Aviation gas turbine engine swirler with adjustable boundary layer thickness

Abstract

The utility model discloses an aviation gas turbine engine swirler with an adjustable boundary layer thickness, which belongs to the technical field of aviation gas turbine engine swirlers, and adopts the technical scheme that the aviation gas turbine engine swirler comprises a swirler body and a blade assembly, an adjusting mechanism is rotatably connected to the inner wall of the mounting frame, the side, close to the adjusting mechanism, of the blade assembly is in bolted connection with the adjusting mechanism, most of existing aero-gas turbine engine swirlers are inconvenient to adjust the thickness of a boundary layer in use, boundary layer airflow is airflow between the surface of an object and mainstream air, and the thickness of the boundary layer is larger than that of the airflow between the surface of the object and the mainstream air. The problems that due to the influence of viscosity, the flow speed of boundary layer airflow is low, the reverse pressure gradient enables the air flow speed to be low, the incidence angle making contact with air becomes large, the reverse pressure gradient becomes stronger, the boundary layer airflow with the low flow speed flows back, encounters mainstream air, hunches up and breaks away from the surface of an object, and the use effect is affected are solved.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation gas turbine engine swirlers, in particular to an aviation gas turbine engine swirler with adjustable boundary layer thickness. Background Art

[0002] The function of the swirler in the combustion chamber is to increase turbulence, improve mixing quality, and strengthen the combustion reaction, thereby increasing fuel utilization efficiency, reducing temperature differences between different ignition positions, reducing noise and vibration generated in the combustion chamber, and making combustion smoother. In the industrial and aviation fields, it improves engine performance and reliability while reducing fuel consumption and pollutant emissions, and has important application value.

[0003] At present, a Chinese patent with announcement number CN211924254U discloses a gas turbine engine, a blade and an internal cooling structure thereof, wherein the internal cooling structure comprises: a first side plate, a plurality of impact holes for fluid to enter are provided on the first side plate; a second side plate spaced apart from the first side plate, the second side plate is used to stop the fluid and exchange heat with the fluid; and a plurality of column ribs arranged between the first side plate and the second side plate, the column ribs are used to disturb the fluid; wherein the thermal conductivity of the column ribs is higher than that of the second side plate, the thermal conductivity of the first side plate is higher than that of the second side plate, the column ribs continuously destroy the boundary layer of the flow, enhance the disturbance of the nearby wall surface, strengthen the heat exchange, and at the same time the column ribs increase the heat exchange area; and the thermal conductivity of the column ribs and the first side plate is higher than that of the second side plate, which reduces the thermal resistance and improves the overall cooling performance of the internal cooling structure.

[0004] However, most existing aviation gas turbine engine swirlers are not convenient for adjusting the boundary layer thickness during use. The boundary layer airflow is the airflow between the surface of an object and the mainstream air. Affected by viscosity, the boundary layer airflow velocity is very slow. The adverse pressure gradient will slow down the air flow velocity, increase the angle of attack in contact with the air, and the adverse pressure gradient will become stronger, causing the slow boundary layer airflow to flow back, and arch up and separate from the surface of the object when it meets the mainstream air, making it inconvenient for users to use. Utility Model Content

[0005] The utility model provides an aviation gas turbine engine swirler with adjustable boundary layer thickness, aiming to solve the problem that most existing aviation gas turbine engine swirlers are inconvenient to adjust the boundary layer thickness during use. The boundary layer airflow is the airflow between the surface of an object and the mainstream air. Affected by viscosity, the boundary layer airflow velocity is very slow. The adverse pressure gradient will slow down the air velocity, increase the angle of attack of the air, and make the adverse pressure gradient more intense, which will cause the boundary layer airflow with a very slow velocity to flow back, and arch up and separate from the surface of the object when it meets the mainstream air, thereby affecting the use effect.

