CN106907242A - Aero-engine impeller - Google Patents
Aero-engine impeller Download PDFInfo
- Publication number
- CN106907242A CN106907242A CN201510971834.1A CN201510971834A CN106907242A CN 106907242 A CN106907242 A CN 106907242A CN 201510971834 A CN201510971834 A CN 201510971834A CN 106907242 A CN106907242 A CN 106907242A
- Authority
- CN
- China
- Prior art keywords
- aero
- shaft part
- driving shaft
- engine
- engine impeller
- 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.)
- Pending
Links
Classifications
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a kind of aero-engine impeller, it includes：The casing contained outside fan and fan, the fan is arranged in the casing contained outside the fan；Some outer culvert support plates, are provided between outer culvert support plate described in each two and contain stator outside multiple；Radial direction power transmission shaft, the radial direction power transmission shaft includes the first shaft portion and second driving shaft part, one end of first shaft portion is connected with each other with one end of the second driving shaft part, the other end of first shaft portion is connected to motor, and the other end of the second driving shaft part is connected to torque transmission unit.Aero-engine impeller of the present invention efficiently reduces aerodynamic loss by reducing the outer thickness for containing support plate, reduces the oil consumption rate of engine.
Description
Technical field
The present invention relates to aero-engine field, more particularly to a kind of aero-engine impeller.
Background technology
In aero-engine impeller field, the torsion of starting device during radial direction power transmission shaft on engine motor
Square passes to the radial direction power transmission shaft used described in the main shaft of engine.
Fig. 1 is the distribution schematic diagram of radial direction power transmission shaft in traditional aero-engine impeller.
As shown in figure 1, aero-engine main shaft 10 in the rotation for most starting is passed through by outside motor 11
What the moment of torsion that radial direction power transmission shaft 12 is provided was produced.Radial direction power transmission shaft 12 outside engine Middle casing by containing branch
Plate 13 and engine Middle casing intension support plate 14.Tapered gear 15 changes biography by angular wheel 16
The direction (axial direction) of torque delivery.
Outer culvert support plate 13 and outer culvert stator 17 are arranged on same row, outer to contain support plate 13 and outer culvert stator 17
All there are guide functions.Traditional radial direction power transmission shaft 12 is designed using same radius, but is helped and radially passed
The diameter of moving axis 12 is relatively thick (the huge moment of torsion of transmission) so that outer culvert support plate 13 need the very thick of design,
Thick thick outer culvert support plate 13 can bring huge aerodynamic loss, and face huge design difficulty.
The content of the invention
The technical problem to be solved in the present invention is to overcome culvert outside fan to be in the prior art radially driven shaft diameter
It is relatively thick, easily bring the defect of huge aerodynamic loss, there is provided a kind of aero-engine impeller.
The present invention is to solve above-mentioned technical problem by following technical proposals：A kind of aero-engine impeller,
Its feature is that the aero-engine impeller includes：
The casing contained outside fan and fan, the fan is arranged in the casing contained outside the fan；
Some outer culvert support plates, are provided between outer culvert support plate described in each two and contain stator outside multiple；
Radial direction power transmission shaft, the radial direction power transmission shaft includes the first shaft portion and second driving shaft part, institute
One end of one end and the second driving shaft part for stating the first shaft portion is connected with each other, and described first passes
The other end of shaft part is connected to motor, and the other end of the second driving shaft part is connected to moment of torsion transmission
Unit.
It is preferred that the torque transmission unit includes the first angular wheel and the second angular wheel, described first
Angular wheel and second angular wheel be mutually perpendicular to engagement, the other end of the second driving shaft part with
The first angular wheel connection.
It is preferred that first shaft portion and the second driving shaft part are respectively adopted different materials
It is made.
It is preferred that first shaft portion and the second driving shaft part use 40Cr, 35CrMo
And in 38CrMoAl any two kinds be made.
It is preferred that diameter of the diameter of first shaft portion less than the second driving shaft part.
It is preferred that being connected by covering tooth between first shaft portion and the second driving shaft part.
It is preferred that the outer a diameter of 7mm for containing support plate.
It is preferred that the motor is arranged on outside the casing contained outside the fan.
