CN205714304U - A kind of electromotor low pressure rotor supporting structure - Google Patents
A kind of electromotor low pressure rotor supporting structure Download PDFInfo
- Publication number
- CN205714304U CN205714304U CN201620336516.8U CN201620336516U CN205714304U CN 205714304 U CN205714304 U CN 205714304U CN 201620336516 U CN201620336516 U CN 201620336516U CN 205714304 U CN205714304 U CN 205714304U
- Authority
- CN
- China
- Prior art keywords
- bearing
- low pressure
- electromotor
- clutch shaft
- flat segments
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model discloses a kind of electromotor low pressure rotor supporting structure, belong to aero-engine field, it is characterized in that, clutch shaft bearing and the second bearing it is provided with on low-pressure shaft between fan propeller and Low Pressure Turbine Rotor, second outer race and the integrated rigid design of bearing block, it is used for bearing axial force, between first and third outer race and bearing block, oil clearance is set.Clutch shaft bearing internal ring is the integrated design with settling down ring, utilizes lubricating oil pressure to provide clutch shaft bearing axial pre tightening force.This utility model is by being designed to thin wall flexible structure by clutch shaft bearing seat; fuse according to predetermined manner when engine blower blade is produced very large unbalance amount by foreign object strike fracture; reduce the unbalanced load being delivered to main load-bearing part the second bearing; it is designed to effectively absorb the articulated structure of deformation at the second bearing block simultaneously; produce local buckling stress in the second position of bearings after avoiding fusing to occur to concentrate, protection engine health work.
Description
Technical field
This utility model relates to aero-engine field, relates to a kind of electromotor low pressure rotor supporting structure, is particularly suited for aero-engine low pressure rotor support structure design.
Background technology
At present, the most military or civilian fanjet all uses many rotor structures, fan propeller and turbine rotor and couple the zero of these rotors, assembly constitutes the low pressure rotor of electromotor.Low pressure rotor axle to pass from high pressure rotor center, it is bearing on engine crankcase by supporting structure, various loads (such as axial gas forces, gravity, inertia force and moment of inertia etc.) suffered on rotor are all born by supporting structure and pass on engine crankcase, are finally installed joint by casing by electromotor and pass on aircraft component.
Traditional low pressure rotor three fulcrum structure typically uses flexible clutch and intershaft bearing, flexible clutch makes compressor rotor and turbine rotor nonconcentricity strengthen, when especially crossing critical speed, amount of deflection and vibration are big, thus cause the radial clearance of blade to change, have impact on economy and the safe operation of electromotor, assembling and balance to electromotor are also made troubles；Using intershaft bearing, the vibration of low pressure rotor and deformation can affect the work of high pressure rotor, and intershaft bearing easily skids, and the design of lubricating oil peripheral passage is relatively difficult, and cooling effect is the most poor.Additionally; owing to engine blower blade is big and thin; and high speed rotating, when engine blower blade is caused huge unbalanced load by foreign object strike damage or fracture, for ensureing that aircraft occurs without catastrophic failure; as electromotor come off, disconnected leaf punctures cabin etc.; ensure that electromotor is installed joint and occurred without fault, it is necessary to carry out actively fusing design to some parts of supporting structure, when making electromotor run into major crisis simultaneously; according to default mode failures even, to protect the safety of main body.Therefore, need a kind of low pressure rotor supporting structure of design badly, not only to ensure reliably to bear the load of rotor, the simple in construction of electromotor, mounting or dismounting and dynamic balancing also should be made convenient.
Utility model content
Disadvantages mentioned above and deficiency for prior art, the utility model proposes a kind of electromotor low pressure rotor supporting structure, by to bearing type, position of the fulcrum, bearing block, the appropriate design of oil clearance, make engine structure simple, mounting or dismounting and dynamic balancing are convenient, simultaneously when engine blower blade is produced the biggest unbalanced load by foreign object strike damage or fracture, it is possible to make electromotor fuse according to predetermined manner, it is ensured that engine main body the most safely and effectively works.
