Third cooling channel; 54: Second air hole; 55: First air hole; 6: Outer cylinder; 7: Bearing housing cavity; 8: Hot gas channel; 9: Bearing seat; 10: bearing; 11: first air supply port; 12: second air supply port; 13: rotor.

detailed description

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

It should be noted that the terms "center", "vertical", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal" , "Top", "Bottom", "Inner", "Outer" and other indicated orientations or positional relationships are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating Or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be construed as limiting the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes, and It should not be read as indicating or implying relative importance.

In the description of the present invention, it should be noted that unless otherwise specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection. Connected, or integrally connected; it can be mechanically connected or electrically connected; it can be directly connected or indirectly connected through an intermediary, and it can be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention in specific situations.

As shown in Figures 1 and 2, a bearing 10 is provided near the turbine outlet of the gas turbine, and the bearing 10 is installed on the bearing seat 9. The gas turbine support column cooling structure provided by the embodiment of the present invention includes a support column 2, an outer The cylinder 6 and the inner cylinder 5, the support column 2 passes through the outer cylinder 6 and the inner cylinder 5, one end of the support column 2 is connected with the bearing seat 9, and the other end is connected with the outer cylinder 1, and the bearing seat 9 connects the rotor 13 through the support column 2 The weight is transferred to the outer cylinder 1, and the outer cylinder 1 is connected to the foundation through an external support. The outer side of the support column 2 is sequentially provided with a first heat insulation sleeve 3 and a second heat insulation sleeve 4, and the first heat insulation sleeve 3 and the support The first cooling passage 31 is formed between the columns 2, and the second cooling passage 41 is formed between the first heat insulation sleeve 3 and the second heat insulation sleeve 4. The two cold air passages effectively reduce the impact of the hot gas passage 8 on the support column 2. Heat transfer reduces the temperature of the support column 2, improves the working environment of the support column, and increases the service life of the support column 2.

Wherein, the outer cylinder 6 is a single-layer annular cylinder, and the inner cylinder 5 is composed of an outer wall 52 of the inner cylinder and an inner wall 51 of the inner cylinder, and a third cooling channel 53 is formed between the outer wall 52 of the inner cylinder and the inner wall 51 of the inner cylinder. Both the outer cylinder 6 and the outer wall 52 of the inner cylinder have holes, and the first heat insulation sleeve 3 passes through the holes and connects with the inner wall 51 of the inner cylinder. 8. There is a gap between the first heat insulation sleeve 3 and the outer wall 52 of the inner cylinder, the third cooling channel 53 communicates with the second cooling channel 41 through the gap, and the third cooling channel 53 communicates with the hot gas channel 8 through the second vent hole 54 Communication, so that cold air can enter the third cooling passage 53 through the second cooling passage 41 , and then enter the hot gas passage 8 through the second vent hole 54 .

In order to reduce the temperature in the bearing housing cavity 7 at the same time, preferably, as shown in FIG. The hot gas channel 8 communicates, so that cold air flows into the hot gas channel 8 through the first cooling channel 31, the bearing housing cavity 7 and the first vent hole 55 arranged at the front end of the bearing housing cavity 7, and reduces the temperature of the passing parts.

In order to ensure that the first cooling channel 31 and the second cooling channel 41 are independent of each other, so that the cold air flows according to a predetermined route, preferably, as shown in Figure 1, one end of the first heat insulation sleeve 3 is connected to the outer cylinder 1, and the other end Connected to the inner wall 51 of the inner cylinder, also in order to ensure that the second cooling channel 41 is relatively independent from the hot gas channel 8 (except for the set second vent hole 54, try to keep the non-communication state), preferably, the second heat insulation sleeve One end of 4 is connected with the outer cylinder 6, and the other end is connected with the outer wall 52 of the inner cylinder.