It is preferred that second angular wheel is arranged on engine spindle.
It is preferred that the aero-engine impeller also includes wheel hub and flow splitter, the wheel hub and flow splitter it
Between be provided with some intension stators and some stator blades, the intension stator and the stator blade are mutual
Every arrangement.
Positive effect of the invention is：
Aero-engine impeller of the present invention efficiently reduces aerodynamic loss by reducing the outer thickness for containing support plate,
Reduce the oil consumption rate of engine.
Brief description of the drawings
The above and other feature of the present invention, property and advantage will be by with reference to the accompanying drawings and examples
Description and become apparent, identical reference represents identical feature all the time in the accompanying drawings, wherein：
Fig. 1 is the distribution schematic diagram of radial direction power transmission shaft in traditional aero-engine impeller.
Fig. 2 is the distribution schematic diagram of radial direction power transmission shaft in aero-engine impeller of the present invention.
Fig. 3 is the circumferential plane figure that support plate and outer culvert stator are contained in aero-engine impeller China and foreign countries of the present invention.
Specific embodiment
It is that the above objects, features and advantages of the present invention can be become apparent, below in conjunction with accompanying drawing to this hair
Bright specific embodiment elaborates.
Many details are elaborated in the following description in order to fully understand the present invention, but it is of the invention
Can also be different from other manner described here using other to implement, therefore the present invention is not by described below
Specific embodiment limitation.
Fig. 2 is the distribution schematic diagram of radial direction power transmission shaft in aero-engine impeller of the present invention.Fig. 3 is the present invention
Contain the circumferential plane figure of support plate and outer culvert stator in aero-engine impeller China and foreign countries.
As shown in Figures 2 and 3, a kind of aero-engine impeller is disclosed in one embodiment of the present of invention,
It includes：Casing 21, some outer culvert support plate 27 and the radial direction power transmission shafts contained outside fan 20, fan.Wherein,
Fan 20 is arranged in the casing 21 contained outside fan.It is provided with outside multiple between culvert support plate 27 outside each two
Contain stator 28.The radial direction power transmission shaft includes the first shaft portion 22 and second driving shaft part 23, this
One end of one end and second driving shaft part 23 for locating the first shaft portion 22 is connected with each other, and first passes
The other end of shaft part 22 is connected to motor 26, and the other end of second driving shaft part 23 is connected to moment of torsion
Transfer unit.Here motor 26 is arranged on outside the casing 21 contained outside fan.
Preferably, the torque transmission unit includes the first angular wheel 24 and the second angular wheel 25, will
First angular wheel 24 and the second angular wheel 25 are mutually perpendicular to engagement, and second driving shaft part 23
The other end be connected with the first angular wheel 24.Second angular wheel 24 is arranged on engine spindle 30.
Especially, the first shaft portion 22 and second driving shaft part 23 are respectively adopted different materials herein
Material is made, and is made for example with any two kinds in 40Cr, 35CrMo and 38CrMoAl.First pass simultaneously
Diameter of the diameter of shaft part 22 less than second driving shaft part 23.
Further, connected by covering tooth between the first shaft portion 22 and second driving shaft part 23
Connect (not shown).It is outer to contain a diameter of 7mm of support plate 27, so as to reduce the pneumatic damage of outer culvert support plate 27
Lose, reduce the oil consumption rate of engine.
Additionally, also including wheel hub 40 and flow splitter 50 in aero-engine impeller of the present invention, flow splitter 50 is used
In air is arranged to inside and outside culvert respectively.Some intension stators 60 are provided between wheel hub 40 and flow splitter 50
With some stator blades 70, stator blade 70 is the third level stator blade of booster stage herein.Intension stator
60 and the spaced arrangement of stator blade 70.
In sum, aero-engine impeller of the present invention is by reducing the outer thickness for containing support plate, and by will
Radial direction power transmission shaft covers the structure of connection using two kinds of materials and by tooth, can efficiently reduce pneumatic damage
Lose, reduce the oil consumption rate of engine.
