A worm gear shaft inner supercharging structure

Abstract

The application relates to a worm shaft and pressure increasing structure, wherein the worm shaft is a hollow shaft, the worm shaft is provided with a radial through hole, the pressure increasing structure is fixed in the shaft cavity of the worm shaft, and the pressure increasing structure comprises an inner ring, an outer ring and blades. When the engine works, oil gas enters the inside of the shaft cavity of the worm shaft, and the oil gas is efficiently discharged from the cavity under the assistance of the pressure increasing device, so that the working pressure of the exhaust related components behind the worm shaft is relieved, the exhaust efficiency is increased, the internal and external pressures of the worm shaft are balanced, and the service life and reliability of the worm shaft and related components are prolonged.

Description

Technical Field

[0001] This invention relates to the field of mechanical structure technology, and in particular to an internal turbocharger structure for a turbine shaft. Background Technology

[0002] The turbine shaft of an aircraft engine serves a transmission function and is a rotating component, an important part of the turbine. One end of the turbine shaft is connected to the compressor shaft, and the other end is connected to the turbine disk. Bearings are mounted circumferentially, and there are evenly distributed vent holes on the shaft side. During engine operation, some of the fuel gas produced enters the shaft cavity through the holes on the turbine shaft and is subsequently discharged from the end of the turbine shaft. Currently, there is no mechanical structure to assist in the fuel gas discharge process. Summary of the Invention

[0003] The purpose of this invention is to install the structure in the turbine shaft cavity, which can pressurize the end of the shaft cavity and assist in the discharge of oil and gas inside the shaft cavity.

[0004] The technical solution of this invention is:

[0005] A worm gear shaft in-screw pressurization structure is provided, comprising a worm gear shaft and a pressurization structure. The worm gear shaft is a hollow shaft with a radial through hole. The pressurization structure is fixed in the shaft cavity of the worm gear shaft. The pressurization structure includes an inner ring, an outer ring, and blades. The inner and outer rings are coaxial with the worm gear shaft, and the outer ring is fixed to the inner wall of the shaft cavity of the worm gear shaft. Multiple blades are uniformly distributed in a ring shape between the inner and outer rings. The pressurization structure can rotate integrally with the worm gear shaft. When the worm gear shaft rotates, the blades can guide oil and gas outside the worm gear shaft into the shaft cavity of the worm gear shaft through the through hole and exit from the open end of the worm gear shaft. Its working principle is: pressurization is applied at the end of the worm gear shaft (open end) to create a suction pressure difference, guiding and discharging residual oil and gas outside the worm gear shaft.

[0006] Furthermore, the outer ring has a diameter of 37 mm; the inner ring has a diameter of 5 mm.

[0007] Furthermore, the outer ring has a thickness of 1.5 mm; the inner ring has a thickness of 1 mm.

[0008] Furthermore, the blade has 8 segments.

[0009] Furthermore, there are multiple through holes, symmetrically arranged with respect to the central axis of the worm gear shaft.

[0010] Furthermore, the open end is the tail end of the worm gear shaft.

[0011] Furthermore, the inner ring is a solid cylinder.

[0012] Furthermore, the blades are made of lightweight metal materials, such as aluminum alloys or titanium alloys.

[0013] Furthermore, the pressurization structure is manufactured by integral casting, integral CNC machining, or 3D printing.

[0014] The advantages of this invention are: when the engine is running, the oil and gas enter the turbine shaft cavity, and with the assistance of the newly designed supercharging device, the oil and gas are efficiently discharged from the cavity. This not only relieves the working pressure on the exhaust-related components after the turbine shaft and increases exhaust efficiency, but also balances the internal and external pressures of the turbine shaft, extending the service life and reliability of the turbine shaft and related components. Simultaneously, it solves the problem of optimizing the aerodynamic layout of turbine components, saving on the number of parts and improving design efficiency.

[0015] This invention makes efficient use of limited space, and its installation has no impact on the installation and use of other components. It features a simple and compact structure, unrestricted installation methods, low cost, and high feasibility. Utilizing the turbine shaft's own rotational performance, it requires no additional input structures. It achieves pressure balance inside and outside the turbine shaft cavity, which helps extend the turbine shaft's service life. It is suitable for small turboshaft, turbofan, and turbojet engines, with a wide range of applications. It allows for the smooth discharge of residual oil and gas, which helps extend bearing life. This structure provides some reinforcement to the turbine shaft's strength, increasing its reliability. This structure can alleviate the working pressure on exhaust-related components downstream of the turbine shaft, increasing exhaust efficiency. The number and structure of the fan blades can be adjusted according to requirements through aerodynamic calculations, offering high versatility. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of an embodiment of the present invention;

[0017] Figure 2 This is an axial sectional view of an embodiment of the present invention;

[0018] Figure 3 This is a schematic diagram of the existing technology;

[0019] Wherein: 1-worm gear shaft, 2-boosting structure, 3-oil and gas, 21-outer ring, 22-blade, 23-inner ring. Detailed Implementation

[0020] The disclosed examples will be described more fully with reference to the accompanying drawings, in which some (but not all) of the disclosed examples are shown. In fact, many different examples may be described, and these examples should not be construed as limited to those set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete, and will fully convey the scope of this disclosure to those skilled in the art.