This utility model solves above-mentioned technical problem and be the technical scheme is that
A kind of electromotor low pressure rotor supporting structure, including low-pressure shaft and be arranged on the fan propeller on described low-pressure shaft and Low Pressure Turbine Rotor, it is characterised in that
Described fan propeller is positioned close to the position of described low-pressure shaft front end, and described Low Pressure Turbine Rotor is positioned close to the position of described low-pressure shaft rear end,
Clutch shaft bearing and the second bearing it is provided with on low-pressure shaft between described fan propeller and Low Pressure Turbine Rotor, distance collar is set between described clutch shaft bearing and the second bearing, described clutch shaft bearing and the internal ring of the second bearing and the equal tightness of described distance collar coordinate on described low-pressure shaft, and the internal ring of described clutch shaft bearing is one-body molded with distance collar, outer shroud and second bearing block of described second bearing are one-body molded, clutch shaft bearing seat and the second bearing block are all fixedly connected on by securing member on the same axial location of electromotor primary load bearing casing, wherein
It is provided with bearing backboard in described clutch shaft bearing seat, described bearing backboard be positioned at the outer shroud of described clutch shaft bearing in the face of the side of described Low Pressure Turbine Rotor, space between described clutch shaft bearing seat inwall and bearing backboard forms a lubrication lubricating cavity, under engine behavior, described bearing backboard produces axial pre tightening force to the outer shroud of described clutch shaft bearing under lubricating oil pressure effect in described lubricating cavity.
Preferably, described clutch shaft bearing seat is a thin wall flexible structure, including the internal ring flat segments parallel with engine center axis and outer flat segments, conical section is set between described internal ring flat segments and outer shroud flat segments, described internal ring flat segments is sheathed on outside described clutch shaft bearing and bearing backboard, the end of described outer shroud flat segments is fixedly connected on the primary load bearing casing of electromotor by securing member, and described tapering transition section one end is connected with described internal ring flat segments, and the other end is connected with described outer shroud flat segments.
Preferably, described tapering transition section becomes 18 °～22 ° of angles with internal ring flat segments.
Preferably, described second bearing block includes outer shroud flat segments, radial section, conical section and outer race, described outer shroud flat segments staggers the most round about with outer race, described outer shroud flat segments is fixedly connected on the primary load bearing casing of electromotor by securing member, described radial section is basically perpendicular to described engine axis, the described junction between outer shroud flat segments and radial section is positioned at outer shroud flat segments centrage in the face of the side of described fan propeller, junction between described radial section and conical section is located remotely from the higher radius of outer race, and a circular arc articulated structure is formed in this junction, conical section is in an acute angle with engine axis and is connected with outer race.
Preferably, the thickness of described second bearing block is 2.6～3mm, is connected on electromotor primary load bearing casing by the most uniform screw.
Preferably, the described junction chamfering radius between outer shroud flat segments and radial section is 2.5～4mm, and the junction chamfering radius between described conical section and outer race is 20～25mm.
Preferably, the chamfering radius of described circular arc articulated structure is 6～8mm.
Preferably, the angle between described conical section and engine axis is 18 °～25 °.
Preferably, described low-pressure shaft uses the support pattern of 0-2-1, is provided with the 3rd bearing after described Low Pressure Turbine Rotor, and described 3rd bearing is coordinated on the rear end of described low-pressure shaft by its internal ring tightness.
Preferably, 0.23～0.25mm oil clearance is set between outer shroud and the clutch shaft bearing seat of described clutch shaft bearing, between described 3rd bearing and the 3rd bearing block, 0.13～0.15mm oil clearance is set.
Electromotor low pressure rotor supporting structure of the present utility model, is particularly suited for High Performance Aeroengine low pressure rotor support structure design.
Compare with existing supporting structure, electromotor low pressure rotor supporting structure of the present utility model has the advantage that the most each point supporting is at an axle, clutch shaft bearing internal ring is integrated structure design with distance collar, the second ball bearing outer shroud with bearing block, make simple in construction, lightweight, mounting or dismounting and dynamic balancing are convenient, and load path is short；In electromotor low pressure rotor supporting structure the most of the present utility model, mainly being born axial force by the second bearing, clutch shaft bearing is ingenious utilizes its lubrication lubricating oil pressure to provide axial pre tightening force to prevent light load slipping；3. clutch shaft bearing seat is designed to thin wall flexible structure, second bearing block is designed to rigidity articulated structure, the bearing block of clutch shaft bearing and supporting thereof is designed to weak link relative to the bearing block of the second bearing and supporting thereof, when engine blower blade is produced the biggest amount of unbalance by foreign object strike damage or fracture, first clutch shaft bearing seat ruptures or destroys, thus change the bang path of low pressure rotor out-of-balance force, reduce the out-of-balance force being delivered to adjacent critical component from fan, the critical component such as Middle casing and installation joint is avoided to destroy because bearing excessive unbalanced load, second bearing hinge connection structure can effectively absorb deformation simultaneously, the partial loop variation and the stress that reduce and produce at release the second bearing are concentrated, ensure that engine main body safely and effectively works；4. after clutch shaft bearing lost efficacy, low-pressure shaft increases at the support stiffness of front fulcrum, by the optimization of the second bearing block rigidity is designed, the low order critical speed of low-pressure shaft can be adjusted, it is ensured that electromotor can safety with windmill rotation speed operation until engine cut-off, aircraft landing；5. in order to control rotor oscillation during electromotor work, between electromotor the first, the 3rd outer race and bearing block, leave gap, in gap, be full of the chargeoil of lubrication, form squeeze film, when making electromotor cross critical speed very steadily, vibration the least.
