CN209398455U - A kind of aero-engine and its blade - Google Patents
A kind of aero-engine and its blade Download PDFInfo
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- CN209398455U CN209398455U CN201822030160.7U CN201822030160U CN209398455U CN 209398455 U CN209398455 U CN 209398455U CN 201822030160 U CN201822030160 U CN 201822030160U CN 209398455 U CN209398455 U CN 209398455U
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Abstract
The purpose of this utility model is to provide a kind of blades, and the difference of actual conditions and design shape under each state is in range of tolerable variance.The another object of the utility model provides a kind of aero-engine one comprising above-mentioned blade.For the blade of aviation engine for realizing foregoing purpose, with blade inlet edge, trailing edge, blade tip, blade root and aerofoil, the aerofoil between the blade inlet edge and trailing edge it is tangential, with the tangential vertical exhibition Xiang Yanshen, and connect the blade tip and the blade root, it is characterized by: the aerofoil is made of magnetically susceptible material, the rigidity of the magnetically susceptible material changes with the size variation of externally-applied magnetic field.
Description
Technical field
The utility model relates to aero-engine more particularly to a kind of blades of aero-engine.
Background technique
For having compressor rotor blade, compressor stator blade, turbine rotor leaf in the aero-engine of aircraft
Piece, turbine stator vane etc..In-engine rotation axis rotation drives above-mentioned rotor blade to circumferentially rotate, and air is pushed to flow backward
It is dynamic, and by stator blade closely, so that air be made to be compressed.Compressed air mixes combustion with fuel oil in a combustion chamber
After burning, turbine rotor blade rotation is pushed, and by being discharged after stator blade closely from engine rear end.In above-mentioned work
In the process, rotor blade will receive the effect of the load such as centrifugal force, thrust gas and temperature, and stator blade will receive gas and push away
The effect of the load such as power and temperature.The blade of engine deforms under the influence of these loads, so as to cause work shape
The shape under blade shape and installation condition under state is inconsistent, when this species diversity is sufficiently large, will produce to the performance of engine
Raw very important influence.
In view of the above-mentioned problems, being selection working time longest state (such as cruising condition) in available engine, to blade
Shape carry out retrospectively calculate, obtain the blade profile under a kind of installation condition, it is ensured that the blade profile becomes under the effect of cruising condition load
The shape reached after shape is consistent with the design blade profile of cruising condition.It is above-mentioned that installation condition is calculated from design point blade shape
The conversion of the process of blade shape, commonly referred to as cold and hot.
However inventors have found that the cold conditions blade profile being converted to by cold and hot, can only guarantee in some working condition
Under, the true form of blade is consistent with design shape.And in other conditions, the true form and design shape of blade then can not
Guarantee consistent.
Utility model content
The purpose of this utility model is to provide a kind of blades, the actual conditions and design shape under each state
Difference is in range of tolerable variance.
The another object of the utility model provides a kind of aero-engine one comprising above-mentioned blade.
For the blade of aviation engine for realizing foregoing purpose, there is blade inlet edge, trailing edge, blade tip, blade root and sky
Aerodynamic force face, the aerofoil between the blade inlet edge and trailing edge it is tangential, with the tangential vertical exhibition
To extension, and connect the blade tip and the blade root, it is characterised in that:
The aerofoil is made of magnetically susceptible material, and the rigidity of the magnetically susceptible material is with externally-applied magnetic field
Size variation and change.
In one or more embodiments, the magnetically susceptible material is magnetic rheology elastic body, the magnetorheological elasticity
Body is made of high molecular polymer and the magnetic-particle being dispersed in the high molecular polymer；
Wherein, the rigidity of the magnetic rheology elastic body and the aerofoil externally-applied magnetic field size are positively correlated.
In one or more embodiments, the high molecular polymer is titanium alloy substrate material, the magnetic-particle
For hydroxy iron powder.
In one or more embodiments, the diameter of the hydroxy iron powder is 5 to 10 microns.
To realize aforementioned another object aero-engine, including engine crankcase, rotating disc and setting in the casing
Interior rotor blade and stator blade, the rotor blade are rotated by rotation axis of the rotating disc central axis, feature
It is, the rotor blade and stator blade are respectively foregoing blade；
Wherein, the aero-engine further includes electromagnetic induction device, the electromagnetic induction device for apply magnetic field in
The aerofoil.
In one or more embodiments, the electromagnetic induction device is separately positioned on the outside of the blade tip and/or institute
It states on the inside of blade root.
In one or more embodiments, the blade is rotor blade, is the casing on the outside of the blade tip, described
It is the rotating disc on the inside of blade root.
In one or more embodiments, the blade is stator blade, is the casing on the outside of the blade tip, described
It is blade inner ring on the inside of blade root.
In one or more embodiments, the electromagnetic induction device includes:
Iron core；
Electromagnetic coil is arranged around the iron core；
Coil baffle, the electromagnetic coil are limited between the coil baffle and the iron core；
Outer housing accommodates the iron core, the electromagnetic coil and the coil baffle, is made of permeability magnetic material；And
Field current controller, Xiang Suoshu electromagnetic coil export electric current；
Wherein, also there is speed detector, the speed detector detects the blade in the aero-engine
Revolving speed, and output signal, the field current controller controls the output size of current according to the signal.