[0006] The utility model is realized as follows: a swirler of an aviation gas turbine engine with adjustable boundary layer thickness comprises a swirler body and a blade assembly, a mounting frame is clamped on the surface of the swirler body, an adjusting mechanism is rotatably connected to the inner wall of the mounting frame, a side of the blade assembly close to the adjusting mechanism is bolted to the adjusting mechanism, and an output assembly is bolted to the inner wall of the mounting frame;

[0007] The adjusting mechanism comprises a rotating shaft, an adjusting gear and a stabilizing frame, the top of the stabilizing frame is bolted to the bottom of the rotating shaft, the top of the rotating shaft is bolted to the bottom of the blade assembly, the inner wall of the adjusting gear is bolted to the surface of the rotating shaft, and the surface of the rotating shaft is rotatably connected to the inner wall of the mounting frame.

[0008] In order to achieve the effect of adjusting the gear rotating on the inner wall of the mounting frame, as a preferred embodiment of the utility model, a swirler of an aviation gas turbine engine with adjustable boundary layer thickness is configured in which the surface of the adjusting gear is movably connected to the inner wall of the mounting frame, and the surface of the stabilizing frame is rotatably connected to the inner wall of the mounting frame.

[0009] In order to achieve the effect of the rotating rod rotating on the inner wall of the mounting frame, as a preferred aviation gas turbine engine swirler with adjustable boundary layer thickness of the utility model, the output end of the output assembly is bolted with a rotating rod, the surface of the rotating rod is rotatably connected to the inner wall of the mounting frame, and the front side of the rotating rod is bolted with a first bevel gear.

[0010] In order to achieve the effect that the first bevel gear drives the second bevel gear to rotate, as a preferred aviation gas turbine engine swirler with adjustable boundary layer thickness of the utility model, the surface of the first bevel gear is meshed with the second bevel gear, the top of the second bevel gear is bolted with a rotating rod, and the surface of the rotating rod is rotatably connected to the inner wall of the mounting frame.

[0011] In order to achieve the effect that the rotating rod drives the output gear to rotate, as a preferred aviation gas turbine engine swirler with adjustable boundary layer thickness of the utility model, the surface of the rotating rod is bolted with an output gear, and the surface of the output gear is meshed with the surface of the adjusting gear.

[0012] In order to achieve the effect of the rotating rod rotating on the inner wall of the mounting frame, as a preferred embodiment of the utility model, an aviation gas turbine engine swirler with adjustable boundary layer thickness is provided with a first rotating groove used in conjunction with the rotating rod on the inner wall of the mounting frame, and a second rotating groove used in conjunction with the rotating rod on the inner wall of the mounting frame is provided.

[0013] In order to achieve the effect of the output gear rotating on the inner wall of the mounting frame, as a preferred aviation gas turbine engine swirler with adjustable boundary layer thickness of the utility model, the inner wall of the mounting frame is provided with a rotating groove used in conjunction with a stabilizing frame, and the inner wall of the mounting frame is provided with an output groove used in conjunction with the output gear.

[0014] In order to achieve the effect that the first bevel gear and the second bevel gear rotate on the inner wall of the mounting frame, as a preferred embodiment of the utility model of an aviation gas turbine engine swirler with adjustable boundary layer thickness, an inner wall of the mounting frame is provided with an engagement groove.

[0015] Compared with the prior art, the beneficial effects of the utility model are:

[0016] The aviation gas turbine engine swirler with adjustable boundary layer thickness is provided with a swirler body, a blade assembly, a mounting frame, an adjustment mechanism and an output assembly. When in use, the swirler body is fixed by the position of the stabilizing frame and the rotating shaft, and the position of the rotating shaft and the blade assembly is fixed, so that the fixed angle of the blade assembly can be adjusted by adjusting the gear. When the boundary layer thickness needs to be adjusted, the output is performed through the output assembly, so that the output assembly drives the adjusting gear to rotate. When the adjusting gear rotates, the rotating shaft is driven to rotate on the inner wall of the mounting frame, so that the blade assembly can be driven to rotate at an angle by the rotating shaft, the contact surface of the blade assembly can be adjusted, and the boundary layer thickness can be adjusted. The swirler body adjustment process is relatively convenient and convenient for users to use. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is the overall structural diagram of the aviation gas turbine engine swirler with adjustable boundary layer thickness of the utility model;

