Miniature turboprop engine reduction gear box

Abstract

The invention discloses a reduction gear box of a micro turboprop engine, and relates to the technical field of turboprop engines. Comprising a turboprop engine reduction gear box body, a first gear is arranged on the turboprop engine reduction gear box body, power turbine rotor blades are arranged at the front end of the turboprop engine reduction gear box body, and a connecting gear is arranged on the turboprop engine reduction gear box body. A reduction gear, an input gear and a connecting shaft are arranged on the turboprop engine reduction gear box body, and a ball bearing and a deep groove ball bearing are arranged on the outer surface of the connecting shaft. The ball bearing comprises an outer ring, a suspension part, an inner ring, a plurality of balls, a reinforcing structural part and a retainer, and the turboprop engine reduction gear box main body is provided with an input shaft. The turboprop engine reduction gear box has the beneficial effects that efficient transmission and conversion of power, speed reduction and torque increase, compact and reliable structure, function differentiation, easiness in maintenance and the like can be realized; and powerful support is provided for stable operation of the micro turboprop engine in various application scenes.

Description

Technical Field

[0001] The invention relates to the technical field of turboprop engines, in particular to a reduction gearbox for a micro turboprop engine. Background Art

[0002] Turboprop engines generally refer to turboprop engines, which are gas turbine engines commonly used on aircraft. Turboprop engines use the power generated by the rotation of the propeller as the propulsion force for the aircraft to move forward, but if the propeller rotates too fast, shock waves will be generated, and the aerodynamic resistance of the propeller will increase significantly, greatly reducing the energy utilization efficiency. The speed of the power turbine of small and medium-sized turboprop engines can generally reach 30,000 to 40,000 revolutions, while the speed of the propeller is only a few thousand revolutions per minute, requiring the speed to be reduced by about ten times. In addition, the high specific gravity ratio of the turbine engine, high reliability requirements, and harsh working environment make the design and manufacture of turboprop engines very difficult.

[0003] In the prior art, there is a reduction gearbox for a lightweight turboprop engine, comprising a first housing and a second housing, an input shaft is provided at the lower portion of the first housing, an input gear is provided on the input shaft, a first gear is provided at the upper portion of the input gear, a second gear is provided at the right side of the first gear, the first gear is sleeved on the connecting shaft, the second gear and the connecting shaft are integrally formed, an output shaft is provided at the lower portion of the second gear, a transmission tooth is provided at a position corresponding to the second gear on the output shaft, a bracket is provided at the upper portion of the second housing, and an oil tank is provided at the upper portion of the second housing located outside the bracket. The present invention adopts a reduction gearbox for a lightweight turboprop engine with the above structure, which has a compact and simple structure, low overall weight and manufacturing cost, high transmission ratio and transmission efficiency, and long service life.

[0004] The existing reduction gearbox has efficiency loss in the power transmission process, especially in multi-stage transmission, the energy loss is more obvious. The existing technology adopts a more complex gear set design, which leads to a bulky overall structure and is difficult to adapt to application scenarios with limited space. It is difficult for the existing reduction gearbox to maintain a low speed while outputting high torque, or it is necessary to sacrifice too much speed when achieving high torque. The existing technology has problems such as gear wear and bearing fatigue when running under high load, resulting in a short service life and high maintenance costs. The existing reduction gearbox is relatively single in function and it is difficult to meet the needs of diversified application scenarios, such as the inability to flexibly adjust the torque and speed. Therefore, a micro turboprop engine reduction gearbox is needed to solve the above problems. Summary of the invention

[0005] The invention provides a micro turboprop engine reduction gearbox to solve the problems in the background technology.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a micro turboprop engine reduction gearbox, comprising a turboprop engine reduction gearbox body, a first gear is arranged on the turboprop engine reduction gearbox body, a power turbine rotor blade is arranged at the front end of the turboprop engine reduction gearbox body, a connecting gear is arranged on the turboprop engine reduction gearbox body, a reduction gear is arranged on the turboprop engine reduction gearbox body, an input gear is arranged on the turboprop engine reduction gearbox body, a connecting shaft is arranged on the turboprop engine reduction gearbox body, a ball bearing and a deep groove ball bearing are arranged on the outer surface of the connecting shaft, the ball bearing comprises an outer ring, a suspension part, an inner ring, balls, a reinforcing structure and a retaining frame, and there are multiple balls, and an input shaft is arranged on the turboprop engine reduction gearbox body.

[0007] Furthermore, the first gear, reduction gear, connecting gear and input gear have the same module and are all spur gears. The input gear is meshed with the reduction gear teeth, and the connecting gear is meshed with the first gear teeth. The reduction gear has more teeth than the input gear, and the tooth width of the reduction gear is slightly wider than that of the input gear. The connecting gear has more teeth than the first gear.