[0021] Conventional turbine shaft structure is shown below Figure 1-2. There is no auxiliary oil and gas discharge structure design in the shaft cavity. The discharge of oil and gas relies on the accumulation of oil and gas in the cavity and the increase of pressure, and on the exhaust-related components behind the turbine shaft, which are far away. Therefore, there is room for optimization in the discharge of oil and gas.

[0022] A worm gear shaft in-screw pressurization structure is provided, comprising a worm gear shaft and a pressurization structure. The worm gear shaft is a hollow shaft with a radial through hole. The pressurization structure is fixed in the shaft cavity of the worm gear shaft. The pressurization structure includes an inner ring, an outer ring, and blades. The inner and outer rings are coaxial with the worm gear shaft, and the outer ring is fixed to the inner wall of the shaft cavity of the worm gear shaft. Multiple blades are uniformly distributed in a ring shape between the inner and outer rings. The pressurization structure can rotate integrally with the worm gear shaft. When the worm gear shaft rotates, the blades can guide oil and gas outside the worm gear shaft into the shaft cavity of the worm gear shaft through the through hole and exit from the open end of the worm gear shaft. Its working principle is: pressurization is applied at the end of the worm gear shaft (open end) to create a suction pressure difference, guiding and discharging residual oil and gas outside the worm gear shaft.

[0023] The outer ring has a diameter of 37 mm; the inner ring has a diameter of 5 mm.

[0024] The outer ring has a thickness of 1.5 mm; the inner ring has a thickness of 1 mm.

[0025] The blade has 8 segments.

[0026] There are multiple through holes, which are symmetrically arranged with respect to the central axis of the worm gear shaft.

[0027] The open end is the tail end of the worm gear shaft.

[0028] The inner ring is a solid cylinder.

[0029] It has a simple and compact structure and can be manufactured by welding or casting, making it easy to process.

[0030] The structure is connected and fixed to the turbine shaft by welding or fixing the mounting edge. When the engine is working, the fan blades rotate together with the turbine shaft to pressurize the end of the turbine shaft and achieve the purpose of assisting in the discharge of oil and gas.

[0031] This structure effectively facilitates the discharge of oil and gas from the shaft cavity during engine operation, thereby improving the service life and reliability of related components.

[0032] Descriptions of various advantageous arrangements have been shown for illustrative and descriptive purposes, but such descriptions are not intended to be exclusive or limited to the disclosed forms. Many modifications and variations will be apparent to those skilled in the art. Furthermore, different advantageous examples may describe different advantages compared to other advantageous examples. One or more examples have been selected and described in order to best illustrate the principles and practical application of the examples, and to enable those skilled in the art to understand that this disclosure contains various examples with various modifications suitable for the particular intended use.

Claims

1. A worm gear shaft internal pressure boosting structure, characterized in that: The device includes a worm gear shaft and a booster structure. The worm gear shaft is a hollow shaft with a radial through hole. The booster structure is fixed in the shaft cavity of the worm gear shaft. The booster structure includes an inner ring, an outer ring, and blades. The inner and outer rings are coaxial with the worm gear shaft, and the outer ring is fixed to the inner wall of the shaft cavity of the worm gear shaft. There are multiple blades, all of which are evenly distributed in a ring shape between the inner and outer rings. The booster structure can rotate as an integral part of the worm gear shaft. When the worm gear shaft rotates, the blades can guide oil and gas from outside the worm gear shaft into the shaft cavity of the worm gear shaft through the through hole and out through the open end of the worm gear shaft.

2. A turbo-axle supercharging structure according to claim 1, characterized in that: The outer ring has a diameter of 37 mm; the inner ring has a diameter of 5 mm.

3. A turbo-axle supercharging structure according to claim 1, characterized in that: The outer ring has a thickness of 1.5 mm; the inner ring has a thickness of 1 mm.

4. A turbo-axle supercharging structure according to claim 1, wherein: The blade has 8 segments.

5. A turbo-axle supercharging structure according to claim 1, wherein: There are multiple through holes, which are symmetrically arranged with respect to the central axis of the worm gear shaft.

6. A turbo-axle supercharging structure according to claim 1, wherein: The open end is the tail end of the worm gear shaft.

7. A turbo-axle supercharging structure according to claim 1, characterized in that: The inner ring is a solid cylinder.

8. A turbo-axle supercharging structure according to claim 1, characterized in that: The blades are made of lightweight metal materials, such as aluminum alloy or titanium alloy.

9. A turbo-axle supercharging arrangement as claimed in claim 1, wherein: The pressurization structure is manufactured by integral casting, integral CNC machining, or 3D printing.

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