Front swirler blade stabilizing structure of aero-engine combustion chamber

Abstract

The utility model relates to the technical field of aero-engines, in particular to an aero-engine combustion chamber front swirler blade stabilizing structure which comprises a shaft piece body, curved surface blades and swirling flow grooves. The curved surface blades are arranged on the outer wall of the side edge of the shaft piece body at equal intervals in a surrounding mode. When the front swirler blade stabilizing structure of the aero-engine combustion chamber is used, through the design that the reinforcing ribs are additionally arranged on the outer walls of the curved-surface blades, the rigidity of the blades can be effectively improved, fatigue damage in the high-temperature and high-speed working environment is prevented, the outer walls of the two sides of each reinforcing rib are further designed to be chamfered, and the stability of the blades is improved. Through the principle of fluid dynamics and the chamfer design, the resistance of airflow when the airflow passes through the ribs can be reduced, the pressure drop is reduced, the airflow efficiency in the whole combustion chamber is improved, meanwhile, the contact area of fluid and the wall face is increased through the ribs, and therefore the heat exchange efficiency is improved, and fuel is more fully heated in the combustion chamber.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aero-engine, especially relates to aero-engine combustion chamber front swirler blade stable structure. BACKGROUND

[0002] The swirler is one of very important parts of the engine, and the function is to form the backflow area of the flame tube head, reduce the airflow velocity, form the stable fire source at the flame tube head, ensure the stable work of the combustion chamber, and the blade swirler commonly used in the annular combustion chamber of the aero-engine generally comprises a cylinder body and a plurality of blades spirally arranged on the cylinder body, and a swirl groove is formed between the adjacent two blades.

[0003] The existing built-in swirl blade of the swirler is generally directly arranged outside the shaft piece, and there is no additional stress support point, and the swirl blade is generally designed as a curved blade, and there is no additional reinforcing support piece, and damage is prone to occur in the actual use process, and therefore a swirl blade with good support and solid structure is required. SUMMARY

[0004] The purpose of the aero-engine combustion chamber front swirler blade stable structure is to solve the above problems, and the existing built-in swirl blade of the swirler is generally directly arranged outside the shaft piece, and there is no additional stress support point, and the swirl blade is generally designed as a curved blade, and there is no additional reinforcing support piece, and damage is prone to occur in the actual use process.

[0005] The aero-engine combustion chamber front swirler blade stable structure comprises a shaft body, a curved blade and a swirl groove, the side outer wall of the shaft body is circumferentially provided with the curved blade at equal intervals, and the swirl groove for guiding the fluid to rotate in a specific direction is formed between the adjacent two groups of curved blades, the side outer wall of the curved blade close to the upper end position is provided with three groups of reinforcing ribs at equal intervals, the side outer wall of the curved blade at the bottom end position is provided with a reinforcing base, and the bottom outer wall of the reinforcing base is connected with the side outer wall of the shaft body, the reinforcing base is integrally provided as an arc triangular plate structure, and the two side outer walls of the reinforcing base are provided with chamfers.

[0006] Preferably, the curved blade is provided as a composite material structure, the curved blade is integrally provided as a curved arc structure, and the two side outer walls and the intermediate turning position of the curved blade are provided with chamfers.

[0007] Preferably, the two side outer walls of the reinforcing rib are provided with chamfers.

[0008] The utility model has the advantages of:

[0009] 1. The aero-engine combustion chamber front swirler blade stable structure in use, through the design of reinforcing ribs added to the outer wall of the curved blade, the rigidity of the blade can be effectively improved, the fatigue damage in high temperature and high speed working environment is prevented, the design of the outer wall of the two sides of the reinforcing ribs is further chamfered, according to the principle of fluid dynamics, the chamfer design can reduce the resistance of airflow when passing through the ribs, reduce the pressure drop, improve the airflow efficiency in the whole combustion chamber, at the same time, the existence of the ribs increases the contact area of the fluid and the wall surface, thereby improving the heat exchange efficiency, so that the fuel is more fully heated in the combustion chamber.

[0010] 2. The aero-engine combustion chamber front swirler blade stable structure in use, through the design of setting triangular structure support at the bottom end of the curved blade, the mechanical properties of the triangular structure with good stability can effectively disperse the pressure of the airflow on the blade, and provide a stable fixing point, so as to realize the effect of enhancing the strength of the curved blade, and simultaneously enhance the stability of the whole structure, at the same time, the triangular structure can effectively guide the flow of the airflow, reduce the formation of vortex, thereby improving the flow efficiency of the airflow, which is helpful to improve the mixing effect and enhance the mixing rate of fuel and air. BRIEF DESCRIPTION OF DRAWINGS

[0011] Figure 1 It is a whole three-dimensional structure schematic view of the utility model;

[0012] Figure 2 It is a reinforcing rib installation three-dimensional structure schematic view of the utility model;

[0013] Figure 3 It is a reinforcing base installation three-dimensional structure schematic view of the utility model;

[0014] Figure 4 It is a curved blade three-dimensional structure schematic view of the utility model.

[0015] In the drawing: 1, shaft body; 2, curved blade; 3, swirled groove; 401, reinforcing rib; 402, reinforcing base. DETAILED DESCRIPTION

[0016] The technical scheme in the embodiments of the utility model will be described clearly and completely in combination with the drawings in the embodiments of the utility model, obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the protection scope of the utility model.