[0008] Furthermore, the connecting gear and the reduction gear are fixedly connected via a fixed shaft, a deep groove ball bearing is respectively arranged on the front and rear sides of the fixed shaft, the outer side of the deep groove ball bearing is fixedly connected to the reduction gear box body, and the inner side is fixedly connected to the fixed shaft.

[0009] Further, the reinforcing structural member is arranged inside the plastic retaining frame, the reinforcing structural member is arranged outside the plastic retaining frame and is firmly connected to the ball bearing retaining frame, the reinforcing structural member is arranged as an insert in the plastic retaining frame of the ball bearing retaining frame to reinforce the web area, the reinforcing structural member is formed by a circumferentially shaped annular member or a wire, the reinforcing structural member is formed as a circumferentially shaped annular member with an I-shaped profile, the reinforcing structural member is formed as a circumferentially shaped annular member with an H-shaped profile, the reinforcing structural member is formed as a circumferentially shaped annular member with an X-shaped profile, the reinforcing structural member is formed as a circumferentially shaped annular member with an L-shaped profile, and the reinforcing structural member is formed as a circumferentially shaped annular member with an O-shaped profile.

[0010] Further, the ball bearing retainer is formed of polyamide-imide, the ball bearing retainer is formed of polyetheretherketone, and the ball bearing retainer is formed of phenolic resin with fine mesh cotton fabric.

[0011] Furthermore, the plurality of balls are distributed in a circular shape in the cage, the inner ring is located inside the cage, and the outer ring includes the cage and the plurality of balls.

[0012] Furthermore, the suspension portion is located inside the retaining frame.

[0013] Furthermore, the power turbine rotor blades are provided with internal splines, the front end of the input shaft is provided with external splines, the turbine rotor blades are connected to the input shaft via splines, and the input shaft is fixedly connected to the input gear.

[0014] Compared with the prior art, the present invention provides a micro turboprop engine reduction gearbox, which has the following beneficial effects:

[0015] 1. The micro turboprop engine reduction gearbox can receive power input from the gas turbine by arranging a first gear, a reduction gear, a connecting gear and an input gear, and by arranging an input gear, a power turbine rotor blade and an input shaft; the input gear transmits the power to the reduction gear to achieve a preliminary reduction in rotation speed and an increase in torque; the reduction gear further transmits the power to the connecting gear to ensure the continuity and stability of the power; finally, the connecting gear drives the first gear to rotate, and finally drives the connecting shaft to rotate, and the connecting shaft can be connected to the propeller, thereby achieving the final output of power; the gear ratio setting of the reduction gear significantly reduces the output rotation speed, and the torque increases accordingly; This is crucial for many application scenarios that require high torque and low speed; it can further optimize the effect of deceleration and torque increase and improve the energy utilization efficiency of the entire system; the setting of the gear set allows the various gears to be arranged closely, reducing space occupancy and making the entire reduction gearbox structure more compact; by setting the first gear, the reduction gear, the connecting gear and the input gear, the present invention can achieve the beneficial effects of efficient transmission and conversion of power, deceleration and torque increase, compact structure and reliability, functional differentiation and easy maintenance; these effects jointly improve the performance and reliability of the entire system and provide strong support for the stable operation of micro turboprop engines in various application scenarios.

[0016] 2. The micro turboprop engine reduction gearbox can increase its service life by arranging ball bearings. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a sectional view of the internal structure of the present invention;

[0018] Figure 2 It is a schematic diagram of the overall structure of the present invention;

[0019] Figure 3 A diagram showing the connection relationship between the connecting shaft and the ball bearing of the present invention;

[0020] Figure 4 It is a structural diagram of a ball bearing of the present invention;

[0021] Figure 5It is a meshing diagram of the first gear, the reduction gear, the connecting gear and the input gear of the present invention;

[0022] Figure 6 A cross-sectional view of the turbine rotor blade structure of the present invention;

[0023] Figure 7 It is the structural diagram of the input shaft of the present invention;

[0024] Figure 8 This is a connection diagram of the turbine rotor blades, input shaft and input gear of the present invention.

[0025] In the figure: 1. turboprop engine reduction gearbox body; 101. turbine rotor blade; 2. first gear; 3. reduction gear; 4. connecting gear; 5. input gear; 6. connecting shaft; 7. input shaft; 8. ball bearing; 801. outer ring; 802. suspension; 803. inner ring; 804. ball; 805. reinforcement structure; 806. retaining frame; 9. deep groove ball bearing; 10. fixing rod. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] See also Figure 1-8 The present invention discloses a micro turboprop engine reduction gearbox, comprising a turboprop engine reduction gearbox body 1, a first gear 2 is arranged on the turboprop engine reduction gearbox body 1, a power turbine rotor blade 101 is arranged at the front end of the turboprop engine reduction gearbox body 1, a connecting gear 4 is arranged on the turboprop engine reduction gearbox body 1, a reduction gear 3 is arranged on the turboprop engine reduction gearbox body 1, an input gear 5 is arranged on the turboprop engine reduction gearbox body 1, a connecting shaft 6 is arranged on the turboprop engine reduction gearbox body 1, a ball bearing 8 and a deep groove ball bearing (9) are arranged on the outer surface of the connecting shaft 6, the ball bearing 8 comprises an outer ring 801, a suspension part 802, an inner ring 803, a ball 804, a reinforcing structure 805 and a retaining frame 806, and the ball 804 is multiple, and the turboprop engine reduction gearbox body 1 is provided with an input shaft 7.

