CN114810348A - Transmission mechanism, turbofan engine and assembly method - Google Patents
Transmission mechanism, turbofan engine and assembly method Download PDFInfo
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- CN114810348A CN114810348A CN202110067944.0A CN202110067944A CN114810348A CN 114810348 A CN114810348 A CN 114810348A CN 202110067944 A CN202110067944 A CN 202110067944A CN 114810348 A CN114810348 A CN 114810348A
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 26
- 238000000034 method Methods 0.000 title claims abstract description 18
- 230000007246 mechanism Effects 0.000 title claims abstract description 16
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 24
- 238000001816 cooling Methods 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 4
- 230000004323 axial length Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000001050 lubricating effect Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 239000007789 gas Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H1/00—Toothed gearings for conveying rotary motion
- F16H1/28—Toothed gearings for conveying rotary motion with gears having orbital motion
- F16H1/32—Toothed gearings for conveying rotary motion with gears having orbital motion in which the central axis of the gearing lies inside the periphery of an orbital gear
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
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Abstract
The invention relates to a transmission mechanism, a turbofan engine and an assembling method. The transmission mechanism comprises a fan disc, and a first face gear is arranged on the axial downstream end face of the fan disc; the planetary gear assembly is positioned at the downstream of the fan disc and comprises an inner gear ring, a planet gear and a sun gear, and the axial upstream end surface of the inner gear ring is provided with a second end surface gear; wherein the first face gear meshes with a second face gear such that the fan disc is coupled with the planetary gear assembly.
Description
Technical Field
The invention relates to the field of turbofan engines, in particular to a transmission mechanism, a turbofan engine and an assembly method.
Background
A Geared Turbofan (GTF) engine is an improvement over conventional Turbofan engines. In the conventional turbofan engine, the rotating speed of the fan is limited to ensure that the tangential speed of the blade tip of the fan does not exceed a certain value (if the tangential speed of the blade tip of the fan exceeds a certain value, excessive noise and shock resistance are generated), so that a boosting stage (a low-pressure compressor) coaxial with the fan and the rotating speed of a low-pressure turbine are slow, and more stages are needed to generate enough power. GTF engines incorporate a planetary gear assembly between the booster stage and the fan so that the fan, booster stage and low pressure turbine can be operated at relatively desired speeds simultaneously, thereby reducing the number of stages of booster stages and turbines and further improving the fuel economy of the turbofan engine.
However, in the GTF engine of the prior art, since the structure of the planetary gear set is complicated and the operating conditions are generally high-speed and high-load conditions, it is necessary to provide a reliable bearing structure and corresponding lubrication, cooling and control techniques. Therefore, the transmission system of the GTF engine has a complex structure, and further has the disadvantages of difficult assembly, inconvenient maintenance, and the like.
Accordingly, there is a need in the art for a transmission, turbofan engine, and method of assembly that addresses the problems of the prior art GTF engines.
Disclosure of Invention
It is an object of the present invention to provide a transmission mechanism.
It is an object of the present invention to provide a turbofan engine.
It is an object of the present invention to provide an assembly method.
A transmission mechanism according to an aspect of the present invention, for a turbofan engine, includes: the fan disc is provided with a first face gear on the axial downstream end face; the planetary gear assembly is positioned at the downstream of the fan disc and comprises an inner gear ring, a planet gear and a sun gear, and the axial upstream end surface of the inner gear ring is provided with a second end surface gear; wherein the first face gear meshes with a second face gear such that the fan disc is coupled with the planetary gear assembly.
In one or more embodiments of the transmission mechanism, the ring gear is a split structure and comprises a first ring gear and a second ring gear which are sequentially connected in the axial direction, and the first ring gear is provided with the second end face gear.
In one or more embodiments of the transmission mechanism, the first ring gear and the second ring gear have connecting holes extending in the axial direction, and the first ring gear and the second ring gear are connected in the axial direction through threaded connectors to form the ring gear.
In one or more embodiments of the transmission, the radially inner wall of the fan disc has a bearing seat for supporting an outer ring of a bearing.
