Multifunctional sleeve gear shaft of aero-engine

Abstract

An inner inclined sleeve tooth is arranged on the inner surface of an annular shaft body of the multifunctional sleeve tooth shaft, and an outer inclined sleeve tooth is arranged on the outer surface of the annular shaft body; outer inclined sleeve teeth are arranged on the outer surface of the aero-engine turbine shaft; inner inclined sleeve teeth are arranged on the inner surface of the central hole of the aero-engine fan or the air compressor rotor. According to the multifunctional sleeve gear shaft of the aero-engine, the design direction of a traditional straight sleeve gear structure is abandoned, the straight sleeve gear structure is improved and upgraded into the inclined sleeve gear structure, in the operation process of the aero-engine, axial micro-movement of the sleeve gear shaft can be restrained, micro-movement abrasion of the sleeve gear shaft can be reduced, meanwhile, axial component force is generated by means of the inclined sleeve gear structure, and the service life of the aero-engine is prolonged. The outer inclined sleeve teeth and the inner inclined sleeve teeth can be tightly attached, fretting wear between the outer inclined sleeve teeth and the inner inclined sleeve teeth is further restrained, particularly, a metal rubber filling body is additionally arranged in the annular shaft body of the sleeve gear shaft, the damping function is achieved through the metal rubber filling body, and the service life of the sleeve gear shaft is prolonged. And finally, further improvement of the performance of the aero-engine is effectively assisted.

Description

Technical Field

[0001] The invention belongs to the technical field of structural design of aircraft engine parts, and in particular relates to a multifunctional sleeve gear shaft of an aircraft engine. Background Art

[0002] At present, the turbine shaft of an aircraft engine and the rotor of a fan or compressor are usually connected by a sleeve gear shaft. An external straight sleeve tooth is provided on the outer surface of the turbine shaft of the aircraft engine, and an internal straight sleeve tooth is provided on the inner surface of the center hole of the rotor of the fan or compressor. The outer surface of the sleeve gear shaft is provided with external straight sleeve teeth, and the inner surface of the sleeve gear shaft is provided with internal straight sleeve teeth. The outer straight sleeve teeth on the outer surface of the sleeve gear shaft cooperate with the inner straight sleeve teeth on the inner surface of the center hole of the fan or compressor rotor, and the inner straight sleeve teeth on the inner surface of the sleeve gear shaft cooperate with the outer straight sleeve teeth on the outer surface of the turbine shaft.

[0003] However, due to the continuous improvement of aircraft engine performance and the influence of the meshing clearance when the external straight sleeve gear and the internal straight sleeve gear cooperate, the micro-wear of the sleeve gear shaft during the operation of the aircraft engine is becoming more and more serious, which seriously restricts the further improvement of aircraft engine performance. Summary of the Invention

[0004] In response to the problems existing in the prior art, the present invention provides a multifunctional sleeve gear shaft for an aircraft engine, which abandons the traditional design direction of a straight sleeve gear structure and improves and upgrades the straight sleeve gear structure to an oblique sleeve gear structure. During the operation of the aircraft engine, the axial micro-movement of the sleeve gear shaft can be suppressed, and the micro-motion wear of the sleeve gear shaft can be reduced. At the same time, the oblique sleeve gear structure generates an axial component force, which can form a tight fit between the outer oblique sleeve gear and the inner oblique sleeve gear, further suppressing the micro-motion wear between the outer oblique sleeve gear and the inner oblique sleeve gear. In addition, a metal rubber filler is specially added inside the circumferential shaft body of the sleeve gear shaft, and a shock-absorbing function is achieved through the metal rubber filler, which ultimately effectively contributes to further improvement of the performance of the aircraft engine.

[0005] In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a multifunctional sleeve gear shaft of an aircraft engine, having an inner beveled sleeve gear provided on the inner surface of its circumferential shaft body, and an outer beveled sleeve gear provided on the outer surface of the circumferential shaft body; an outer beveled sleeve gear is also provided on the outer surface of the turbine shaft of the aircraft engine; an inner beveled sleeve gear is also provided on the inner surface of the center hole of the rotor of the fan or compressor of the aircraft engine; the inner beveled sleeve gear on the inner surface of the circumferential shaft body is meshed with the outer beveled sleeve gear on the outer surface of the turbine shaft of the aircraft engine; the outer beveled sleeve gear on the outer surface of the circumferential shaft body is meshed with the inner beveled sleeve gear on the inner surface of the center hole of the rotor of the fan or compressor of the aircraft engine.

