A gas turbine combustion chamber guide bushing

Abstract

A gas turbine combustor guide bushing belongs to the field of gas turbine combustor bushing structures. It comprises a flange portion and a shell portion. The flange portion comprises a front flange and a rear flange. The front flange and rear flange are welded to the front and rear sides of the shell portion, respectively. The front end of the shell portion is fixed to the high-pressure compressor outer casing via the front flange, and the rear end of the shell portion is fixed to the high-pressure compressor rear diffuser via the rear flange. The shell portion comprises a shroud and a fairing, which are alternately welded to form a cylindrical shell structure. This solves the problem that current combustor bushings have no guiding effect on airflow, and compressed air at the compressor outlet flows back through the bushing into the flame tube, which is prone to uneven air flow, speed, and direction. The curved surface structure of the guide bushing allows the air at the high-pressure compressor outlet to pass through, thereby stabilizing and guiding the air flow, reducing turbulence when air enters the flame tube, and ensuring more stable air within the flame tube.

Description

Technical Field

[0001] The invention relates to a gas turbine combustion chamber guide liner and belongs to the field of gas turbine combustion chamber liner structures. Background Art

[0002] A gas turbine is an internal combustion engine that uses air as a working fluid, converting the fuel's energy into useful work. Fuel combustion occurs within the combustion tube. The compressor draws in air from the outside and gradually increases its pressure. The compressed air enters the combustion tube, mixes with the injected fuel, and burns to produce high-temperature, high-pressure gas. This gas is then passed into the turbine to produce work and output.

[0003] [As a combustion medium, the air flow rate, flow velocity and flow direction have a vital impact on the fuel combustion effect. At present, the annular tube type combustion chamber liners are mostly simple cylindrical and have no guiding effect on the airflow. The compressed air at the compressor outlet flows back through the liner and enters the flame tube, which is prone to uneven air flow, velocity and direction, leading to local combustion of the flame tube, incomplete fuel combustion and many other problems, which in turn affect the unit emissions and unit efficiency.

[0004] Therefore, it is urgent to propose a new type of gas turbine combustion chamber guide liner, in which the air at the compressor outlet is rectified through the combustion chamber liner, mixed with the fuel in the flame tube through the swirler and then burned to solve the above technical problems. Summary of the Invention

[0005] The purpose of the research and development of this invention is to solve the problem that the current annular tube type combustion chamber liners are mostly simple cylindrical and have no guiding effect on the airflow. The compressed air at the compressor outlet flows back through the liner and enters the flame tube, which is prone to uneven air flow, speed, and direction. In serious cases, it may even lead to local combustion of the flame tube and insufficient combustion of fuel, thereby affecting the unit emissions and unit efficiency. A brief overview of the invention is given below to provide a basic understanding of certain aspects of the invention. It should be understood that this overview is not an exhaustive overview of the invention. It is not intended to determine the key or important parts of the invention, nor is it intended to limit the scope of the invention.

[0006] The technical solution of the present invention:

[0007] A gas turbine combustion chamber guide bushing includes a flange portion and a shell portion, wherein the flange portion includes a front end flange and a rear end flange, and the front end flange and the rear end flange are welded to the front and rear sides of the shell portion respectively. The front end of the shell portion is fixed to the outer casing of the high-pressure compressor through the front end flange, and the rear end of the shell portion is fixed to the rear end diffuser of the high-pressure compressor through the rear end flange. The shell portion includes a shroud and a fairing, and the shroud and the fairing are alternately welded to form a cylindrical shell structure.

[0008] Preferably, the number of the shields and fairings is 8 each, which are alternately welded to form a cylindrical shell structure.

[0009] Preferably: the diameter ratio of the front end and the rear end of the shell part is 1.2:1, the front end of the shell part forms an angle of 40° to 45° with its center line, the rear end of the shell part forms an angle of 2° to 3° with its center line, and the middle of the shell part adopts an arc transition.

[0010] Preferably, the fairing is manufactured by a stamping method.

[0011] Preferably, the center of the fairing is designed with an arc-shaped protrusion of R35 to R40, and is transitioned to the edge with an arc.

[0012] Preferably, in the 2° to 3° flat angle area of ​​the shield, a corrugation is designed every 60 mm to 90 mm, the height of the corrugation is 2 mm to 3 mm, and the arc radius of the corrugation is R2 to R3. Beneficial effects

[0013] 1. The present invention allows the air at the high-pressure compressor outlet to pass through the curved surface structure of the guide bushing, which has the effect of stabilizing and guiding the air flow, reducing the turbulence problem of the air entering the flame tube;

[0014] 2. The front end of the shell portion of the present invention forms an angle of 40° to 45° with its centerline, making the air flow channel area around the flame tube basically uniform, achieving uniform air flow between the guide sleeve and the flame tube, and ensuring more stable air in the flame tube;

[0015] 3. The corrugated structure designed on the shield of the present invention effectively absorbs the expansion of the guide bushing caused by high-temperature air, improves the service life of the guide bushing, and avoids many problems such as local combustion of the flame tube and incomplete combustion of fuel. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a three-dimensional diagram of a gas turbine combustion chamber guide liner;

[0017] Figure 2 This is a front view of a gas turbine combustion chamber guide liner;

[0018] Figure 3 The present invention is a top view of a gas turbine combustion chamber guide liner;

[0019] Figure 4 It is a schematic structural diagram of the protective cover of the present invention;

[0020] Figure 5 It is a front view of the fairing of the present invention;

[0021] Figure 6is a plan view of a fairing of the present invention;

[0022] Figure 7 It is a perspective view of the fairing of the present invention.