In order to facilitate cooling, preferably, as shown in FIG. 1 , a first air supply port 11 and a second air supply hole 12 are provided on the outer cylinder 1, and the first air supply port 11 communicates with the first cooling channel 31 , and the second air supply port 11 communicates with the first cooling channel 31 . The second air supply port 12 is connected with the second cooling channel 41, so that the cold air forms two independent flow paths. The first flow path is that the cold air enters the first cooling channel 31 from the first air supply port 11, and then passes through the bearing housing cavity 7 1. The first air hole 55 flows into the hot gas channel 8; the second flow path is that cold air enters the second cooling channel 41 from the second air supply port 12, and then flows into the hot gas channel through the third cooling channel 53 and the second air hole 54 8. The cold air takes away the heat at the place where it flows, reduces the heat transferred to the support column 2 by the air flow in the hot gas channel 8, and improves the service life of the support column 2.

In order to make the gas flow can be adjusted according to the actual situation, preferably, a flow regulating device is provided at the second air hole 54, the first air hole 55, the first air supply hole 11 and the second air supply hole 12 for controlling the gas flow rate here. Through the flow of gas, the specific flow regulating device can be a flow regulating valve and other devices that can control the flow.

To sum up, the gas turbine support column cooling structure provided by the present invention includes a support column, an outer cylinder and an inner cylinder, the support column passes through the outer cylinder and the inner cylinder, and one end of the support column is connected to the bearing seat The other end is connected to the outer cylinder. The outer side of the support column is sequentially provided with a first heat insulation sleeve and a second heat insulation sleeve, and a first cooling channel is formed between the first heat insulation sleeve and the support column. The first The second cooling channel is formed between the heat insulation sleeve and the second heat insulation sleeve, through the two cold air channels, the heat transfer from the hot gas channel to the support column can be effectively reduced, the temperature of the support column can be reduced, the working environment of the support column can be improved, and the support can be improved. At the same time, the temperature of the gas entering the bearing housing cavity along the supporting column is reduced, and the working environment of the measuring instrument and lubricating oil system in the bearing housing is improved, thereby indirectly improving the service life, reliability and safety of the gas turbine.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: it can still be Modifications are made to the technical solutions described in the foregoing embodiments, or equivalent replacements are made to some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims (7)

1. A support column cooling structure for a gas turbine, characterized in that: it comprises a support column (2), an outer cylinder (6) and an inner cylinder (5), and the support column (2) passes through the outer cylinder (6) and The inner cylinder (5), one end of the support column (2) is connected with the bearing seat (9), and the other end is connected with the outer cylinder (1), and the outer side of the support column (2) is sequentially sleeved with first The heat insulation sleeve (3) and the second heat insulation sleeve (4), and the first cooling channel (31) is formed between the first heat insulation sleeve (3) and the support column (2), and the first heat insulation A second cooling passage (41) is formed between the sleeve (3) and the second heat insulation sleeve (4). 2. The gas turbine supporting column cooling structure according to claim 1, characterized in that: the inner cylinder (5) comprises an inner cylinder inner wall (51) and an inner cylinder outer wall (52), and the inner cylinder inner wall (51) and A third cooling passage (53) is formed between the outer walls (52) of the inner cylinder, and the third cooling passage (53) communicates with the second cooling passage (41), and the third cooling passage (53) passes through The second air hole (54) communicates with the hot gas channel (8). 3. The gas turbine support column cooling structure according to claim 2, characterized in that: the first cooling channel (31) communicates with the bearing housing cavity (7) for accommodating the bearing housing (9), and the bearing housing The cavity (7) communicates with the hot gas channel (8) through the first air hole (55). 4. The gas turbine support column cooling structure according to claim 3, characterized in that: one end of the first heat insulation sleeve (3) is connected to the outer cylinder (1), and the other end is connected to the inner wall (51) of the inner cylinder. 5. The gas turbine support column cooling structure according to claim 4, characterized in that: one end of the second heat insulation sleeve (4) is connected to the outer cylinder (6), and the other end is connected to the outer wall (52) of the inner cylinder. 6. The gas turbine support column cooling structure according to any one of claims 1-5, characterized in that: the outer cylinder (1) is provided with a first air supply port (11) and a second air supply port (12 ), and the first air supply port (11) communicates with the first cooling passage (31), and the second air supply port (12) communicates with the second cooling passage (41). 7. The gas turbine supporting column cooling structure according to claim 5, characterized in that: the second air hole (54), the first air hole (55), the first air supply hole (11) and the second air supply hole ( 12) All are equipped with flow regulating devices.