CN212657001U

CN212657001U - Engine fan driving structure

Info

Publication number: CN212657001U
Application number: CN202021396014.7U
Authority: CN
Inventors: 梁霄; 徐和; 车俊龙; 宋健
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2020-07-15
Filing date: 2020-07-15
Publication date: 2021-03-05
Anticipated expiration: 2030-07-15

Abstract

The utility model relates to an engine fan drive structure. The fan of the engine fan driving structure comprises a blade disc and blades arranged on the blade disc; the adapter shaft is connected with a low-pressure rotor of the engine and is driven to rotate by the low-pressure rotor; the intermediate bearing is arranged between the blade disc and the adapter shaft, and the adapter shaft supports the blade disc and the blades through the intermediate bearing; the planet wheel assembly is arranged between the blade disc and the adapter shaft, the adapter shaft drives the blade disc to rotate through the planet wheel assembly, and the planet wheel assembly is arranged at the rear part of the adapter shaft relative to the intermediate bearing. The utility model provides an engine fan drive structure, overall structure is compact, reduces weight, improves the work efficiency of engine.

Description

Engine fan driving structure

Technical Field

The utility model relates to an aeroengine designs and makes technical field, especially relates to an engine fan drive structure.

Background

At present, a gear-driven fan (GTF) engine is a double-shaft turbofan engine in which a planetary reduction gear mechanism is introduced between a low-pressure compressor and a fan, and a gear system is flexibly connected, so that the fan, the low-pressure compressor and a low-pressure turbine can simultaneously work at relatively ideal rotating speeds, thereby reducing the number of stages of the low-pressure compressor and the turbine, reducing the noise of the engine, and reducing the oil consumption of the engine. The reduced components just offset the weight associated with the addition of the reduction gear mechanism. The drive gear system needs to transmit large power, and also has low mass and high reliability. Maintenance costs for GTF engines are expected to be saved by 40%. Because the speed reducer adopts a large number of high-speed heavy-load gears and bearings, the working condition is severe, the speed reducer needs to work safely and reliably under the conditions of high input rotating speed and high transmission power, and the speed reducer is very difficult to realize under the condition of the prior art. Even if the transmission efficiency is achieved, the amount of heat generated is very high, which is very demanding in terms of lubrication, cooling, gearbox distortion control techniques, etc. It is a challenge to have a reduction gearbox that meets the design requirements of light weight, high efficiency, and high reliability. The existing GTF engine generally needs a reduction box which is arranged between a fan and a booster stage, so that the axial size of the engine is lengthened and the structure is complex. Although the application is started abroad, the problems are more.

For example, chinese patent application CN201410309501.8 discloses a novel GTF aero-engine fan main reducer. Referring to fig. 1, the left end of an input shaft 3 is connected with a low-pressure turbine, the low-pressure turbine transmits rotary power to the input shaft 3, the input shaft 3 is mounted on a left box cover 5 through a sliding bearing, an input end cover 4 penetrates through the input shaft 3 to be positioned and sealed, the input end cover 4 is fixed on the outer surface of the left box cover 5 through a bolt, the left box cover 5 is fixed on a box 6 through a bolt, the right end of the box 6 is fixed with a right box cover 10 through a bolt, an output end cover 14 plays a role in positioning a spherical roller bearing 11, and the output end cover 14 is fixed on the right end face of the right box cover 10 through a bolt. The right end of an input shaft 3 is connected with an internal spline of a sun wheel 15 through an external spline, an input shaft plug 13 is arranged at an oil hole at the right end of the input shaft 3 and used for storing lubricating oil, the sun wheel 15 is simultaneously meshed with 5 star wheels 16, the star wheels 16 are arranged on a left box body cover 5 through a star wheel shaft 1, a star wheel shaft plug 2 is arranged at the right end of the star wheel shaft 1, a lining 17 for automatically compensating the flexible deformation of a cantilever end is arranged on the outer surface of the shaft diameter and ensuring the flexible load-sharing effect, shaft elastic check rings A18 and B19 are respectively arranged on the star wheel shaft 1 and used for keeping the reserved axial floating amount of the star wheels 16, firstly, the sun wheel 15 divides power to the 5 star wheels 16, then the 5 star wheels 16 converge the power to an internal gear ring A20 and an internal gear B21, then the internal gear A20 and the internal gear B21 are connected with a gear coupling 7 through the external, finally, the gear coupling 7 transmits power to the output shaft 12 through the internal spline, the left end and the right end of the gear coupling 7 are respectively provided with the elastic retainer ring 8 and the elastic positioning ring 9 for holes, necessary axial floating amount of the star wheel 16 is guaranteed, axial positioning is carried out simultaneously, large-range axial movement of the star wheel 16 is prevented, the output shaft 12 is arranged on the right box cover 10 through the spherical roller bearing 11, the right end of the output shaft 12 is connected with an aircraft engine fan to drive the fan to run, so that the power is transmitted to the aircraft engine fan through the speed reducer by the low-pressure turbine of the aircraft engine, and the whole process of speed reduction and torque increase is completed. The whole structure is complex, and the problem of transmission reliability exists.

