Rotational flow cooling type flame tube

Abstract

The utility model provides a rotational flow cooling type flame tube, which comprises a flame tube inner layer and a flame tube outer layer, and is characterized in that a spiral flow deflector is arranged on the outer wall surface of the flame tube inner layer, a gas film groove is formed in the flame tube inner layer along the spiral direction of the flow deflector, and a cooling hole is formed in the flame tube outer layer along the spiral direction of the flow deflector. According to the designed cooling mode, the heat exchange intensity is improved, the service life of the combustion chamber of the gas turbine is prolonged, and meanwhile overlarge thermal stress caused by overhigh temperature and uneven distribution of the wall face of the flame tube is avoided.

Description

Technical Field

[0001] The utility model relates to the field of gas turbine combustion chambers, in particular to a swirl cooling type flame tube. Background Art

[0002] As one of the most important components in a gas turbine, the combustion chamber is subject to a large heat load and thermal shock on the inner wall of the flame tube under high-temperature combustion conditions. The working environment is also very harsh. Excessively high wall temperatures of the flame tube can cause erosion inside the flame tube. The effectiveness of the cooling film depends greatly on the degree of adhesion of the film to the wall and the interaction between the mainstream flue gas and the cooling film. The current cooling method mainly flows the cooling gas directly into the combustion chamber through the cooling holes of the flame tube to form a cooling film. However, the cooling time of the cooling gas in the flame tube is short, and the film cannot be well attached to the inner wall of the flame tube, making it increasingly difficult to adapt to the development needs of high-performance aircraft engines. Therefore, how to reasonably reduce the wall temperature of the combustion chamber flame tube and improve the degree of adhesion of the film to the wall within a certain range is particularly important. Ensuring the reliability of the work and its life is a problem that needs to be solved in the design of the flame tube of the gas turbine combustor.

[0003] Therefore, those skilled in the art provide a swirl-cooled flame tube to solve the problems raised in the above background technology. Utility Model Content

[0004] In order to overcome the problems existing in the related art to at least a certain extent, the purpose of the present invention is to provide a swirl cooling type flame tube, which helps to enhance the heat exchange effect between the flame tube wall and the cooling gas.

[0005] To achieve the above objectives, the technical solution of this utility model is as follows:

[0006] A swirl-cooled flame tube comprises an inner layer and an outer layer of the flame tube, and is characterized in that a spiral guide vane is provided on the outer wall of the inner layer of the flame tube, an air film groove is provided on the inner layer of the flame tube along the spiral direction of the guide vane, and a cooling hole is provided on the outer layer of the flame tube along the spiral direction of the guide vane.

[0007] Preferably, the air film groove has a square notch, and the air film groove is arranged obliquely on the inner side of the inner layer of the flame tube.

[0008] Preferably, the inner layer of the flame tube and the outer layer of the flame tube are annular.

[0009] Preferably, the cooling hole is circular.

[0010] The beneficial effects of the utility model are:

[0011] The present application provides a swirl cooling flame tube based on the actual product application of the flame tube. The structure is novel. The cooling air passing through the cooling hole and the cooling air flowing from the flame tube interlayer are mixed in the flame tube, impacting the cooling guide vanes, thereby enhancing the heat exchange effect of the inner wall of the flame tube. After mixing, the cooling air flows around the flame tube in the direction of the guide vanes, thereby increasing the heat exchange time of the cooling air in the flame tube. The cooling air flowing out through the air film groove forms an air film that adheres to the inner wall of the flame tube, thereby forming good air film cooling. The cooling method designed by the utility model improves the heat exchange intensity and the service life of the gas turbine combustion chamber, while avoiding excessive thermal stress caused by excessive temperature and uneven distribution of the flame tube wall.

[0012] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0014] Figure 1 It is a structural diagram of a swirl cooling flame tube;

[0015] Figure 2 It is a schematic diagram of the structure of the inner layer of a swirl-cooled flame tube;

[0016] Figure 3 yes Figure 1 A partial enlarged schematic diagram;

[0017] In the figure: 1-inner layer of flame tube, 2-outer layer of flame tube, 3-guide vane, 4-air film groove, 5-cooling hole, 6-slot. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0019] Combined with reference Figure 1-3The utility model provides a technical solution: a swirl cooling flame tube, comprising a flame tube inner layer 1 and a flame tube outer layer 2, characterized in that: the outer wall surface of the flame tube inner layer 1 is provided with a spiral guide vane 3, the flame tube inner layer 1 is provided with an air film groove 4 along the spiral direction of the guide vane 3, the flame tube outer layer 2 is provided with a cooling hole 5 along the spiral direction of the guide vane 3, the notch 6 of the air film groove 4 is square, and the air film groove 4 is inclined on the inner side of the flame tube inner layer 1, and the flame tube inner layer 1 and the flame tube outer layer 2 are annular.

[0020] Working principle: The cooling air is divided into two paths, one path flows through the cooling hole 5, and the other path flows in from the flame tube interlayer. The two paths of cooling air are mixed in the flame tube and impact the cooling guide vane 3, thereby enhancing the heat exchange efficiency of the inner wall of the flame tube. The mixed cooling air flows around the flame tube in the direction of the guide vane 3, thereby increasing the heat exchange time of the cooling air in the flame tube. The cooling air evenly cools the flame tube wall, and the cooling air flowing out through the air film groove 4 forms an air film that adheres to the inner wall of the flame tube inner layer 1, thereby forming good air film cooling.

[0021] Matters not covered in this utility model are known technologies.

[0022] It can be understood that the same or similar parts of the above embodiments can be referenced to each other, and the contents not described in detail in some embodiments can refer to the same or similar contents in other embodiments.

[0023] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A swirl-cooled flame tube, comprising a flame tube inner layer and a flame tube outer layer, characterized in that: The outer wall surface of the inner layer of the flame tube is provided with a spiral guide vane, the inner layer of the flame tube is provided with an air film groove along the spiral direction of the guide vane, and the outer layer of the flame tube is provided with a cooling hole along the spiral direction of the guide vane.

2. The swirl cooling flame tube according to claim 1, characterized in that: The air film groove has a square notch, and the air film groove is tilted on the inner side of the inner layer of the flame tube.

3. The swirl cooling flame tube according to claim 1, characterized in that: The inner layer of the flame tube and the outer layer of the flame tube are ring-shaped.

4. The swirl cooling flame tube according to claim 1, characterized in that: The cooling hole is circular.

Images