Accompanying drawing explanation
Other features of the present utility model and advantage will be more fully understood that by the detailed description of the invention described in detail below in conjunction with accompanying drawing, and in accompanying drawing, identical reference identifies same or analogous parts, wherein:
Fig. 1 is typical case's fanjet low pressure rotor three point supporting structural representation of the present utility model.
Fig. 2 is enlarged diagram at first, second bearing of the present utility model.
Detailed description of the invention
Being described in further detail this utility model below in conjunction with embodiment, following example are that this utility model is not limited to following example to explanation of the present utility model.
Fig. 1,2 it is a kind of typical case's fanjet situation when using electromotor low pressure rotor supporting structure of the present utility model and use three point supportings (0-2-1), the fan propeller 5 including low-pressure shaft 4 and being arranged on low-pressure shaft and Low Pressure Turbine Rotor 6, fan propeller 5 is positioned close to the position of low-pressure shaft 4 front end, and Low Pressure Turbine Rotor 6 is positioned close to the position of low-pressure shaft 4 rear end.Low-pressure shaft 4 is connected transmission moment of torsion respectively by spline 29 with fan propeller 5 and Low Pressure Turbine Rotor 6, and two faces of cylinder at spline two ends reach, with the cooperation of little tightness, requirement of feeling relieved.First ball bearing, the second ball bearing are positioned at after fan propeller 5 before Low Pressure Turbine Rotor 6, coordinated by internal ring tightness and be fixed on low-pressure shaft front end together with fan propeller 5 with front clamp nut 7, after third leg bearing is positioned at Low Pressure Turbine Rotor 6, is coordinated by internal ring tightness and be fixed on low-pressure shaft rear end together with Low Pressure Turbine Rotor 6 with rear clamp nut 8.
Distance collar 10 between clutch shaft bearing internal ring 9 and first and second bearing is designed as one, and the second outer race 11 and the second bearing block 12 are designed as one so that simple in construction, cumulative errors are little, and load path is short.Second bearing block 12 thickness is 2.6～3mm rigid design, is connected on electromotor rigidity preferable primary load bearing casing 14 by the most uniform screw 13, is primarily subjected to axial force；Clutch shaft bearing backboard 15 and clutch shaft bearing seat 16 are sealed by O-shaped rubber ring 17 and define lubrication lubricating cavity 18, lubricating oil pressure produces the active force of 40 kilograms forward under engine behavior to clutch shaft bearing backboard 15, and then act on clutch shaft bearing outer shroud 19, clutch shaft bearing axial pre tightening force is provided, prevents clutch shaft bearing light load slipping.
Clutch shaft bearing seat 16 is designed as the thin wall flexible structure of thickness 1.3～1.5mm, by the internal ring flat segments 20 parallel with engine center axis, outer shroud flat segments 21, the conical section 22 becoming 18 °～22 ° with flat segments forms, the oil clearance of 0.23～0.25mm is set between clutch shaft bearing outer shroud 19 and bearing block 20, the oil clearance of 0.13～0.15mm is set between the 3rd outer race 27 and bearing block 28, vibration during fan propeller 5 critical speed excessively can be reduced, prevent fan blade tip scraped finish；Second bearing block 12 devises the orthodrome articulated structure 26 being made up of the conical section 24 and radial section 25 becoming 18 °～25 ° with engine axis, this articulated structure 26 radially should be located remotely from the higher radius of outer race 11, it is axially located the left side of the second bearing block outer shroud flat segments center line 30, the design of this structure can be when engine blower blade be produced the biggest amount of unbalance by foreign object strike damage or fracture, effectively absorb deformation, it is ensured that electromotor the most safely and effectively works.