SUMMERY OF THE UTILITY MODEL

To the above-mentioned problem of prior art, the utility model provides an engine fan drive structure, overall structure is compact, reduces weight, improves the work efficiency of engine.

Specifically, the utility model provides an engine fan drive structure, include:

the fan comprises a blade disc and blades arranged on the blade disc;

the adapter shaft is connected with a low-pressure rotor of an engine and is driven to rotate by the low-pressure rotor;

an intermediate bearing disposed between the blisk and the transfer shaft, the transfer shaft passing through the intermediate bearing to support the blisk and the blades;

the planetary wheel assembly is arranged between the blade disc and the transfer shaft, the transfer shaft drives the blade disc to rotate through the planetary wheel assembly, and the planetary wheel assembly is arranged at the rear part of the transfer shaft relative to the intermediate bearing.

According to the utility model discloses an embodiment, the inner ring of intermediary's bearing is followed the change over spindle is rotatory, the outer loop of intermediary's bearing is followed the bladed disk is rotatory.

According to the utility model discloses an embodiment, the planet wheel subassembly includes ring gear, planet wheel and sun gear, the sun gear is installed change epaxial, the planet wheel respectively with sun gear and ring gear meshing, the ring gear with the bladed disk cooperation is fixed, change epaxial through sun gear and planet wheel variable speed after, the warp the ring gear drive the bladed disk rotates.

According to the utility model discloses an embodiment, the planet wheel subassembly still include the bolt and with the fixed nut of bolt cooperation be equipped with the bolt hole on the bladed disk, the ring gear passes through the bolt penetrates the bolt hole is fixed by the nut on the bladed disk.

According to the utility model discloses an embodiment, the planet wheel subassembly still includes axis stop gear, sets up the both sides of ring gear, by the bolt penetrates axis stop gear and ring gear and fixed with bolt hole screw-thread fit, axis stop gear is used for the restriction the axial float of ring gear.

According to the utility model discloses an embodiment, the quantity of planet wheel is 3 to 5.

According to an embodiment of the present invention, the inner diameter surface of the blisk and the surface of the transfer shaft form a receiving space for the intermediate bearing.

According to an embodiment of the present invention, a convex shoulder is formed on the surface of the adapter shaft, and the intermediate bearing is disposed in the accommodating space and attached to the shoulder.

According to the utility model discloses an embodiment, intermediary's bearing includes inner ring gland nut and outer loop gland nut the internal diameter surface of bladed disk forms first screw thread the switching shaft surface forms the second screw thread, outer loop gland nut with first screw-thread fit is with compressing tightly fixed the outer loop of bearing, inner ring gland nut with second screw-thread fit is with compressing tightly fixed the inner ring of bearing.

According to the utility model discloses an embodiment, the blade root portion of blade forms the forked tail shape the external diameter surface of bladed disk forms the dovetail, and both cooperate fixedly.