[0006] A metal rubber filler for shock absorption is fixedly filled in the annular shaft.

[0007] Beneficial effects of the present invention:

[0008] The multifunctional sleeve gear shaft for an aircraft engine of the present invention abandons the traditional design direction of a straight sleeve gear structure and improves and upgrades the straight sleeve gear structure to an oblique sleeve gear structure. During the operation of the aircraft engine, the axial micro-movement of the sleeve gear shaft can be suppressed, and the micro-motion wear of the sleeve gear shaft can be reduced. At the same time, the axial component force is generated by the oblique sleeve gear structure, so that the outer oblique sleeve gear and the inner oblique sleeve gear can be closely fitted, further suppressing the micro-motion wear between the outer oblique sleeve gear and the inner oblique sleeve gear. In addition, a metal rubber filler is specially added inside the circumferential shaft body of the sleeve gear shaft, and a shock-absorbing function is achieved through the metal rubber filler, which ultimately effectively contributes to further improvement of the performance of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 This is a schematic structural diagram of a multifunctional sleeve gear shaft for an aircraft engine according to the present invention;

[0010] In the figure, 1 is the circumferential shaft, 2 is the inner bevel gear, 3 is the outer bevel gear, and 4 is the metal rubber filler. DETAILED DESCRIPTION

[0011] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0012] like Figure 1 As shown, a multifunctional sleeve gear shaft of an aircraft engine has inner beveled sleeve teeth 2 provided on the inner surface of its annular shaft body 1, and outer beveled sleeve teeth 3 provided on the outer surface of the annular shaft body 1; outer beveled sleeve teeth 3 are also provided on the outer surface of the turbine shaft of the aircraft engine; inner beveled sleeve teeth 2 are also provided on the inner surface of the central hole of the rotor of the fan or compressor of the aircraft engine; the inner beveled sleeve teeth 2 on the inner surface of the annular shaft body 1 are meshed with the outer beveled sleeve teeth 3 on the outer surface of the turbine shaft of the aircraft engine; the outer beveled sleeve teeth 3 on the outer surface of the annular shaft body 1 are meshed with the inner beveled sleeve teeth 2 on the inner surface of the central hole of the rotor of the fan or compressor of the aircraft engine.

[0013] The interior of the annular shaft body 1 is fixedly filled with a metal rubber filler 4 for shock absorption.

[0014] When the multifunctional sleeve gear shaft of the present invention is adopted in an aircraft engine, by improving and upgrading the straight sleeve gear structure to an oblique sleeve gear structure, the axial micro-movement of the sleeve gear shaft can be suppressed during the operation of the aircraft engine, and the micro-motion wear of the sleeve gear shaft can be reduced. At the same time, the axial component force is generated by the oblique sleeve gear structure, so that the outer oblique sleeve gear 3 and the inner oblique sleeve gear 2 can be tightly fitted, further suppressing the micro-motion wear between the outer oblique sleeve gear 3 and the inner oblique sleeve gear 2. At the same time, the metal rubber filler 4 added to the interior of the sleeve gear shaft 1 can also realize a shock-absorbing function, which can effectively help to further improve the performance of the aircraft engine.

[0015] The solutions in the embodiments are not intended to limit the scope of protection of the present invention. All equivalent implementations or modifications that do not depart from the scope of protection of the present invention are included in the scope of protection of the present invention.

Claims

1. A multifunctional sleeve gear shaft for an aircraft engine, characterized in that: Inner beveled sleeve teeth are arranged on the inner surface of the annular shaft body, and outer beveled sleeve teeth are arranged on the outer surface of the annular shaft body; outer beveled sleeve teeth are also arranged on the outer surface of the turbine shaft of the aircraft engine; inner beveled sleeve teeth are also arranged on the inner surface of the rotor center hole of the fan or compressor of the aircraft engine; the inner beveled sleeve teeth on the inner surface of the annular shaft body are meshed with the outer beveled sleeve teeth on the outer surface of the turbine shaft of the aircraft engine; the outer beveled sleeve teeth on the outer surface of the annular shaft body are meshed with the inner beveled sleeve teeth on the inner surface of the rotor center hole of the fan or compressor of the aircraft engine.

2. The multifunctional sleeve gear shaft of an aircraft engine according to claim 1, characterized in that: A metal rubber filler for shock absorption is fixedly filled inside the annular shaft body.

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