A turbofan engine according to an aspect of the present invention includes: the fan comprises a fan disc and fan blades mounted on the fan disc; a pressurization stage; and a planetary gear assembly coupled to the fan and the booster stage, respectively; wherein the axial downstream end face of the fan disc has a first face gear; the planetary gear assembly is positioned at the downstream of the fan disc and comprises an inner gear ring, a planet gear and a sun gear, and the axial upstream end surface of the inner gear ring is provided with a second end surface gear; the first face gear meshes with a second face gear such that the fan disc is coupled with the planetary gear assembly.
In one or more embodiments of the turbofan engine, further comprising a bearing, a handling case, and a fan case, the handling case having a first bearing seat, a radially inner wall of the fan disk having a second bearing seat, an inner ring of the bearing supported by the first bearing seat, an outer ring of the bearing supported by the second bearing seat such that the fan is independently supported by the bearing to the handling case.
In one or more embodiments of the turbofan engine, the downstream mounting edge of the handling case is fixedly coupled to the upstream mounting edge of the fan case.
In one or more embodiments of the turbofan engine, the inner ring of the bearing is a split structure, and includes a first inner ring and a second inner ring that are sequentially connected in an axial direction; or the outer ring of the bearing is of a split structure and comprises a first outer ring and a second outer ring which are sequentially connected in the axial direction.
In one or more embodiments of the turbofan engine, the sun gear is formed separately or integrally with the fulcrum 1 and the fulcrum 2 of the low pressure rotor of the turbofan engine.
An assembly method according to one aspect of the invention for a geared turbofan engine, comprising: s1, assembling downstream components; s2, mounting a planetary gear assembly to the low-voltage rotor, wherein the planetary gear assembly and the downstream component form a first assembly body, and the upstream end of an inner gear ring of the planetary gear assembly is provided with a second end face gear; s3, connecting a processor box and a bearing with the fan to form a second assembly body, wherein the fan comprises a fan disc and fan blades, a first face gear is arranged at the downstream end of the fan disc, a second bearing seat is arranged on the radial inner wall of the fan disc, the processor box provides a first bearing seat, and the bearing is arranged between the first bearing seat and the second bearing seat; s4, assembling and connecting a first assembly body and a second assembly body, butt-jointing the first end face gear and the second end face gear, butt-jointing the downstream installation edge of the processing casing and the upstream installation edge of the fan casing, and enabling the second assembly body to be connected with the first assembly body.
The progressive effects of the scheme include but are not limited to:
1. on the premise that a fan, a booster stage and a low-pressure turbine can simultaneously work at a relatively ideal rotating speed by the traditional GTF engine, the fan disc and the inner gear ring are provided with end teeth for meshing, and the planetary gear assembly can directly drive the fan through the end teeth, so that the axial load of the planetary gear assembly is small or even close to zero, the working load of the planetary gear is reduced, and the reliability of the planetary gear assembly is improved; meanwhile, the reliability is improved, so that the structure of the corresponding planetary gear assembly, the bearing structure and the corresponding lubricating and cooling structure can be simplified, the assembly difficulty is reduced, and the maintenance is convenient; or the diameter of the inner gear ring can be further increased, the transmission ratio of the planetary gear assembly is improved, the stages of the gas compressor and the turbine are further reduced, the axial length of the engine is reduced, and the structure of the turbofan engine is compact;
2. the fan is independently supported on the treatment casing through the bearing by increasing the arrangement of the treatment casing, so that the support structure is simple and convenient to assemble and maintain;
3. the inner gear ring of the planetary gear assembly is of a split structure, and assembly is facilitated.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments in conjunction with the accompanying drawings, it being noted that the drawings are given by way of example only and are not drawn to scale, and should not be taken as limiting the scope of the invention which is actually claimed, wherein:
FIG. 1 is a schematic block diagram of a turbofan engine according to an embodiment.
Fig. 2A and 2B are schematic structural diagrams of a fan disc of a transmission mechanism according to an embodiment.