Furthermore, it is necessary to illustrate, the specific embodiment described in this specification, the shape of its parts and components, be named title etc. can be different.All equivalences done according to structure, feature and principle described in this utility model inventional idea or simple change, be all included in the protection domain of this utility model patent.Described specific embodiment can be made various amendment or supplements or use similar mode to substitute by this utility model person of ordinary skill in the field; without departing from structure of the present utility model or surmount scope defined in the claims, protection domain of the present utility model all should be belonged to.
Claims (10)
1. an electromotor low pressure rotor supporting structure, including low-pressure shaft and be arranged on the fan propeller on described low-pressure shaft and Low Pressure Turbine Rotor, it is characterised in that
Described fan propeller is positioned close to the position of described low-pressure shaft front end, and described Low Pressure Turbine Rotor is positioned close to the position of described low-pressure shaft rear end,
Clutch shaft bearing and the second bearing it is provided with on low-pressure shaft between described fan propeller and Low Pressure Turbine Rotor, distance collar is set between described clutch shaft bearing and the second bearing, described clutch shaft bearing and the internal ring of the second bearing and the equal tightness of described distance collar coordinate on described low-pressure shaft, and the internal ring of described clutch shaft bearing is one-body molded with distance collar, outer shroud and second bearing block of described second bearing are one-body molded, clutch shaft bearing seat and the second bearing block are all fixedly connected on by securing member on the same axial location of electromotor primary load bearing casing, wherein
It is provided with bearing backboard in described clutch shaft bearing seat, described bearing backboard be positioned at the outer shroud of described clutch shaft bearing in the face of the side of described Low Pressure Turbine Rotor, space between described clutch shaft bearing seat inwall and bearing backboard forms a lubrication lubricating cavity, under engine behavior, described bearing backboard produces axial pre tightening force to the outer shroud of described clutch shaft bearing under lubricating oil pressure effect in described lubricating cavity.
Electromotor low pressure rotor supporting structure the most according to claim 1, it is characterized in that, described clutch shaft bearing seat is a thin wall flexible structure, including the internal ring flat segments parallel with engine center axis and outer flat segments, conical section is set between described internal ring flat segments and outer shroud flat segments, described internal ring flat segments is sheathed on outside described clutch shaft bearing and bearing backboard, the end of described outer shroud flat segments is fixedly connected on the primary load bearing casing of electromotor by securing member, described tapering transition section one end is connected with described internal ring flat segments, the other end is connected with described outer shroud flat segments.
Electromotor low pressure rotor supporting structure the most according to claim 2, it is characterised in that described tapering transition section becomes 18 °～22 ° of angles with internal ring flat segments.
Electromotor low pressure rotor supporting structure the most according to claim 2, it is characterized in that, described second bearing block includes outer shroud flat segments, radial section, conical section and outer race, described outer shroud flat segments staggers the most round about with outer race, described outer shroud flat segments is fixedly connected on the primary load bearing casing of electromotor by securing member, described radial section is basically perpendicular to described engine axis, the described junction between outer shroud flat segments and radial section is positioned at outer shroud flat segments centrage in the face of the side of described fan propeller, junction between described radial section and conical section is located remotely from the higher radius of outer race, and a circular arc articulated structure is formed in this junction, conical section is in an acute angle with engine axis and is connected with outer race.
Electromotor low pressure rotor supporting structure the most according to claim 4, it is characterised in that the thickness of described second bearing block is 2.6～3mm, is connected on electromotor primary load bearing casing by the most uniform screw.
Electromotor low pressure rotor supporting structure the most according to claim 4, it is characterized in that, the described junction chamfering radius between outer shroud flat segments and radial section is 2.5～4mm, and the junction chamfering radius between described conical section and outer race is 20～25mm.
Electromotor low pressure rotor supporting structure the most according to claim 4, it is characterised in that the chamfering radius of described circular arc articulated structure is 6～8mm.
Electromotor low pressure rotor supporting structure the most according to claim 4, it is characterised in that the angle between described conical section and engine axis is 18 °～25 °.
Electromotor low pressure rotor supporting structure the most according to claim 1, it is characterized in that, described low-pressure shaft uses the support pattern of 0-2-1, is provided with the 3rd bearing after described Low Pressure Turbine Rotor, and described 3rd bearing is coordinated on the rear end of described low-pressure shaft by its internal ring tightness.