[0018] Figure 2 This is a structural diagram of the blade assembly in the utility model;

[0019] Figure 3 It is a structural diagram of the adjustment mechanism in the utility model;

[0020] Figure 4 It is a cross-sectional view of the mounting frame in the utility model;

[0021] Figure 5 This is a structural diagram of the adjusting gear in the utility model;

[0022] Figure 6 It is a structural diagram of the output component in the utility model.

[0023] In the figure, 1, cyclone body; 2, adjustment mechanism; 201, rotating shaft; 202, adjusting gear; 203, stabilizing frame; 3, blade assembly; 4, mounting frame; 5, output assembly; 6, rotating rod; 7, first bevel gear; 8, second bevel gear; 9, rotating rod; 10, output gear; 11, first rotating groove; 12, second rotating groove; 13, rotating groove; 14, output groove; 15, meshing groove. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solution and advantages of the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model and are not used to limit the utility model.

[0025] In the description of the present invention, it should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, in the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined.

[0026] See also Figure 1-6 The utility model provides a technical solution: a swirler of an aviation gas turbine engine with adjustable boundary layer thickness, comprising a swirler body 1 and a blade assembly 3, a mounting frame 4 is clamped on the surface of the swirler body 1, an adjusting mechanism 2 is rotatably connected to the inner wall of the mounting frame 4, a side of the blade assembly 3 close to the adjusting mechanism 2 is bolted to the adjusting mechanism 2, and an output assembly 5 is bolted to the inner wall of the mounting frame 4;

[0027] The adjusting mechanism 2 includes a rotating shaft 201, an adjusting gear 202 and a stabilizing frame 203. The top of the stabilizing frame 203 is bolted to the bottom of the rotating shaft 201, the top of the rotating shaft 201 is bolted to the bottom of the blade assembly 3, the inner wall of the adjusting gear 202 is bolted to the surface of the rotating shaft 201, and the surface of the rotating shaft 201 is rotatably connected to the inner wall of the mounting frame 4.

[0028] In this embodiment, the cyclone body 1, the blade assembly 3, the mounting frame 4, the adjustment mechanism 2 and the output assembly 5 are provided. When in use, the stabilizing frame 203 and the rotating shaft 201 are fixed, and the rotating shaft 201 and the blade assembly 3 are fixed, so that the fixed angle of the blade assembly 3 can be adjusted by the adjusting gear 202 later. When the boundary layer thickness needs to be adjusted, the output is performed through the output assembly 5, so that the output assembly 5 drives the adjusting gear 202 to rotate. When the adjusting gear 202 rotates, the rotating shaft 201 is driven to rotate on the inner wall of the mounting frame 4, so that the blade assembly 3 can be driven to rotate at an angle by the rotating shaft 201 later, so that the contact surface of the blade assembly 3 can be adjusted, and the boundary layer thickness can be adjusted. The adjustment process of the cyclone body 1 is relatively convenient, and it is convenient for users to use.

[0029] As a technical optimization solution of the present invention, the surface of the adjusting gear 202 is movably connected to the inner wall of the mounting frame 4 , and the surface of the stabilizing frame 203 is rotationally connected to the inner wall of the mounting frame 4 .

[0030] In this embodiment: when the fixed angle of the blade assembly 3 needs to be adjusted, the rotating shaft 201 is driven to rotate by adjusting the gear 202. When the rotating shaft 201 rotates, it will drive the stabilizing frame 203 to rotate on the inner wall of the mounting frame 4, so as to facilitate the stable adjustment of the blade assembly 3.

[0031] As a technical optimization solution of the utility model, the output end of the output assembly 5 is bolted with a rotating rod 6 , the surface of the rotating rod 6 is rotatably connected to the inner wall of the mounting frame 4 , and the front side of the rotating rod 6 is bolted with a first bevel gear 7 .

[0032] In this embodiment: by setting the rotating rod 6 and the first bevel gear 7, the position of the rotating rod 6 and the output component 5 are fixed during use, and the position of the rotating rod 6 and the first bevel gear 7 are fixed, which is convenient for subsequent output through the output component 5, so that the output component 5 drives the rotating rod 6 to rotate, and the rotating rod 6 will drive the first bevel gear 7 to rotate while rotating.

[0033] As a technical optimization solution of the utility model, the surface of the first bevel gear 7 is meshed with the second bevel gear 8 , the top of the second bevel gear 8 is bolted with a rotating rod 9 , and the surface of the rotating rod 9 is rotatably connected to the inner wall of the mounting frame 4 .

[0034] In this embodiment: by setting the second bevel gear 8 and the rotating rod 9, the positions of the second bevel gear 8 and the rotating rod 9 are fixed during use. When the first bevel gear 7 rotates, the second bevel gear 8 is driven to rotate, so that the second bevel gear 8 drives the rotating rod 9 to rotate on the inner wall of the mounting frame 4.

[0035] As a technical optimization solution of the utility model, an output gear 10 is bolted to the surface of the rotating rod 9 , and the surface of the output gear 10 is meshed with the surface of the adjusting gear 202 .

[0036] In this embodiment: by setting the output gear 10, the position of the output gear 10 and the rotating rod 9 are fixed during use, so that the output gear 10 can be driven to rotate by the rotating rod 9 later. When the output gear 10 rotates, it will also drive the adjusting gear 202 to rotate, so that the adjusting gear 202 can drive the blade assembly 3 to adjust the angle.

[0037] As a technical optimization solution of the utility model, the inner wall of the mounting frame 4 is provided with a first rotation groove 11 used in conjunction with the rotation rod 6 , and the inner wall of the mounting frame 4 is provided with a second rotation groove 12 used in conjunction with the rotation rod 9 .

[0038] In this embodiment: through the first rotating groove 11 opened on the inner wall of the mounting frame 4, it is convenient for the rotating rod 6 to rotate on the inner wall of the mounting frame 4 through the first rotating groove 11, and through the second rotating groove 12 opened on the inner wall of the mounting frame 4, it is convenient for the rotating rod 9 to rotate on the inner wall of the mounting frame 4 through the second rotating groove 12.

[0039] As a technical optimization solution of the utility model, the inner wall of the mounting frame 4 is provided with a rotation groove 13 used in conjunction with the stabilizing frame 203 , and the inner wall of the mounting frame 4 is provided with an output groove 14 used in conjunction with the output gear 10 .

[0040] In this embodiment: the rotating groove 13 opened on the inner wall of the mounting frame 4 facilitates the stabilizing frame 203 to rotate on the inner wall of the mounting frame 4 through the rotating groove 13, and the output groove 14 opened on the inner wall of the mounting frame 4 facilitates the output gear 10 to rotate on the inner wall of the mounting frame 4 through the output groove 14.

[0041] As a technical optimization solution of the present utility model, an engagement groove 15 is provided on the inner wall of the mounting frame 4 .

[0042] In this embodiment, the meshing groove 15 provided on the inner wall of the mounting frame 4 facilitates the first bevel gear 7 and the second bevel gear 8 to rotate on the inner wall of the mounting frame 4 .

[0043] Working principle: First, during use, the positions of the stabilizing frame 203 and the rotating shaft 201 are fixed, and the positions of the rotating shaft 201 and the blade assembly 3 are fixed, so that the fixed angle of the blade assembly 3 can be adjusted by the adjusting gear 202 later. When the boundary layer thickness needs to be adjusted, the output is output through the output assembly 5, so that the output assembly 5 drives the rotating rod 6 to rotate, so that the rotating rod 6 drives the first bevel gear 7 to rotate. When the first bevel gear 7 rotates, it will drive the second bevel gear 8 to rotate, so that the second bevel gear 8 drives the rotating rod 9 to rotate. When the rotating rod 9 rotates, it will drive the output gear 10 to rotate, so that the output gear 10 drives the adjusting gear 202 to rotate. When the adjusting gear 202 rotates, it will drive the rotating shaft 201 to rotate on the inner wall of the mounting frame 4, so that the blade assembly 3 can be driven to rotate at an angle laterally through the rotating shaft 201, so that the contact surface of the blade assembly 3 can be adjusted, so as to adjust the boundary layer thickness. The adjustment process of the cyclone body 1 is relatively convenient and convenient for users to use.

[0044] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aviation gas turbine engine swirler with adjustable boundary layer thickness, comprising a swirler body (1) and a blade assembly (3), characterized in that: The surface of the cyclone body (1) is clamped with a mounting frame (4), the inner wall of the mounting frame (4) is rotatably connected to the adjusting mechanism (2), the side of the blade assembly (3) close to the adjusting mechanism (2) is bolted to the adjusting mechanism (2), and the inner wall of the mounting frame (4) is bolted to the output assembly (5); The adjusting mechanism (2) comprises a rotating shaft (201), an adjusting gear (202) and a stabilizing frame (203); the top of the stabilizing frame (203) is bolted to the bottom of the rotating shaft (201); the top of the rotating shaft (201) is bolted to the bottom of the blade assembly (3); the inner wall of the adjusting gear (202) is bolted to the surface of the rotating shaft (201); and the surface of the rotating shaft (201) is rotatably connected to the inner wall of the mounting frame (4).

2. The aviation gas turbine engine swirler with adjustable boundary layer thickness according to claim 1, characterized in that: The surface of the adjusting gear (202) is movably connected to the inner wall of the mounting frame (4), and the surface of the stabilizing frame (203) is rotationally connected to the inner wall of the mounting frame (4).

3. The aviation gas turbine engine swirler with adjustable boundary layer thickness according to claim 1, characterized in that: The output end of the output assembly (5) is bolted with a rotating rod (6), the surface of the rotating rod (6) is rotatably connected to the inner wall of the mounting frame (4), and the front side of the rotating rod (6) is bolted with a first bevel gear (7).

4. The aviation gas turbine engine swirler with adjustable boundary layer thickness according to claim 3, characterized in that: The surface of the first bevel gear (7) is meshed with a second bevel gear (8), the top of the second bevel gear (8) is bolted with a rotating rod (9), and the surface of the rotating rod (9) is rotatably connected to the inner wall of the mounting frame (4).

5. The aviation gas turbine engine swirler with adjustable boundary layer thickness according to claim 4, characterized in that: An output gear (10) is bolted to the surface of the rotating rod (9), and the surface of the output gear (10) is meshed with the surface of the adjusting gear (202).

6. The aviation gas turbine engine swirler with adjustable boundary layer thickness according to claim 5, characterized in that: The inner wall of the mounting frame (4) is provided with a first rotation groove (11) for use in conjunction with the rotation rod (6), and the inner wall of the mounting frame (4) is provided with a second rotation groove (12) for use in conjunction with the rotation rod (9).

7. The aviation gas turbine engine swirler with adjustable boundary layer thickness according to claim 5, characterized in that: The inner wall of the mounting frame (4) is provided with a rotation groove (13) for use with the stabilizing frame (203), and the inner wall of the mounting frame (4) is provided with an output groove (14) for use with the output gear (10).

8. The aviation gas turbine engine swirler with adjustable boundary layer thickness according to claim 1, characterized in that: An engagement groove (15) is provided on the inner wall of the mounting frame (4).

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