The utility model provides a pair of engine fan drive structure, fan pass through intermediary bearing support, and the change shaft passes through planet wheel subassembly direct drive fan and rotates, simplifies the engine structure, reduces engine axial dimensions, reduces the engine progression, reduces weight, improves engine work efficiency.

It is to be understood that both the foregoing general description and the following detailed description of the present invention are exemplary and explanatory and are intended to provide further explanation of the invention as claimed.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principle of the invention. In the drawings:

FIG. 1 shows a schematic representation of a prior art GTF engine.

Fig. 2 shows a schematic structural diagram of an engine fan driving structure according to an embodiment of the present invention.

Fig. 3 shows a schematic structural view of the blisk in fig. 2.

Fig. 4 shows a schematic structural view of the adapter shaft in fig. 2.

Fig. 5 shows a schematic view of the blade of fig. 2.

Wherein the figures include the following reference numerals:

engine fan drive structure 200 fan 201

The transfer shaft 202 is supported by a bearing 203

Planetary wheel assembly 204 blisk 205

Inner ring 207 of blades 206

Planet gear 208 sun gear 209

Bolt 210 and nut 211

Bolt hole 212 axis limiting mechanism 213

Shoulder 214 inner ring gland nut 215

Outer ring compression nut 216 first thread 217

Second thread 218 dovetail shape 219

Dovetail groove 220

Detailed Description

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.

The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It should be apparent that the described embodiments are only some of the embodiments of the present application, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the application, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.

The relative arrangement of the components and steps, the numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present application unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

In the description of the present application, it is to be understood that the orientation or positional relationship indicated by the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the orientation or positional relationship shown in the drawings, and are used for convenience of description and simplicity of description only, and in the case of not making a reverse description, these directional terms do not indicate and imply that the device or element being referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore, should not be considered as limiting the scope of the present application; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.

Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may also be oriented 90 degrees or at other orientations and the spatially relative descriptors used herein interpreted accordingly.

It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of protection of the present application is not to be construed as being limited. Further, although the terms used in the present application are selected from publicly known and used terms, some of the terms mentioned in the specification of the present application may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein. Further, it is required that the present application is understood not only by the actual terms used but also by the meaning of each term lying within.

Fig. 2 shows a schematic structural diagram of an engine fan driving structure according to an embodiment of the present invention. Fig. 3 shows a schematic structural view of the blisk in fig. 2. Fig. 4 shows a schematic structural view of the adapter shaft in fig. 2. As shown, an engine fan drive structure 200 mainly includes a fan 201, a transfer shaft 202, an intermediate bearing 203, and a planetary gear assembly 204.

The fan 201 includes a blade disk 205 and blades 206 disposed on the blade disk 205.

The coupling shaft 202 is connected to a low-pressure spool of the engine, and the low-pressure spool drives the coupling shaft 202 to rotate.

An intermediate bearing 203 is provided between the disk 205 and the spindle 202, and the spindle 202 supports the disk 205 and the blades 206 via the intermediate bearing 203.

The planet assembly 204 is disposed between the blisk 205 and the adapter shaft 202. The adapter shaft 202 drives the blade disc 205 to rotate through a planetary wheel assembly 204, and the planetary wheel assembly 204 is arranged at the rear part of the adapter shaft 202 relative to the intermediate bearing 203. The front and rear refer to the air intake direction of the engine, and the air intake direction of the engine in fig. 2 is from left to right, i.e., front to left and rear to right. As will be readily appreciated, the intermediate bearing 203 is disposed at the forward end of the transfer shaft 202 and the planet assembly 204 is disposed at the rearward end of the transfer shaft 202.