Fig. 3 is a schematic structural view of a first ring gear of a planetary gear assembly of the transmission according to an embodiment.
Fig. 4 is a schematic structural view of a second ring gear of the planetary gear assembly of the transmission according to an embodiment.
FIG. 5 is a flow diagram illustrating an assembly method according to one embodiment.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the disclosure, but these are by way of example only and are not limiting as to the scope of the invention.
In addition, it is to be understood that references to "one embodiment", "an embodiment", and/or "some embodiments", "one or more embodiments" mean that a particular feature, structure, or characteristic described in connection with at least one embodiment of the application is intended. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "some embodiments" or "one or more embodiments" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
As shown in fig. 1, the turbofan engine 100 includes a fan 1, a compressor including a boost stage 2 and a high-pressure compressor, a combustor including a low-pressure turbine 3 and a high-pressure turbine, and a stream of air entering the engine from the fan enters the core engine, enters the combustor after being boosted by the compressor, and is mixed with fuel ejected from a fuel nozzle and combusted in the combustor to form high-temperature and high-pressure combustion gas to drive the turbine to output power, and another stream of air enters an outer duct and is discharged through an outlet guide vane.
With continued reference to fig. 1, a planetary gear assembly 10 is provided between fan 1 and booster stage 2, i.e. planetary gear assembly 10 is located downstream of fan 1 and upstream of booster stage 2. The booster stage 2 is supported by a fulcrum assembly 21 consisting of a low-pressure rotor fulcrum 1 and a fulcrum 2. The planetary gear assembly 10 is a herringbone gear planetary gear, but not limited thereto, the planetary gear assembly 10 includes an inner gear ring 101, a planetary gear and a sun gear, wherein the sun gear is supported by the low-pressure rotor and can be integrally formed with the fulcrum assembly 21, so that the assembly work of the engine can be facilitated; it is understood that the sun gear may be independent of the fulcrum assembly 21. The number of the planet wheels is generally 3-5. The fan 1 includes a fan disk 11 and blades 12 mounted on the fan disk 11, and the blades 12 are mounted on the fan disk 11 through a tongue-and-groove 113 structure, or may be an integral structure, for example, the blades 12 are welded to the fan disk 11 by laser welding.
As shown in fig. 1, 2A, 2B and 3, in an embodiment, the fan disk 11 of the fan 1 is coupled with the ring gear 101 of the planetary gear assembly 10 to form a transmission mechanism. As shown in fig. 2A and 2B, an axially downstream end surface of the fan disk 11 has a first end face gear 111, and an axially upstream end surface of the ring gear 101 of the planetary gear assembly 10 has a second end face gear 102. It should be understood that the face gear described herein is defined similarly to its normal definition, i.e., the face gear is a gear that mates with a spur or helical gear at a 90 degree angle, the pinion and face gear of the type having perpendicular central axes, which may intersect or be offset from each other.
The fan disc 11 is coupled with the planetary gear assembly 10 by the engagement of the first face gear 111 with the second face gear 102, forming a transmission mechanism. The beneficial effects obtained in this way are that the fan, the booster stage and the low-pressure turbine can simultaneously work at a relatively ideal rotating speed by the traditional GTF engine realized by the planetary gear assembly 10, the fan disc 11 and the inner gear ring 101 are provided with the first face gear 111 and the second face gear 102 which are meshed, the planetary gear assembly 10 can directly drive the fan 1 through the end teeth, so that the axial load of the planetary gear assembly 10 is very small or even close to zero, the working load of the planetary gear is reduced, and the reliability of the planetary gear assembly is improved; meanwhile, the reliability is improved, so that the structure of the corresponding planetary gear assembly, the bearing structure and the corresponding lubricating and cooling structure can be simplified, the assembly difficulty is reduced, and the maintenance is convenient; or the diameter of the inner gear ring 101 of the planetary gear assembly 10 can be further increased, so that the transmission ratio of the planetary gear assembly 10 is improved, the number of stages of the compressor and the turbine is further reduced, the axial length of the turbofan engine is reduced, and the structure of the turbofan engine is compact.