Although the foregoing describing specific embodiment of the invention, it will be appreciated by those of skill in the art that
These are merely illustrative of, and protection scope of the present invention is defined by the appended claims.This area
Technical staff can make many on the premise of without departing substantially from principle of the invention and essence to these implementation methods
Plant change or change, but these changes and modification each fall within protection scope of the present invention.
Claims (10)
1. a kind of aero-engine impeller, it is characterised in that the aero-engine impeller includes：
The casing contained outside fan and fan, the fan is arranged in the casing contained outside the fan；
Some outer culvert support plates, are provided between outer culvert support plate described in each two and contain stator outside multiple；
Radial direction power transmission shaft, the radial direction power transmission shaft includes the first shaft portion and second driving shaft part, institute
One end of one end and the second driving shaft part for stating the first shaft portion is connected with each other, and described first passes
The other end of shaft part is connected to motor, and the other end of the second driving shaft part is connected to moment of torsion transmission
Unit.
2. aero-engine impeller as claimed in claim 1, it is characterised in that the torque transmission unit
Including the first angular wheel and the second angular wheel, first angular wheel and the second angular wheel phase
Mutual Vertical Meshing, the other end of the second driving shaft part is connected with first angular wheel.
3. aero-engine impeller as claimed in claim 1, it is characterised in that first driveshaft section
Divide and the second driving shaft part is respectively adopted different materials and is made.
4. aero-engine impeller as claimed in claim 3, it is characterised in that first driveshaft section
It is divided to and the second driving shaft part is made of any two kinds in 40Cr, 35CrMo and 38CrMoAl.
5. aero-engine impeller as claimed in claim 3, it is characterised in that first driveshaft section
Diameter of the diameter for dividing less than the second driving shaft part.
6. aero-engine impeller as claimed in claim 5, it is characterised in that first driveshaft section
Divide and connected by covering tooth and the second driving shaft part between.
7. aero-engine impeller as claimed in claim 1, it is characterised in that described outer to contain the straight of support plate
Footpath is 7mm.
8. aero-engine impeller as claimed in claim 1, it is characterised in that the motor is arranged on institute
State outside the casing contained outside fan.
9. aero-engine impeller as claimed in claim 2, it is characterised in that second angular wheel
It is arranged on engine spindle.
10. aero-engine impeller as claimed in claim 1, it is characterised in that the aero-engine
Impeller also includes wheel hub and flow splitter, and some intension stators and some are provided between the wheel hub and flow splitter
Stator blade, the intension stator and the spaced arrangement of the stator blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510971834.1A CN106907242A (en) | 2015-12-22 | 2015-12-22 | Aero-engine impeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510971834.1A CN106907242A (en) | 2015-12-22 | 2015-12-22 | Aero-engine impeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106907242A true CN106907242A (en) | 2017-06-30 |
Family
ID=59199489
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510971834.1A Pending CN106907242A (en) | 2015-12-22 | 2015-12-22 | Aero-engine impeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106907242A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1904325A (en) * | 2005-07-29 | 2007-01-31 | 通用电气公司 | PTO device for a gas turbine engine |
| CN101153559A (en) * | 2006-09-27 | 2008-04-02 | 通用电气公司 | Gas turbine engine assembly and method of assembling same |
| CN101280726A (en) * | 2007-04-03 | 2008-10-08 | 通用电气公司 | Power output system and gas turbine assembly including same |
| GB201122076D0 (en) * | 2011-12-22 | 2012-02-01 | Rolls Royce Plc | Aeroengine arrangement |
-
2015
- 2015-12-22 CN CN201510971834.1A patent/CN106907242A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1904325A (en) * | 2005-07-29 | 2007-01-31 | 通用电气公司 | PTO device for a gas turbine engine |
| CN101153559A (en) * | 2006-09-27 | 2008-04-02 | 通用电气公司 | Gas turbine engine assembly and method of assembling same |
| CN101280726A (en) * | 2007-04-03 | 2008-10-08 | 通用电气公司 | Power output system and gas turbine assembly including same |
| GB201122076D0 (en) * | 2011-12-22 | 2012-02-01 | Rolls Royce Plc | Aeroengine arrangement |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Applicant after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Applicant before: AVIC Commercial Aircraft Engine Co.,Ltd. |
|
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170630 |