The utility model provides a pair of engine fan drive structure 200, wherein fan 201 supports on adapter shaft 202 through intermediary's bearing 203, and fan 201 is direct drive after by planet wheel subassembly 204 variable speed. The speed of the fan 201 can be achieved by adjusting the transmission ratio of the planetary gear assembly 204 as required. The structure can simplify the structure of the engine, reduce the axial size of the engine, reduce the number of stages of the engine and further improve the working efficiency of the engine. The problem that current GTF engine exists is solved. Meanwhile, the structure is simplified, so the weight is reduced, the design difficulty of the lubricating oil system is reduced, the fuel consumption rate is reduced, and the noise is reduced to a certain extent.

Preferably, the inner ring of the intermediate bearing 203 follows the rotation of the transfer shaft 202, and the relative rotation speed is high. The outer ring of the intermediate bearing 203 follows the rotation of the blisk 205 with a low relative speed.

Preferably, the planetary assembly 204 includes an inner gear ring 207, planetary gears 208, and a sun gear 209. A sun gear 209 is mounted on the transfer shaft 202, and planet gears 208 are respectively meshed with the sun gear 209 and the ring gear 207. The inner gear ring 207 is matched and fixed with the fan disc 205, and the fan disc 205 is driven to rotate by the inner gear ring 207 after the speed of the adapter shaft 202 is changed through the sun gear 209 and the planet gears 208.

Preferably, the planet assembly 204 further includes a bolt 210 and a nut 211 engaged with the bolt 210. The fan disc 205 is provided with bolt holes 212, and the ring gear 207 is fixed to the fan disc 205 by bolts 210 inserted through the bolt holes 212 and nuts 211. Preferably, the planet assembly 204 further includes an axis limiting mechanism 213, and the axis limiting mechanism 213 is disposed on two sides of the ring gear 207. When assembling, the bolt 210 penetrates the axis limiting mechanism 213 and the inner gear ring 207 and is fixed with the bolt hole 212 in a threaded fit manner. The axis limiting mechanism 213 is used for limiting the axial movement of the inner gear ring 207 and improving the stability of the driving fan 201.

Preferably, the number of planet wheels 208 is 3 to 5.

Preferably, a receiving space for disposing the intermediate bearing 203 is formed between the inner diameter surface of the fan disc 205 and the surface of the coupling shaft 202. Preferably, a protruding shoulder 214 is formed on the surface of the adapter shaft 202, and the intermediate bearing 203 is disposed in the receiving space and abuts against the shoulder 214. The installation of the medium bearing 203 is convenient, and the positioning is accurate.

Preferably, the intermediate bearing 203 includes an inner ring compression nut 215 and an outer ring compression nut 216. Referring to fig. 3 and 4, a first screw thread 217 is formed on the inner diameter surface of the fan disc 205, and a second screw thread 218 is formed on the surface of the adaptor shaft 202. Wherein an outer ring compression nut 216 cooperates with the first thread 217 to compress the outer ring of the fixed bearing during assembly. Inner ring compression nut 215 cooperates with second threads 218 to compress the inner ring of the stationary bearing during assembly.

Fig. 5 shows a schematic view of the blade 206 of fig. 2. As shown in fig. 3, the blade 206 has a dovetail shape 219 formed at the root portion thereof and a dovetail groove 220 formed at the outer diameter surface of the fan disk 205, and both are fixed in a form-fitting manner. By way of example and not limitation, the blade root of the blade 206 may also be formed with a short palm tree shape, with a corresponding short palm tree groove formed in the outer diameter surface of the fan disc 205 to secure the blade 206. The blade root of the blade 206 and the outer diameter surface of the fan disc 205 may also be formed in other simplified structures as long as they are suitable for assembly and convenient fixing.

The assembly process of the present invention for the fan driving structure 200 of the engine will be described in detail with reference to all the drawings.

1. The planet wheel assembly 204 is installed, the planet wheel 208 is meshed with the sun wheel 209, the inner gear ring 207 and the axial limiting mechanism are installed, the planet wheel assembly 204 is formed, and a bolt 210 penetrates from the right side to the left side.