Electromotor low pressure rotor supporting structure the most according to claim 9, it is characterized in that, 0.23～0.25mm oil clearance is set between outer shroud and the clutch shaft bearing seat of described clutch shaft bearing, between described 3rd bearing and the 3rd bearing block, 0.13～0.15mm oil clearance is set.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620336516.8U CN205714304U (en) | 2016-04-20 | 2016-04-20 | A kind of electromotor low pressure rotor supporting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620336516.8U CN205714304U (en) | 2016-04-20 | 2016-04-20 | A kind of electromotor low pressure rotor supporting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205714304U true CN205714304U (en) | 2016-11-23 |
Family
ID=57298292
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620336516.8U Expired - Fee Related CN205714304U (en) | 2016-04-20 | 2016-04-20 | A kind of electromotor low pressure rotor supporting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205714304U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109281944A (en) * | 2018-10-19 | 2019-01-29 | 中国科学院工程热物理研究所 | The axial force pre-load arrangement of deep groove ball bearing in a kind of engine rotor fulcrum |
| CN111188686A (en) * | 2020-01-19 | 2020-05-22 | 中国科学院工程热物理研究所 | Double-ball bearing supporting structure for preventing light load from slipping |
| CN113123881A (en) * | 2019-12-31 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Support structure of engine |
| CN114215614A (en) * | 2021-12-17 | 2022-03-22 | 中国航发沈阳发动机研究所 | Engine rotor fulcrum supporting structure |
-
2016
- 2016-04-20 CN CN201620336516.8U patent/CN205714304U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109281944A (en) * | 2018-10-19 | 2019-01-29 | 中国科学院工程热物理研究所 | The axial force pre-load arrangement of deep groove ball bearing in a kind of engine rotor fulcrum |
| CN113123881A (en) * | 2019-12-31 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Support structure of engine |
| CN113123881B (en) * | 2019-12-31 | 2022-05-31 | 中国航发商用航空发动机有限责任公司 | Support structure of engine |
| CN111188686A (en) * | 2020-01-19 | 2020-05-22 | 中国科学院工程热物理研究所 | Double-ball bearing supporting structure for preventing light load from slipping |
| CN111188686B (en) * | 2020-01-19 | 2021-03-30 | 中国科学院工程热物理研究所 | Double-ball bearing supporting structure for preventing light load from slipping |
| CN114215614A (en) * | 2021-12-17 | 2022-03-22 | 中国航发沈阳发动机研究所 | Engine rotor fulcrum supporting structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105822366A (en) | Low-pressure rotor supporting structure of engine with fusing design | |
| CN205714304U (en) | A kind of electromotor low pressure rotor supporting structure | |
| CA2870683C (en) | Apparatus and method for assembling a damper bearing assembly | |
| EP3438420B1 (en) | Aero-engine and fusing method thereof under fan blade out load | |
| US10598016B2 (en) | Combination of two interconnected shafts for high-speed rotors | |
| US6098399A (en) | Ducted fan gas turbine engine | |
| EP1900910B1 (en) | Thrust bearing housing for a gas turbine engine | |
| US6079200A (en) | Ducted fan gas turbine engine with fan shaft frangible connection | |
| KR20060046685A (en) | Bearing support | |
| CN206477916U (en) | The Aero-engine Bearing support cone wall of fusible | |
| EP2771549A1 (en) | Gas turbine engine support strut assembly | |
| CN107780984A (en) | Can be failed rotor support structure and aero-engine | |
| US11261753B2 (en) | Method and device for connecting fan rotor to low pressure turbine rotor | |
| US8807918B2 (en) | Rotating catcher for impeller containment | |
| CN108071429A (en) | Can fail rotor support structure and aero-engine | |
| US20120275921A1 (en) | Turbine engine and load reduction device thereof | |
| CN111894737B (en) | Rotor support structure and gas turbine | |
| CN110206646B (en) | Aeroengine bearing support subassembly and aeroengine | |
| CN206256937U (en) | Bearing support structure and aero-engine | |
| CN209942947U (en) | Fan rotor support system and bearing support device that can lose efficacy of aeroengine | |
| CN209781044U (en) | Fan rotor support system | |
| CN110005479B (en) | Aeroengine and fusing load reduction structure for supporting low-voltage rotor bearing thereof | |
| US11022099B2 (en) | Ram air turbine shaft whirl damper | |
| CN110320044B (en) | Active load reduction device after sudden loading of aircraft engine tester | |
| EP1479874A2 (en) | Gas turbine stubshaft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161123 Termination date: 20210420 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |