An aero turbine engine

Abstract

The present application relates to a kind of aviation turbine engines, comprising: impeller system, rotating blade shafting and brake system, it mainly includes shell, brake disc, blade, movable crank, self-lubricating bush, brake pad and piston.The piston pushes the brake pad close to the brake disc and generates friction, realize the brake pad braking, while pushing the brake disc moves along the shell upwards, drive the blade angle change connected with the movable crank, while the self-lubricating bush is displaced in horizontal plane, realize the blade and brake pad synchronous braking.Compared with prior art, the present application has the advantages of aviation turbine engine braking speed, response speed is rapid, can realize the simultaneous braking of blade and brake pad etc..

Description

Technical Field

[0001] This invention relates to the field of aerospace equipment technology, and in particular to an aircraft turbine engine. Background Technology

[0002] As one of the most important components of an aircraft, the performance of an aero-turbine engine not only reflects the overall capability of the aircraft but also serves as a significant indicator of a nation's industrial level and capabilities. With major breakthroughs in materials, manufacturing, and design in recent years, my country's aero-turbine engines have made tremendous progress. However, with the continuous advancements in my country's scientific research and technology, the first four generations of aero-turbine engines are gradually becoming insufficient to meet current demands. Against this backdrop, the development of a fifth-generation aero-engine has been put on the agenda.

[0003] The focus of fifth-generation aero-turbine engines is to improve propulsive efficiency and mission adaptability. The first four generations of aero-turbine engines commonly used a combined fixed-blade design. While this design can meet the needs of most flight missions and environments, in certain special missions, aircraft need to perform frequent acceleration and braking as required. Currently, aircraft braking methods mostly rely on external structures and systems, and during braking, the turbine engine stops fuel supply to bring the aircraft to a slow stop, which increases braking time. Furthermore, a turbine engine malfunction that prevents rapid braking can cause greater damage to the engine and even lead to injuries or fatalities. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide an aircraft turbine engine that can achieve rapid braking of brake pads and blades using a hydraulic braking system.

[0005] The objective of this invention can be achieved through the following technical solutions:

[0006] An aircraft turbine engine, comprising:

[0007] An impeller system includes a housing, a brake disc movably connected to the housing and having the freedom to move up and down therethere, and a plurality of blades disposed on the housing at variable angles.

[0008] The rotating blade shaft system connected to the impeller system includes a movable crank and a self-lubricating bushing that can be moved horizontally within the brake disc. One end of the movable crank is connected to the blade, and the other end is connected to the self-lubricating bushing.

[0009] A braking system connected to the impeller system and the rotating blade shaft system includes brake pads and a piston that pushes the brake pads to move;

[0010] The piston pushes the brake pads closer to the brake disc and generates friction, thereby braking the brake pads. At the same time, it pushes the brake disc to move upward along the housing, causing the angle of the blades connected to the movable crank to change. Simultaneously, the self-lubricating bushing is displaced on the horizontal plane, achieving synchronous braking between the blades and the brake pads.

[0011] Furthermore, the blade has a connecting rod that can be connected to the housing. The connecting rod passes sequentially through the second flat key, the second bushing, the movable crank, the first bushing, the second round nut, and the second locking washer, and is connected to the housing.

[0012] Furthermore, the second flat key and the second bushing are located between the blade and the housing, and the movable crank, the first bushing, the second round nut and the second locking washer are located inside the blade. The second bushing, the movable crank and the first bushing are coaxial with the blade, and the second flat key, the second round nut and the second locking washer are used to restrict the axial movement of the blade.

[0013] Furthermore, the movable crank includes: a slider connected to the self-lubricating bushing, a rotating shaft connected to the connecting rod of the blade, and a crank connected to the slider and the rotating shaft. The movable crank serves to assist in motion, converting the longitudinal reciprocating motion transmitted by the piston into the rotation of the blade shaft system to achieve changes in blade angle and enable rapid braking.

[0014] Furthermore, the rotating blade shaft system also includes a self-resetting structure for realizing the self-resetting of the blades, the self-resetting structure comprising:

[0015] End cap;

[0016] A spring that enables the blade to self-reset;

[0017] A spring limiting block is disposed between the spring and the end cap to restrict the position of the spring;

[0018] A guide screw, passing through the spring limiting block and the spring, and connected to the brake disc, allows the spring limiting block to move freely up and down along the guide screw.

[0019] When the brake pad pushes the brake disc upward, the distance between the brake disc and the end cover shortens, and the spring is compressed to generate a certain elastic potential energy; when the brake pad moves downward, the brake disc also moves downward under the push of the spring to complete self-reset.

