CN219103047U

CN219103047U - Flame tube annular connector

Info

Publication number: CN219103047U
Application number: CN202223549119.3U
Authority: CN
Inventors: 黄卫东; 朱家桢
Original assignee: AVIC Jincheng Nanjing Engineering Institute of Aircraft Systems
Current assignee: AVIC Jincheng Nanjing Engineering Institute of Aircraft Systems
Priority date: 2022-12-29
Filing date: 2022-12-29
Publication date: 2023-05-30
Anticipated expiration: 2032-12-29

Abstract

The utility model belongs to the field of combustion chambers of aviation power devices, and provides a flame tube annular connector. The flame tube comprises a first annular section, a transition section and a second annular section, wherein the transition section and the second annular section are connected with the first annular section and the second annular section, and a circle of small holes are circumferentially formed in the second annular section or the transition section. And the inner side of the first annular section is welded with the outer side of the tail part of the flame tube. The diameter of the second annular section is larger than that of the first annular section, and a turbine guider or a turbine air inlet volute is inserted between the second annular section and the outer wall of the tail of the flame tube. The annular connector of the flame tube is simple and feasible in structure, is suitable for the tail part of the flame tube, and eliminates or reduces the influence of airflow oscillation and thermal stress on the tail part of the flame tube.

Description

Flame tube annular connector

Technical Field

The utility model belongs to the field of combustion chambers of aviation power devices, and relates to a flame tube annular connector.

Background

The flame tube is an important component of the combustion chamber, and outside the flame tube, air flows through a channel between the flame tube and a casing of the combustion chamber, and enters the flame tube from an opening on the flame tube or a cyclone, etc.; in the flame tube, fuel and air are combusted to generate high-temperature fuel gas; at the outlet of the flame tube, the tail part of the flame tube is connected with a turbine guider or a turbine air inlet volute. The flame tube bears the thermal stress of fuel gas in the flame tube, aerodynamic force of air outside the flame tube and aerodynamic force of the fuel gas in the flame tube.

The tail part of the existing flame tube is usually lapped on a turbine guider or a turbine air inlet volute, and the tail part of the flame tube is easy to crack and the like under the alternating load of the oscillating action of airflow and thermal stress, so that the use reliability and service life are affected.

Disclosure of Invention

The purpose of the utility model is that: an annular flame tube connector is provided, which is applicable to the tail part of a flame tube.

The technical scheme of the utility model is as follows:

the flame tube annular connector sequentially comprises a first annular section, a transition section and a second annular section, wherein the transition section is used for connecting the first annular section and the second annular section;

and a circle of small holes are circumferentially arranged on the second annular section or the transition section.

Preferably, the inner side of the first annular section is welded with the outer side of the tail part of the flame tube.

Preferably, the diameter of the second annular section is larger than that of the first annular section, the turbine guide or the turbine air inlet volute is inserted between the second annular section and the outer wall of the tail part of the flame tube, and the insertion depth is not more than the distance between the small hole and the rear end face of the second annular section.

Preferably, the turbine guide or the turbine air inlet volute is connected with the flame tube, and gaps are reserved between the part inserted between the second annular section and the outer wall of the tail of the flame tube and the parts inserted between the inner wall of the second annular section and the outer wall of the tail of the flame tube.

Preferably, the thicknesses of the first annular section, the second annular section and the transition section are all larger than the thickness of the tail part of the flame tube.

Preferably, the included angle between the center line of the small hole and the axis of the flame tube is 30-60 degrees.

The utility model has the beneficial effects that: according to the utility model, the flame tube tail and the turbine guider or the turbine air inlet volute are wrapped through the flame tube annular connector, so that the influence of airflow oscillation on the flame tube tail is eliminated or reduced; meanwhile, through the small holes arranged on the annular connector of the flame tube, air flow with lower temperature outside the flame tube is impacted to the tail part of the flame tube and the turbine guider or the turbine air inlet volute, so that the influence of thermal stress on the tail part of the flame tube is eliminated or reduced. The utility model has simple and feasible structure, and can improve the reliability and service life of the tail part of the flame tube.