2. The bearing back half inner ring is mounted to the adapter shaft 202 in position against the shoulder 214.

3. The fan disc 205 is first assembled with the outer ring of the bearing (containing the cage, rolling elements) in place by an outer ring gland nut 216. Then the bearing is installed in place with the rear half inner ring of the bearing, then the front half inner ring of the bearing is installed in place, finally the inner ring compression nut 215 is screwed down, and the intermediate bearing 203 is fastened.

4. The ring gear 207 is aligned with the bolt hole 212 of the fan disc 205, the bolt 210 is screwed into the bolt hole 212, and the other end of the bolt 210 is fastened and fixed by the nut 211.

5. The blade 206 is installed.

The utility model provides a pair of engine fan drive structure's advantage as follows:

1. the rotating speed of the fan can adjust the transmission ratio of the planetary wheel assembly as required;

2. the fan is independently supported by the intermediate bearing, so that the mutual interference between the rotors can be avoided;

3. the fan disc adopts an integrated design and can be simultaneously provided with blades, bearings, inner gear rings and axial limiting mechanisms;

4. the blade root part connecting structure can be a dovetail groove or a short palm tree groove, so that the structure is simplified and the assembly is convenient;

5. the number of the low-pressure rotor stages of the engine can be further reduced;

6. the processing and assembling difficulty is reduced;

7. the reliability of the engine is improved;

8. the weight reduction brings about a reduction in fuel consumption and a reduction in noise.

It will be apparent to those skilled in the art that various modifications and variations can be made to the above-described exemplary embodiments of the present invention without departing from the spirit and scope of the invention. Thus, it is intended that the present invention cover the modifications and variations of this invention provided they come within the scope of the appended claims and their equivalents.

Claims

1. An engine fan drive structure, characterized by comprising:

the fan comprises a blade disc and blades arranged on the blade disc;

2. The engine fan drive structure of claim 1, wherein the inner ring of the intermediate bearing rotates with the adapter shaft, and the outer ring of the intermediate bearing rotates with the blisk.

3. The engine fan driving structure according to claim 2, wherein the planetary wheel assembly includes an inner gear ring, planet wheels, and a sun wheel, the sun wheel is mounted on the connecting shaft, the planet wheels are respectively engaged with the sun wheel and the inner gear ring, the inner gear ring is fixed in cooperation with the blisk, and the connecting shaft is driven by the inner gear ring to rotate after being shifted by the sun wheel and the planet wheels.

4. The engine fan driving structure according to claim 3, wherein the planetary wheel assembly further includes a bolt and a nut engaged with and fixed to the bolt, a bolt hole is provided in the blisk, and the ring gear is inserted into the bolt hole through the bolt and fixed to the blisk by the nut.

5. The engine fan driving structure according to claim 4, wherein the planetary wheel assembly further includes axis limiting mechanisms provided on both sides of the ring gear, the axis limiting mechanisms and the ring gear being inserted by the bolts and fixed in threaded engagement with the bolt holes, the axis limiting mechanisms being configured to limit axial play of the ring gear.

6. The engine fan drive of claim 3, wherein the number of planet wheels is 3 to 5.

7. The engine fan driving structure according to claim 1, wherein a receiving space in which the intermediate bearing is provided is formed between an inner diameter surface of the blisk and a surface of the spindle.

8. The engine fan drive structure of claim 7, wherein a protruding shoulder is formed on a surface of the transfer shaft, and the intermediate bearing is disposed in the receiving space and abuts against the shoulder.

9. The engine fan drive structure of claim 7, wherein the intermediate bearing comprises an inner ring compression nut and an outer ring compression nut, a first thread is formed on an inner diameter surface of the blisk, a second thread is formed on a surface of the spindle, the outer ring compression nut is engaged with the first thread to compressively fix the outer ring of the bearing, and the inner ring compression nut is engaged with the second thread to compressively fix the inner ring of the bearing.

10. The engine fan drive structure according to claim 1, wherein the blade root portion of the blade is formed in a dovetail shape, and a dovetail groove is formed in an outer diameter surface of the disk, and both are fitted and fixed.