[0028] Specifically, the first gear, reduction gear, connecting gear and input gear have the same module and are all spur gears. The input gear 5 is meshed with the reduction gear 3, and the connecting gear 4 is meshed with the first gear 2. The reduction gear 3 has more teeth than the input gear 5, and the tooth width of the reduction gear 3 is slightly wider than that of the input gear 5. The connecting gear 4 has more teeth than the first gear 2.

[0029] Specifically, the connecting gear 4 is fixedly connected to the reduction gear 3 via a fixed shaft 10 , and a deep groove ball bearing 9 is provided on both sides of the front and rear of the fixed shaft 10 . The outer side of the deep groove ball bearing 9 is fixedly connected to the reduction gear box body 1 , and the inner side is fixedly connected to the fixed shaft 10 .

[0030] Specifically, the reinforcing structural member 805 is arranged inside the plastic retaining frame 806, the reinforcing structural member 805 is arranged outside the plastic retaining frame 806 and is firmly connected to the ball bearing 8 retaining frame 806, the reinforcing structural member 805 is arranged as an insert in the plastic retaining frame 806 of the ball bearing 8 retaining frame 806 to reinforce the web area, the reinforcing structural member 805 is formed by a circular annular member or a wire, the reinforcing structural member 805 is formed as a circular annular member with an I-shaped profile, the reinforcing structural member 805 is formed as a circular annular member with an H-shaped profile, the reinforcing structural member 805 is formed as a circular annular member with an X-shaped profile, the reinforcing structural member 805 is formed as a circular annular member with an L-shaped profile, and the reinforcing structural member 805 is formed as a circular annular member with an O-shaped profile.

[0031] Specifically, the retainer 806 of the ball bearing 8 is formed of polyamide-imide, the retainer 806 of the ball bearing 8 is formed of polyetheretherketone, and the retainer 806 of the ball bearing 8 is formed of phenolic resin with fine mesh cotton fabric.

[0032] Specifically, the plurality of balls 804 are distributed in a circular shape in the retaining frame 806 , the inner ring 803 is located inside the retaining frame 806 , and the outer ring 801 includes the retaining frame 806 and the plurality of balls 804 .

[0033] Specifically, the suspension portion 802 is located inside the retaining frame 806 .

[0034] Specifically, the power turbine rotor blade 101 is provided with an internal spline, the front end of the input shaft 7 is provided with an external spline, the turbine rotor blade 101 is connected to the input shaft 7 via the spline, and the input shaft 7 is fixedly connected to the input gear 5 .

[0035] When in use, a gas turbine is fixed at the front end of the turboprop engine reduction gearbox body 1, and the gas turbine at the front end of the turboprop engine reduction gearbox body 1 is started. After the gas turbine is started, it will generate gas, which further drives the turbine rotor blades 101 to rotate, drives the input shaft 7 to rotate, and then drives the input gear 5. The input gear 5 drives the reduction gear 3 to rotate. Due to the gear ratio setting of the reduction gear 3, the rotation speed is slowed down and the torque is increased; then, the rotation of the reduction gear 3 drives the connecting gear 4 to rotate together; the connecting gear 4 acts as a bridge to smoothly transmit power to the first gear 2; finally, the first gear 2 starts to rotate driven by the connecting gear 4, and finally drives the connecting shaft 6 to rotate, thereby reducing the rotation speed of the front power turbine and improving the energy utilization efficiency; this gear set transmission method is widely used in various mechanical equipment, providing stable and reliable power support for industrial production.

[0036] In summary, the micro-turboprop engine reduction gearbox can receive power input from the gas turbine by setting the first gear 2, the reduction gear 3, the connecting gear 4 and the input gear 5, and by setting the input gear 5, the power turbine rotor blades 101 and the input shaft 7; the input gear 5 transmits the power to the reduction gear 3 to achieve a preliminary reduction in the rotation speed; the reduction gear 3 further transmits the power to the connecting gear 4 to ensure the continuity and stability of the power; finally, the connecting gear 4 drives the first gear 2 to rotate, and finally drives the connecting shaft 6 to rotate, and the connecting shaft 6 can be connected to the propeller to achieve the final output of power; the gear ratio setting of the reduction gear 3 significantly reduces the output speed, and the torque increases accordingly; this is very useful for many high-torque engines. The micro-turboprop engine is crucial for applications with high torque and low speed; the effect of deceleration and torque increase can be further optimized, and the energy utilization efficiency of the entire system can be improved; the arrangement of the gear set enables the gears to be arranged closely, reducing the space occupied, and making the entire reduction gear box structure more compact; by arranging the first gear 2, the reduction gear 3, the connecting gear 4 and the input gear 5, the micro-turboprop engine reduction gear box can achieve the beneficial effects of efficient transmission and conversion of power, deceleration and torque increase, compact structure and reliability, functional differentiation and easy maintenance; these effects jointly improve the performance and reliability of the entire system, and provide strong support for the stable operation of the micro-turboprop engine in various application scenarios; by arranging the ball bearing 8, the service life can be increased.

[0037] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A micro turboprop engine reduction gearbox, comprising a turboprop engine reduction gearbox body (1), characterized in that: The turboprop engine reduction gearbox body (1) is provided with a first gear (2), the front end of the turboprop engine reduction gearbox body (1) is provided with a power turbine rotor blade (101), the turboprop engine reduction gearbox body (1) is provided with a connecting gear (4), the turboprop engine reduction gearbox body (1) is provided with a reduction gear (3), the turboprop engine reduction gearbox body (1) is provided with an input gear (5), the turboprop engine reduction gearbox body (1) is provided with a connecting shaft (6), the outer surface of the connecting shaft (6) is provided with a ball bearing (8) and a deep groove ball bearing (9), the ball bearing (8) comprises an outer ring (801), a suspension part (802), an inner ring (803), a ball (804), a reinforcing structure (805) and a retaining frame (806), and the ball (804) is multiple, and the turboprop engine reduction gearbox body (1) is provided with an input shaft (7).

2. A micro turboprop engine reduction gearbox according to claim 1, characterized in that: The first gear (2), the reduction gear (3), the connecting gear (4) and the input gear (5) have the same module and are all spur gears; the input gear (5) is meshed with the reduction gear (3) teeth, the connecting gear (4) is meshed with the first gear (2) teeth, the reduction gear (3) has more teeth than the input gear (5), and the tooth width of the reduction gear (3) is slightly wider than that of the input gear (5); the connecting gear (4) has more teeth than the first gear (2).

3. A micro turboprop engine reduction gearbox according to claim 1, characterized in that: The connecting gear (4) and the reduction gear (3) are fixedly connected via a fixed shaft (10); a deep groove ball bearing (9) is provided on each of the front and rear sides of the fixed shaft (10); the outer side of the deep groove ball bearing (9) is fixedly connected to the reduction gear box body (1), and the inner side is fixedly connected to the fixed shaft (10).

4. A micro turboprop engine reduction gearbox according to claim 1, characterized in that: The reinforcing structure (805) is arranged inside the plastic retainer (806), the reinforcing structure (805) is arranged outside the plastic retainer (806) and is firmly connected to the ball bearing (8) retainer (806), the reinforcing structure (805) is arranged as an insert in the plastic retainer (806) of the ball bearing (8) retainer (806) to reinforce the web area, the reinforcing structure (805) is formed by a circumferential ring-shaped member or a wire, the reinforcing structure (805) is formed as a circumferential ring-shaped member with an I-shaped profile, the reinforcing structure (805) is formed as a circumferential ring-shaped member with an H-shaped profile, the reinforcing structure (805) is formed as a circumferential ring-shaped member with an X-shaped profile, the reinforcing structure (805) is formed as a circumferential ring-shaped member with an L-shaped profile, and the reinforcing structure (805) is formed as a circumferential ring-shaped member with an O-shaped profile.

5. The micro turboprop engine reduction gearbox according to claim 1, characterized in that: The ball bearing (8) retainer (806) is formed of polyamide-imide, the ball bearing (8) retainer (806) is formed of polyetheretherketone, and the ball bearing (8) retainer (806) is formed of phenolic resin with fine mesh cotton fabric.

6. The micro turboprop engine reduction gearbox according to claim 1, characterized in that: A plurality of balls (804) are respectively distributed in a circular shape in a retaining frame (806), the inner ring (803) is located inside the retaining frame (806), and the interior of the outer ring (801) includes the retaining frame (806) and the plurality of balls (804).

7. The micro turboprop engine reduction gearbox according to claim 1, characterized in that: The suspension portion (802) is located inside the retaining frame (806).

8. The micro turboprop engine reduction gearbox according to claim 1, characterized in that: The power turbine rotor blade (101) is provided with an internal spline, the front end of the input shaft (7) is provided with an external spline, the turbine rotor blade (101) and the input shaft (7) are connected via the spline, and the input shaft (7) is fixedly connected to the input gear (5).

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