Drawings

FIG. 1 is a cross-sectional view of a flame tube annular fitting of the present utility model;

FIG. 2 is a schematic flow diagram of the annular union of the flame tube of the present utility model of FIG. 1;

wherein: 1-a first annular segment; 2-a second annular segment; 3-transition section; 4-small holes; 5-flame tube tail; 6-turbine pilot or turbine inlet volute.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

As shown in fig. 1, the present utility model provides a flame tube annular joint, which sequentially comprises a first annular section 1, a transition section 3 connecting the first annular section 1 and a second annular section 2, and a second annular section 2 along the axial direction of the flame tube;

the second annular section 2 or the transition section 3 is circumferentially provided with a circle of small holes 4. As shown in fig. 2, through the small holes 4 arranged on the annular connector of the flame tube, the air flow with lower temperature outside the flame tube is impacted to the flame tube tail 5 and the turbine guider or the turbine air inlet volute 6, so that the temperature and the temperature non-uniformity of the flame tube tail 5 and the turbine guider or the turbine air inlet volute 6 can be reduced, and the influence of thermal stress on the flame tube tail 5 can be eliminated or reduced.

The inner side of the first annular section 1 is welded with the outer side of the flame tube tail 5.

The diameter of the second annular section 2 is larger than that of the first annular section 1, a turbine guide or a turbine air inlet volute 6 is inserted between the second annular section 2 and the outer wall of the tail part 5 of the flame tube, and the insertion depth is not more than the distance between the small hole 4 and the rear end face of the second annular section 2. As shown in fig. 2, the liner annular joint encloses the liner tail 5 and the turbine guide or turbine inlet volute 6 to eliminate or reduce the effects of airflow oscillations on the liner tail 5. The depth is set so that air passing through the outside of the flame tube can impact the tail 5 of the flame tube and the turbine guider or the turbine air inlet volute 6 after passing through the small holes 4, thereby ensuring the cooling effect.

The turbine guider or turbine air inlet volute 6 is connected with the flame tube, and gaps are reserved between the part inserted between the second annular section 2 and the outer wall of the tail part 5 of the flame tube and the part inserted between the inner wall of the second annular section 2 and the outer wall of the tail part 5 of the flame tube. As shown in fig. 2, the gaps on two sides are arranged so that the flame tube tail 5, the turbine guide or the turbine air inlet volute 6 are deformed due to heating, and concentrated stress is not generated.

The thicknesses of the first annular section 1, the second annular section 2 and the transition section 3 are all larger than the thickness of the tail part 5 of the flame tube. When the thickness of the tail part of the flame tube is 0.8-1.0 mm, the annular joint of the flame tube comprises a first annular section 1, a second annular section 2 and a transition section 3, and the thickness of the first annular section is 1.5-3.0 mm. Through the thickening of the thickness of the material, the deformation of the flame tube tail 5 is better limited, and the reliability and the service life of the flame tube tail 5 are improved.

The included angle between the center line of the small hole 4 and the axis of the flame tube is 30-60 degrees. The arrangement of the included angle is beneficial to better flowing of air with lower temperature outside the flame tube.

The utility model has simple and feasible structure, is suitable for the tail part of the flame tube, eliminates or reduces the influence of airflow oscillation and thermal stress on the tail part of the flame tube, and can improve the reliability and service life of the tail part of the flame tube.

The foregoing is merely a detailed description of the utility model, which is not a matter of routine skill in the art. However, the scope of the present utility model is not limited thereto, and any changes or substitutions that can be easily contemplated by those skilled in the art within the scope of the present utility model should be included in the scope of the present utility model. The protection scope of the present utility model shall be subject to the protection scope of the claims.

Claims

1. A flame tube annular joint which is characterized in that: the annular joint sequentially comprises a first annular section (1), a transition section (3) and a second annular section (2) along the axial direction of the flame tube, wherein the transition section (3) is used for connecting the first annular section (1) and the second annular section (2);

a circle of small holes (4) are circumferentially arranged on the second annular section (2) or the transition section (3).

2. The liner annular joint of claim 1, wherein: the inner side of the first annular section (1) is welded with the outer side of the flame tube tail (5).

3. The liner annular joint of claim 1, wherein: the diameter of the second annular section (2) is larger than that of the first annular section (1), a turbine guide or a turbine air inlet volute (6) is inserted between the second annular section (2) and the outer wall of the tail part (5) of the flame tube, and the insertion depth is not more than the distance between the small hole (4) and the rear end face of the second annular section (2).

4. A burner ring joint as claimed in claim 3, wherein: the turbine guider or the turbine air inlet volute (6) is connected with the flame tube, and gaps are reserved between the part inserted between the second annular section (2) and the outer wall of the tail part (5) of the flame tube and the part inserted between the inner wall of the second annular section (2) and the outer wall of the tail part (5) of the flame tube.

5. The liner annular joint of claim 1, wherein: the thicknesses of the first annular section (1), the second annular section (2) and the transition section (3) are all larger than the thickness of the tail part (5) of the flame tube.

6. The liner annular joint of claim 1, wherein: the included angle between the center line of the small hole (4) and the axis of the flame tube is 30-60 degrees.