Referring to fig. 3 and 4, in some embodiments, the specific structure of the ring gear 101 may be a split structure including a first ring gear 1011 and a second ring gear 1012 connected in sequence in the axial direction, where the first ring gear 1011 is located upstream, the second ring gear 1012 is located downstream, and the first ring gear 1012 has a second face gear 102 engaged with the first face gear 111 of the fan disc 11. The use of an annulus gear of split construction facilitates assembly of the planetary gear assembly 10 in a turbofan engine, the assembly process being described in detail in the assembly method described below.
Further, with continued reference to fig. 3 and 4, in some embodiments, the connection structure of the first ring gear 1011 and the second ring gear 1012 may be that the first ring gear 1011 and the second ring gear 1012 have connection holes 103 extending axially, the first ring gear 1011 and the second ring gear 1012 are connected axially by the threaded connection member 4 to form the ring gear 101, the threaded connection member 4 may be a bolt, and the connection holes 103 are bolt holes. Thus, the connecting structure for connecting the two is simple, the connecting operation is easy, and the component cost of the connecting structure is low.
Referring to fig. 1 and 2B, a bearing 5 for supporting the fan is supported by a bearing housing. The specific structure of the bearing seat may be that the turbofan engine 100 further includes a processing casing 6, the processing casing 6 provides a first bearing seat 61, as shown in fig. 1 and 2B, an upstream section of a radially inner wall of the fan disk 11 has a second bearing seat 112, an inner ring of the bearing 8 is supported by the first bearing seat 61, an outer ring of the bearing 8 is supported by the second bearing seat 112, so that the fan 1 is supported by the bearing 8 independently from the processing casing 6, and the bearing 8 may be a two-way angular contact ball bearing, a one-way thrust bearing, or the like, which is not listed here. It should be noted that here fan 1 is independently supported, which means independent of booster stage 2, as opposed to the conventional fan 1 being coaxially connected with booster stage 2, in this embodiment fan 1 is independently supported, independent of booster stage 2 supported by the low pressure spool, and the speed relationship of the two is adjusted by planetary gear assembly 10 respectively coupled to both. The beneficial effects are obtained in this way, as mentioned above, the fan and the pressurizing stage are in a split structure, the fan is independently supported on the treatment casing 6 through the bearing, and the supporting structure is simple and convenient to assemble and maintain. The mounting structure of the processor casing 6 can be that the downstream mounting edge of the processor casing 6 is butted in place with the upstream mounting edge of the fan casing 7, and the processor casing is fixedly connected with the fan casing through bolts. It should be understood that the term "processing case 6" is used broadly herein to include both a narrow sense of processing case, i.e., a case processed (casing), as is commonly understood in the art, i.e., a technical measure for extending the stable operating range and improving the performance of the compressor, i.e., a porous inner wall is formed, buckled, slotted or otherwise configured at a corresponding portion of the compressor case at the top of the rotor of one or more stages to suppress stall of the airflow at the tip region and to modify the flow loss, and an untreated conventional case. The casing includes a casing body 60, a support plate 62 and a first bearing seat 61, wherein the support plate 62 connects the casing body 60 and the first bearing seat 61 in a radial direction. The downstream mounting edge of the processing case housing 60 can be assembled in butt-joint with the upstream mounting edge of the fan case 7.
In some embodiments, the bearing 8 may also be a split structure, and specifically, the inner ring of the bearing may be a split structure, for example, a double-half inner ring angular contact ball bearing, which includes a first inner ring and a second inner ring that are connected in sequence in the axial direction, similar to the inner ring 101 of the split structure, where the first inner ring is located upstream and the second inner ring is located downstream. The fan assembling method has the advantages that the bearing can be guaranteed to have enough strength to support the fan, meanwhile, the assembling is convenient, and the specific assembling process is described in the following assembling method. It is understood that similarly, the outer ring of the bearing may be a split structure, including a first outer ring and a second outer ring connected in sequence in the axial direction, similar to the inner ring 101 of the split structure, the first outer ring being located upstream and the second outer ring being located downstream.
Referring to FIG. 5, a method of assembling a geared turbofan engine may include the steps of:
s1, assembling a downstream component 200;
for example, as shown in fig. 1, the downstream components include components downstream of the aforementioned transmission, including a fulcrum assembly 21, a booster stage 2, an outer bypass Outlet Guide Vane (OGV), a fan case 7, an intermediate case, a low pressure turbine main unit, a core main unit, and the like.
S2, mounting the planetary gear assembly 10 to a low-voltage rotor 201, wherein the planetary gear assembly 10 and the downstream component 200 form a first assembly body, and the upstream end of an inner gear ring 101 of the planetary gear assembly 10 is provided with a second end face gear 102;
and S3, connecting the processing casing 6 and the bearing 8 with the fan 1 to form a second assembly body. The fan 1 comprises a fan disc 11 and fan blades 12, wherein the downstream end of the fan disc 11 is provided with a first end face gear 111, the radial inner wall of the fan disc 11 is provided with a second bearing seat 112, the processor casing 6 provides a first bearing seat 61, and a bearing 8 is arranged between the first bearing seat 61 and the second bearing seat 62;
the specific steps can be to assemble the fan 1, the treatment casing 6 and the bearing 8 respectively; assembling the fan disc 11 and the blades 12 into the fan 1; assembling the hood 20, the processor casing 6 and the bearing 8, namely, the inner ring of the bearing 8 is supported on the first bearing seat 61 of the processor casing 6, when the inner ring of the bearing 8 is in a split structure, the first inner ring is firstly installed on the first bearing seat 61, then the assembly of the retainer, the rolling body and the bearing outer ring is installed on the first inner ring, and then the second inner ring is installed until the first bearing seat 61 is butted with the first inner ring; the fan disk 11 is then assembled to the bearing 8 by providing a second bearing seat 112 to form a second assembly, where the outer ring of the bearing 8 is supported by the second bearing seat 112 provided by the radially inner wall of the fan disk 11 and can be further fixed by the screw thread 110 provided by the upstream section of the radially inner wall of the fan disk 11.
It is understood that the sequence of assembling S2 of the first assembly and assembling S3 of the second assembly is not limited to the described sequence, and for example, S2 and S3 may be performed simultaneously.
S4, the first assembly body and the second assembly body are assembled and connected. As shown in fig. 1, the first face gear 111 on the axial downstream end face of the fan disk 11 is butted with the second face gear 102 on the axial upstream end face of the ring gear 101 of the planetary gear assembly 10, and the downstream mounting edge of the processing casing shell 60 of the processing casing 6 is butted with the upstream mounting edge of the fan casing 7, for example, at the connection position 9 shown in fig. 1, so that the second assembly body is assembled and connected with the first assembly body.
As can be understood from the above description, due to the second bearing seat 112 disposed on the radially inner wall upstream section of the fan disk 11, the structure that the first face gear 111 is disposed on the downstream end face of the fan disk 11 to provide support for the fan disk 11, and the butt joint of the first face gear 111 and the second face gear 102, the modular assembly, that is, the modular assembly of the first assembly body and the second assembly body, can be achieved, and the assembly process of the fan 1 in the turbofan engine is simplified.
In summary, the beneficial effects of the transmission mechanism, the turbofan engine and the assembling method described by the above embodiments include but are not limited to:
1. on the premise that a fan, a booster stage and a low-pressure turbine can simultaneously work at a relatively ideal rotating speed by the traditional GTF engine, the fan disc and the inner gear ring are provided with end teeth for meshing, and the planetary gear assembly can directly drive the fan through the end teeth, so that the axial load of the planetary gear assembly is small or even close to zero, the working load of the planetary gear is reduced, and the reliability of the planetary gear assembly is improved; meanwhile, the reliability is improved, so that the structure of the corresponding planetary gear assembly, the bearing structure and the corresponding lubricating and cooling structure can be simplified, the assembly difficulty is reduced, and the maintenance is convenient; or the diameter of the inner gear ring can be further increased, the transmission ratio of the planetary gear assembly is improved, the stages of the gas compressor and the turbine are further reduced, the axial length of the engine is reduced, and the structure of the turbofan engine is compact;
2. the fan is independently supported on the treatment casing through the bearing by increasing the arrangement of the treatment casing, so that the support structure is simple and convenient to assemble and maintain;
3. the inner gear ring of the planetary gear assembly is of a split structure, and assembly is facilitated.