[0020] Furthermore, the braking system also includes a piston seat and a limiting disc, with the piston mounted on the piston seat and the brake pads movably connected to the limiting disc.

[0021] Furthermore, when the braking system is not braking, there is a certain gap between the brake pads and the brake disc.

[0022] Furthermore, when the braking system brakes, the brake pads are located on top of the limiting disc and in close contact with the brake disc, pushing the brake disc to move upward along the housing, with the blades facing the direction of movement with the largest surface area.

[0023] Furthermore, a limiting ring is provided above the brake disc to restrict the displacement of the brake disc.

[0024] Furthermore, the housing and the limiting ring are secured by a number of second screws.

[0025] Furthermore, the housing has several grooves inside, and the brake disc has several protrusions that fit the grooves of the housing and a sliding groove that connects to one end of the self-lubricating bushing on the outside.

[0026] Furthermore, the upper part of the housing is fixedly connected to the end cap by a first screw.

[0027] Furthermore, the brake disc and the end cover are connected by an input shaft, and a first flat key that serves as a guide is axially fixed on the surface of the input shaft. A first locking washer and a first round nut that serve as a limiting element are also provided between the brake disc and the end cover through the input shaft.

[0028] Compared with the prior art, the present invention has the following advantages:

[0029] (1) The aero-turbine engine provided by the present invention can achieve rapid braking by utilizing the changes in the angle of the brake pads and blades, enabling the aircraft to complete special tasks under special operating conditions. The brake pads contact and rub against the brake disc under the push of the piston, consuming the kinetic energy of the impeller system; at the same time, the blades change angle with the movement of the brake disc, increasing air resistance, thus achieving rapid braking on two levels.

[0030] (2) The aero-turbine engine provided by the present invention adopts a movable crank structure, which ensures that the brake pads and blades are angled simultaneously, start and end at the same time, and has high reliability because it is completed synchronously by means of mechanical structure. Attached Figure Description

[0031] Figure 1 This is a three-dimensional structural diagram of the aircraft turbine engine shown in Example 1 in its initial state;

[0032] Figure 2 This is an exploded view of the aircraft turbine engine impeller system and rotating blade shaft system shown in Example 1;

[0033] Figure 3This is a partial structural cross-sectional view of the aircraft turbine engine impeller system and rotating blade shaft system shown in Example 1;

[0034] Figure 4 This is a cross-sectional view of the aircraft turbine engine braking system shown in Example 1;

[0035] Figure 5 The right view of the rotating blade shaft system of the aero-turbine engine shown in Example 1 in its initial state;

[0036] Figure 6 The image shows the right view of the rotating blade shaft system of the aircraft turbine engine in the braking state as shown in Example 1.

[0037] Explanation of markings in the diagram:

[0038] 1-Impeller system, 2-Rotating blade shaft system, 3-Brake system, 4-Input shaft, 5-First flat key, 6-First screw, 7-End cover, 8-First locking washer, 9-First round nut, 10-Guide screw, 11-Spring limiting block, 12-Spring, 13-Second round nut, 14-Second locking washer, 15-Moving crank, 16-Self-lubricating bushing, 17-First bushing, 18-Second bushing, 19-Housing, 20-Blade, 21-Second flat key, 22-Brake disc, 23-Limiting ring, 24-Second screw, 25-Brake pad, 26-Limiting disc, 27-Piston, 28-Piston seat. Detailed Implementation

[0039] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. These embodiments are based on the technical solution of the present invention and provide detailed implementation methods and specific operating procedures. However, the scope of protection of the present invention is not limited to the following embodiments. In the following embodiments or examples, unless otherwise specified, the functional components or structures are conventional components or structures used in the art to achieve the corresponding functions. In the description of the present invention, it should be noted that the terms "upper," "lower," "inner," "outer," "horizontal," "axial," etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings and are only for the convenience of describing the present invention and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0040] Example 1

[0041] An aircraft turbine engine, such as Figure 1 As shown, it includes:

[0042] Impeller system 1 includes a housing 19, a brake disc 22 movably connected to the housing 19 and having the freedom to move up and down therethere, and a plurality of blades 20 disposed on the housing 19 with variable angles.

[0043] The rotating blade shaft system 2 connected to the impeller system 1 includes a movable crank 15 and a self-lubricating bushing 16 that can be moved horizontally within the brake disc 22. One end of the movable crank 15 is connected to the blade 20, and the other end is connected to the self-lubricating bushing 16.

[0044] The braking system 3, which is connected to the impeller system 1 and the rotating blade shaft system 2, includes a brake pad 25 and a piston 27 that pushes the brake pad 25 to move.

[0045] The piston 27 pushes the brake pad 25 closer to the brake disc 22 and generates friction, thereby braking the brake pad 25. At the same time, it pushes the brake disc 22 to move upward along the housing 19, causing the angle of the blade 20 connected to the movable crank 15 to change. Simultaneously, the self-lubricating bushing 16 is displaced on the horizontal plane, thereby achieving synchronous braking of the blade 20 and the brake pad 25.

[0046] like Figure 2 and Figure 3 As shown, the blade 20 has eight blades, each with a connecting rod that can be connected to the housing 19. The connecting rod passes sequentially through the second flat key 21, the second bushing 18, the movable crank 15, the first bushing 17, the second round nut 13, and the second locking washer 14, and is connected to the housing 19. The second flat key 21 and the second bushing 18 are located between the blade 20 and the housing 19, while the movable crank 15, the first bushing 16, the second round nut 13, and the second locking washer 14 are located inside the blade 20. The second bushing 18, the movable crank 15, and the first bushing 17 are coaxial with the blade 20. The second flat key 21, the second round nut 13, and the second locking washer 14 are used to restrict the axial movement of the blade 20.

[0047] The movable crank 15 includes a slider that cooperates with the self-lubricating bushing 16 and is fixedly connected to the brake disc 22, a rotating shaft connected to the connecting rod of the blade 20, and a crank connected to the slider and the rotating shaft. The movable crank 15 plays an auxiliary motion role, converting the longitudinal reciprocating motion transmitted by the piston 27 into the axial rotational motion of the blade 20, realizing the angle change of the blade 20, increasing air resistance, and enabling rapid braking. The rotating blade shaft system 2 also includes a self-resetting structure for realizing the self-resetting of the blade 20. The self-resetting structure includes: an end cover 7; four springs 12 that realize the self-resetting function of the blade 20; a spring limiting block 11 disposed between the springs 12 and the end cover 7 to limit the position of the springs 12; and a guide screw 10 passing through the spring limiting block 11 and the springs 12 and connected to the brake disc 22. The spring limiting block 11 has the freedom to move up and down along the guide screw 10. When the brake pad 25 pushes the brake disc 22 upward, the distance between the brake disc 22 and the end cover 7 becomes shorter, and the spring 12 is compressed to generate a certain elastic potential energy; when the brake pad 25 moves downward, the brake disc 22 also moves downward under the push of the spring 12 to complete self-reset.

[0048] like Figure 4 As shown, the braking system 3 also includes a piston seat 28 and a limiting disc 27. The piston 27 is disposed on the piston seat 28, and the brake pad 25 is movably connected to the limiting disc 27. When the braking system 3 is not braking, there is a certain gap between the brake pad 25 and the brake disc 22. When the braking system 3 is braking, the brake pad 25 is located on top of the limiting disc 26 and close to the brake disc 22, pushing the brake disc 22 to move upward along the housing 19, and the blade 20 faces the direction of movement of the device with the largest surface area.

[0049] A limiting ring 23 for restricting the displacement of the brake disc 22 is also provided above the brake disc 22. The housing 19 and the limiting ring 23 are fixed by 12 second screws 24. The housing 19 has 10 grooves inside, and the brake disc 22 has 10 protrusions that fit the grooves of the housing 19 and 8 sliding grooves that connect to one end of the self-lubricating bushing 17 on the outside. The housing 19 is fixedly connected to the end cover 7 by 8 first screws. The brake disc 22 and the end cover 7 are connected by an input shaft 4. A first flat key 5 for guiding is axially fixed on the surface of the input shaft 4. A first locking washer 8 and a first round nut 9 for limiting are also provided between the brake disc 22 and the end cover 7 through the input shaft 4.

[0050] like Figure 5 and Figure 6As shown, the working principle is as follows: Under hydraulic pressure, the piston 27 in the braking system 3 pushes the brake pad 25, causing it to be located on top of the limiting plate 25, closely adhering to the brake disc 22 and generating friction. Under the pushing action of the brake pad 25, the brake disc 22 moves upward along the housing 19 through the groove, thereby causing the self-lubricating bushing 16 connected to the slide groove to move on the horizontal plane, driving the movable crank 15 to work, converting the upward force provided by the piston 27 into the force of rotating the blade shaft system 2, causing the blade 20 to change angle, increasing its wind resistance, and completing the simultaneous rapid braking of the blade 20 and the brake pad 25.

[0051] Although the present invention has been described in detail above with general descriptions, specific embodiments, and experiments, modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, all such modifications or improvements made without departing from the spirit of the present invention fall within the scope of protection claimed by the present invention.

Claims

1. An aircraft turbine engine, characterized in that, include: The impeller system (1) includes a housing (19), a brake disc (22) movably connected to the housing (19) and having the freedom to move up and down therethere, and a plurality of blades (20) with variable angles disposed on the housing (19). The rotating blade shaft system (2) connected to the impeller system (1) includes a movable crank (15) and a self-lubricating bushing (16) movable in the brake disc (22) in the horizontal direction. One end of the movable crank (15) is connected to the blade (20) and the other end is connected to the self-lubricating bushing (16). A braking system (3) connected to the impeller system (1) and the rotating blade shaft system (2) includes a brake pad (25) and a piston (27) that pushes the brake pad (25) to move. The piston (27) pushes the brake pad (25) close to the brake disc (22) and generates friction to brake the brake pad (25). At the same time, it pushes the brake disc (22) to move upward along the housing (19), causing the angle of the blade (20) connected to the movable crank (15) to change. Meanwhile, the self-lubricating bushing (16) is displaced on the horizontal plane to achieve synchronous braking of the blade (20) and the brake pad (25). The blade (20) has a connecting rod that can be connected to the housing (19). The connecting rod passes through the second flat key (21), the second bushing (18), the movable crank (15), the first bushing (17), the second round nut (13), and the second locking washer (14) in sequence and is connected to the housing (19). The second flat key (21) and the second bushing (18) are located between the blade (20) and the housing (19). The movable crank (15), the first bushing (17), the second round nut (13), and the second locking washer (14) are located inside the blade (20). The second bushing (18), the movable crank (15), and the first bushing (17) are coaxial with the blade (20). The second flat key (21), the second round nut (13), and the second locking washer (14) are used to restrict the axial movement of the blade (20).

2. An aero-turbine engine according to claim 1, characterized in that, The movable crank (15) includes: The slider connected to the self-lubricating bushing (16); A rotating shaft connected to the connecting rod of the blade (20); And a crank connected to the slider and the shaft.

3. An aero-turbine engine according to claim 1, characterized in that, The rotating blade shaft system (2) also includes a self-resetting structure for realizing the self-resetting of the blade (20), the self-resetting structure including: End cap (7); Spring (12) that enables the self-resetting function of the blade (20); A spring limiting block (11) is disposed between the spring (12) and the end cap (7) to limit the position of the spring (12). The guide screw (10) passes through the spring limit block (11) and the spring (12) and is connected to the brake disc (22). The spring limit block (11) has the freedom to move up and down along the guide screw (10).

4. An aero-turbine engine according to claim 1, characterized in that, The braking system (3) further includes a piston seat (28) and a limiting disc (26), the piston (27) is disposed on the piston seat (28), and the brake pad (25) is movably connected to the limiting disc (26).

5. An aero-turbine engine according to claim 1, characterized in that, When the braking system (3) is not braking, there is a certain gap between the brake pads (25) and the brake disc (22).

6. An aero-turbine engine according to claim 1, characterized in that, When the braking system (3) brakes, the brake pads (25) are in close contact with the brake disc (22), pushing the brake disc (22) to move upward along the housing (19), and the blades (20) face the direction of movement with the largest surface area.

7. An aero-turbine engine according to claim 1, characterized in that, A limiting ring (23) is also provided above the brake disc (22) to limit the displacement of the brake disc (22). The housing (19) and the limiting ring (23) are fixed by a number of second screws (24).

8. An aero-turbine engine according to claim 1, characterized in that, The housing (19) has several grooves inside, and the brake disc (22) has several protrusions that are adapted to the grooves of the housing (19) and a sliding groove connected to one end of the self-lubricating bushing (16) on the outside.

9. An aero-turbine engine according to claim 8, characterized in that, The upper part of the housing (19) is fixedly connected to the end cap (7) by a number of first screws (6); The brake disc (22) and the end cover (7) are connected by an input shaft (4). A first flat key (5) is axially fixed on the surface of the input shaft (4) to serve as a guide. A first locking washer (8) and a first round nut (9) are also provided between the brake disc (22) and the end cover (7) through the input shaft (4) to serve as a limit.

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