[0017] In specific implementation: such as Figures 1-4As shown, the front swirler vane stabilizing structure of the aero-engine combustion chamber comprises a shaft body 1, a curved vane 2 and a swirl groove 3: the curved vanes 2 are arranged at equal intervals on the side outer wall of the shaft body 1, and the swirl grooves 3 for guiding fluid to rotate in a specific direction are formed between the adjacent two groups of curved vanes 2;

[0018] Here, the curved vanes 2 are limited and supported by the shaft body 1, and when air enters the combustion chamber, it first passes through the shaft body 1 of the swirler, and the design of the air inlet guide of the swirler allows the air flow to rotate in a certain way. The curved vanes 2 guide the air to rotate in a specific direction to form a swirl. This rotating air flow enhances the interaction between air molecules, thereby improving the atomization effect and uniformity of the fuel; the swirl groove 3 in the swirler further enhances the rotational motion of the gas, and the design of the swirl groove 3 is to increase the kinetic energy and rotational speed of the fluid. Through this structure, the change in air flow velocity will cause a pressure gradient, resulting in more mixing motion; when the fuel is injected into the combustion chamber, the swirling air flow will help to better atomize and mix the fuel and air, and the presence of swirl can make the fuel be surrounded by air faster, thereby improving the combustion efficiency; the design of the swirler can help maintain the stability of combustion, avoid incomplete combustion and increase engine efficiency, and good mixing can achieve higher combustion temperature and pressure, thereby improving power output and reducing the generation of combustion pollutants.

[0019] The curved vanes 2 are arranged at equal intervals on the side outer wall near the upper end position, and three groups of reinforcing ribs 401 are arranged on the side outer wall near the upper end position; here, the design of adding reinforcing ribs 401 on the surface of the vane can effectively improve the rigidity of the vane and prevent fatigue damage in high-temperature and high-speed working environment.

[0020] The curved vanes 2 are arranged at equal intervals on the side outer wall near the upper end position, and three groups of reinforcing ribs 401 are arranged on the side outer wall near the upper end position; here, the design of adding reinforcing ribs 401 on the surface of the vane can effectively improve the rigidity of the vane and prevent fatigue damage in high-temperature and high-speed working environment.

[0021] The curved vanes 2 are arranged at equal intervals on the side outer wall near the upper end position, and three groups of reinforcing ribs 401 are arranged on the side outer wall near the upper end position; here, the design of adding reinforcing ribs 401 on the surface of the vane can effectively improve the rigidity of the vane and prevent fatigue damage in high-temperature and high-speed working environment.

[0022] The two side outer walls of the reinforcing rib 401 are provided with chamfers; so as to ensure that the reinforcing rib 401 normally reinforces and supports without affecting the normal passing of the airflow.

[0023] The reinforcing base 402 is provided as an arc-shaped triangular plate structure as a whole, and the two side outer walls of the reinforcing base 402 are provided with chamfers; the design of providing the reinforcing base 402 as an arc-shaped triangular plate structure utilizes the stability of the triangular plate structure, so that the reinforcing base 402 can more stably reinforce and support the curved surface blade 2.

[0024] In use, the provision of the shaft body 1 limits and supports the installation of the curved surface blade 2; when air enters the combustion chamber, it will first pass through the shaft body 1 of the swirler, and the design of guiding the intake air to the swirler allows the air flow to rotate in a certain way; the curved surface blade 2 guides the air to rotate in a specific direction, forming a swirl; this rotating air flow enhances the interaction between air molecules, thereby improving the atomization effect and uniformity of the fuel; the swirl groove 3 in the swirler further enhances the rotational motion of the gas; the design of the swirl groove 3 is to increase the kinetic energy and rotational speed of the fluid; through this structure, the change in air flow velocity will cause a pressure gradient, resulting in more mixing motion; when the fuel is injected into the combustion chamber, the swirling air flow will help to better atomize and mix the fuel and air; the presence of the swirl can make the fuel be surrounded by air faster, thereby improving the combustion efficiency; the design of the swirler can help maintain the stability of combustion, avoid incomplete combustion and increase engine efficiency; good mixing can achieve higher combustion temperature and pressure, thereby improving power output and reducing the generation of combustion pollutants.

[0025] In addition, it should be understood that although the present specification is described in terms of embodiments, not every embodiment contains only one independent technical solution, and the description of the specification is only for the sake of clarity, and those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can be appropriately combined to form other embodiments that those skilled in the art can understand.

Claims

1. A robust structure for the inlet cyclone separator blades of an aero-engine combustion chamber, characterized in that, Includes a shaft body (1), curved blades (2) and a swirl channel (3): the side outer wall of the shaft body (1) is provided with curved blades (2) at equal intervals, and a swirl channel (3) is formed between two adjacent sets of curved blades (2) to guide the fluid to rotate in a specific direction. The curved blade (2) has three sets of reinforcing ribs (401) evenly spaced on the outer side wall near the upper end. The curved blade (2) is provided with a reinforcing base (402) on the outer side wall at the bottom position, and the outer side wall of the bottom end of the reinforcing base (402) is connected to the outer side wall of the shaft body (1). The reinforced base (402) is configured as an arc-shaped triangular plate structure, and both outer walls of the reinforced base (402) are chamfered.

2. The stabilizing structure for the inlet cyclone separator blades of an aero-engine combustion chamber according to claim 1, characterized in that: The curved blade (2) is configured as a composite material structure, and the curved blade (2) as a whole is configured as a curved arc structure, and the outer walls on both sides and the middle turning position of the curved blade (2) are provided with chamfers.

3. The stabilizing structure for the inlet cyclone separator blades of an aero-engine combustion chamber according to claim 1, characterized in that: Both sides of the outer wall of the reinforcing rib (401) are chamfered.

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