Although the present invention has been disclosed in the above-mentioned embodiments, it is not intended to limit the present invention, and those skilled in the art may make variations and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (10)
1. A transmission mechanism for a turbofan engine, comprising:
the fan disc is provided with a first face gear on the axial downstream end face;
the planetary gear assembly is positioned at the downstream of the fan disc and comprises an inner gear ring, a planet gear and a sun gear, and the axial upstream end surface of the inner gear ring is provided with a second end surface gear;
wherein the first face gear meshes with a second face gear such that the fan disc is coupled with the planetary gear assembly.
2. The transmission mechanism according to claim 1, wherein the ring gear is a split structure and comprises a first ring gear and a second ring gear which are sequentially connected in the axial direction, and the first ring gear is provided with the second end face gear.
3. The transmission mechanism according to claim 2, wherein the first ring gear and the second ring gear have axially extending connection holes, and the first ring gear and the second ring gear are axially connected by a threaded connection member to constitute the ring gear.
4. The transmission of claim 1, wherein the radially inner wall of the fan disc has bearing seats for supporting the outer race of the bearing.
5. A turbofan engine, comprising:
the fan comprises a fan disc and fan blades mounted on the fan disc;
a pressurization stage; and
a planetary gear assembly coupled to the fan and the booster stage, respectively;
wherein the axial downstream end face of the fan disc is provided with a first face gear; the planetary gear assembly is positioned at the downstream of the fan disc and comprises an inner gear ring, a planet gear and a sun gear, and the axial upstream end surface of the inner gear ring is provided with a second end surface gear; the first face gear meshes with a second face gear such that the fan disc is coupled with the planetary gear assembly.
6. The turbofan engine of claim 5 further comprising a bearing, a processor case, and a fan case, the processor case having a first bearing seat, the radially inner wall of the fan disk having a second bearing seat, an inner ring of the bearing supported by the first bearing seat, and an outer ring of the bearing supported by the second bearing seat such that the fan is independently supported by the bearing to the processor case.
7. The turbofan engine of claim 6 wherein the downstream mounting edge of the handling case is fixedly coupled to the upstream mounting edge of the fan case.
8. The turbofan engine of claim 6 wherein the inner ring of the bearing is a split structure comprising a first inner ring and a second inner ring connected in series in an axial direction; or the outer ring of the bearing is of a split structure and comprises a first outer ring and a second outer ring which are sequentially connected in the axial direction.
9. The turbofan engine of claim 5 wherein the sun gear is separate from or integral with fulcrum 1, fulcrum 2 of a low pressure spool of the turbofan engine.
10. A method of assembly for a geared turbofan engine, comprising:
s1, assembling downstream components;
s2, mounting a planetary gear assembly to the low-voltage rotor, wherein the planetary gear assembly and the downstream component form a first assembly body, and the upstream end of an inner gear ring of the planetary gear assembly is provided with a second end face gear;
s3, connecting a processor box and a bearing with the fan to form a second assembly body, wherein the fan comprises a fan disc and fan blades, a first face gear is arranged at the downstream end of the fan disc, a second bearing seat is arranged on the radial inner wall of the fan disc, the processor box provides a first bearing seat, and the bearing is arranged between the first bearing seat and the second bearing seat;
s4, assembling and connecting a first assembly body and a second assembly body, and butting the downstream mounting edge of the processing casing with the upstream mounting edge of the fan casing by butting the first face gear with the second face gear so as to connect the second assembly body with the first assembly body.
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