[0023] In the figure: 1-shell part, 2-front end flange, 3-rear end flange, 4-shield, 5-fairing. DETAILED DESCRIPTION

[0024] To make the objectives, technical solutions, and advantages of the present invention more clearly apparent, the present invention is described below using specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely illustrative and are not intended to limit the scope of the present invention. In addition, in the following description, descriptions of well-known structures and technologies are omitted to avoid unnecessary confusion of the concepts of the present invention.

[0025] The connections mentioned in the present invention are divided into fixed connections and detachable connections. The fixed connection refers to a non-detachable connection, including but not limited to conventional fixed connection methods such as hem connection, rivet connection, adhesive connection, and welding connection. The detachable connection refers to but not limited to conventional detachable connection methods such as threaded connection, snap connection, pin connection, and hinge connection. When the specific connection method is not clearly specified, it is assumed that at least one connection method can always be found among the existing connection methods to achieve the function. Those skilled in the art can choose according to their needs. For example, a welded connection is selected for a fixed connection, and a hinge connection is selected for a detachable connection.

[0026] Combine Figure 1-Figure 7 To illustrate this embodiment, a gas turbine combustion chamber guide sleeve according to this embodiment includes a flange portion and a shell portion 1, and the shell portion 1 and the flange portion are welded to form a combustion chamber guide sleeve; the air at the high-pressure compressor outlet passes through the curved surface structure of the guide sleeve, which has the effect of stabilizing and guiding the air flow, thereby reducing the turbulence problem of the air entering the flame tube.

[0027] The flange part includes a front end flange 2 and a rear end flange 3. The front end flange 2 and the rear end flange 3 are welded on the front and rear sides of the shell part 1 respectively. The front end of the shell part 1 is fixed to the outer casing of the high-pressure compressor through the front end flange 2, and the rear end of the shell part 1 is fixed to the rear end diffuser of the high-pressure compressor through the rear end flange 3. The shell part 1 includes a shroud 4 and a fairing 5. The number of the shroud 4 and the fairing 5 are both 8. The shroud 4 and the fairing 5 are alternately welded to form a cylindrical shell structure.

[0028] The diameter ratio of the front end and the rear end of the shell part 1 is 1.2:1, and the front end of the shell part 1 forms an angle of 40° to 45° with its center line, so that the area of ​​the air circulation channel around the flame tube is basically the same, realizing uniform air flow between the guide sleeve and the flame tube, ensuring that the air in the flame tube is more stable, the rear end of the shell part 1 forms an angle of 2° to 3° with its center line, and the middle of the shell part 1 adopts an arc transition.

[0029] The fairing 5 is manufactured by a stamping method. The center of the fairing 5 is designed with an arc-shaped protrusion of R35 to R40, and the arc is used to transition to the edge.

[0030] In the 2°~3° angle flat area of ​​the shield 4, a corrugation is designed every 60mm~90mm. The height of the corrugation is 2mm~3mm, and the arc radius of the corrugation is R2~R3, which effectively absorbs the expansion problem of the guide bushing caused by high-temperature air, improves the service life of the guide bushing, and avoids many problems such as local combustion of the flame tube and insufficient combustion of fuel.

[0031] Working principle:

[0032] When the gas turbine is in operation, air at the high-pressure compressor outlet passes through a gas turbine combustion chamber guide sleeve of this embodiment and flows back into the flame tube to participate in combustion and cooling.

[0033] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be permuted and combined. Those skilled in the art can exhaust all possibilities based on the mathematical knowledge of permutations and combinations. Therefore, the present invention will no longer describe the technical solutions after permutations and combinations one by one, but it should be understood that the technical solutions after permutations and combinations have been disclosed by the present invention.

[0034] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A gas turbine combustion chamber guide liner, characterized in that: The invention comprises a flange part and a shell part (1), wherein the flange part comprises a front end flange (2) and a rear end flange (3), the front end flange (2) and the rear end flange (3) are welded to the front and rear sides of the shell part (1), respectively, the front end of the shell part (1) is fixed to the outer casing of the high-pressure compressor through the front end flange (2), and the rear end of the shell part (1) is fixed to the rear end diffuser of the high-pressure compressor through the rear end flange (3), the shell part (1) comprises a shroud (4) and a fairing (5), and the shroud (4) and the fairing (5) are alternately welded to form a cylindrical shell structure; the diameter ratio of the front end to the rear end of the shell part (1) is 1 .2:1, the front end of the shell part (1) forms an angle of 40° to 45° with its center line, the rear end of the shell part (1) forms an angle of 2° to 3° with its center line, and the middle of the shell part (1) adopts an arc transition; the center of the fairing (5) is designed with an arc-shaped protrusion of R35 to R40, and transitions to the edge with an arc; in the flat area of ​​2° to 3° of the shield (4), a corrugation is designed every 60mm to 90mm.

2. The gas turbine combustion chamber guide liner according to claim 1, characterized in that: The number of the guards (4) and fairings (5) is 8, and they are welded alternately to form a cylindrical shell structure.

3. The gas turbine combustion chamber guide liner according to claim 2, characterized in that: The fairing (5) is manufactured by a stamping method.

4. The gas turbine combustion chamber guide liner according to claim 3, characterized in that: The height of the corrugation is 2 mm to 3 mm, and the arc radius of the corrugation is R2 to R3.

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