In one or more embodiments, the revolving speed of the output size of current and the rotating disc is positively correlated.
The utility model has the beneficial effects that:
Blade of aviation engine is made of a kind of magnetically susceptible material, and the rigidity of the magnetically susceptible material can be in material
Outside apply magnetic field size variation and change.To when engine it is in running order in, blade of aviation engine by
Extraneous load act on when, by change blade rigidity, enable to blade when the engine is working, by changing the rigid of itself
Property keeps the shape of blade all being consistent property under each working condition of engine, to reduce the mill to engine
Damage.
Detailed description of the invention
The above and other feature, property and advantage of the utility model will be by with reference to the accompanying drawings and examples
Description and become readily apparent from, in which:
Fig. 1 shows the front schematic view of one embodiment of blade of aviation engine；
Fig. 2 shows the diagrammatic cross-sections of blade of aviation engine；
Fig. 3 shows the diagrammatic cross-section of one embodiment of aero-engine；
Fig. 4 shows the schematic diagram of blade and electromagnetic induction device distribution in Fig. 3；
Fig. 5 shows the magnetic induction line distribution schematic diagram of blade of aviation engine externally-applied magnetic field；
Fig. 6 shows the diagrammatic cross-section of another embodiment of aero-engine；
Fig. 7 shows the schematic diagram of blade and electromagnetic induction device distribution in Fig. 6；
Fig. 8 shows the diagrammatic cross-section of another embodiment of aero-engine；
Fig. 9 shows the schematic diagram of blade and electromagnetic induction device distribution in Fig. 8；
Figure 10 shows the schematic diagram of one embodiment of electromagnetic induction device.
Specific embodiment
It is following to disclose the embodiment or embodiment of subject technology scheme described in a variety of different implementations.For simplification
The specific example of each element and arrangement is described below in disclosure, and certainly, these are only example, is not to this
The protection scope of invention is limited.Such as the fisrt feature then recorded in the description above second feature or above
It is formed, may include the embodiment that the first and second features are formed by way of directly contacting, also be included in the first He
The embodiment that supplementary features are formed between second feature, to can not directly be contacted between the first and second features.In addition,
In these disclosures may in different examples repeat reference numerals and/or letter.The repetition is in order to brief and clear
Chu itself does not indicate each embodiment being discussed and/or interstructural relationship.Further, when first element be with
The mode that second element is connected or combines describes, which includes the reality that the first and second elements are connected directly or are bonded to each other
Mode is applied, also includes so that the first and second interelements ground connection is connected or is tied each other using one or more other intervening elements additions
It closes.
It should be noted that use in the case where, it is described below in up, down, left, right, before and after, top, bottom, just,
Instead, clockwise and anticlockwise merely for the sake of used in convenient purpose, and any specific fixed-direction is not implied that.Thing
In reality, they be used to reflect relative position and/or direction between the various pieces of object.
Aero-engine is that the engine for the required power that flies is provided for aircraft, is the core component of aircraft interior
One of.Aero-engine includes engine crankcase, rotating disc, rotor blade and stator blade.Wherein, rotor blade and
Stator blade is arranged in engine crankcase, and rotor blade is that setting is on rotating disc, and along the central axis of rotating disc
Rotation axis is rotated, and stator blade is fixedly disposed in blade inner ring.
Fig. 1 shows the front schematic view of 1 one embodiments of blade of aviation engine, and Fig. 2 shows aero-engines
The diagrammatic cross-section of blade 1.The blade of aviation engine 1 can be the rotor blade in aero-engine, be also possible to stator
Blade.Blade of aviation engine 1 has blade inlet edge 7, trailing edge 9, blade tip 15, blade root 13 and aerofoil 3,
In, aerofoil 3 between blade inlet edge 7 and trailing edge 9 tangential 5, the exhibition vertical with tangential 5 to 11 extend, and even
Connect blade tip 15 and blade root 13.Aerofoil 3 its also along one it is tangential 17 extend, this tangential 17 perpendicular on the pressure side 19 with inhale
Between power side 21 tangential 5 with open up to 11, blade on the pressure side 19 constitutes the surface of blade with suction side 2, by blade inlet edge 7
It is connected together with the interconnection of trailing edge 9.
Wherein, blade of aviation engine 1 is made of a kind of magnetically susceptible material, and the rigidity of the magnetically susceptible material can be with
Outer material side apply magnetic field size variation and change.To when engine it is in running order in, aero-engine leaf
Piece 1 by extraneous load act on when, by change blade 1 rigidity, enable to blade 1 when the engine is working, by changing
Become the rigidity of itself to keep the shape of blade 1 all being consistent property under each working condition of engine, to reduce
Abrasion to engine.
Although one embodiment of this blade of aviation engine as described above, still this blade of aviation engine other
In embodiment, blade of aviation engine may have more details, and this relative to above-described embodiment in many aspects
At least part of a little details can have the variation of multiplicity.In being changed below with some embodiments to this details and a bit at least
A part is illustrated.
In an embodiment of blade of aviation engine 1, the magnetically susceptible material that aerofoil 3 is made is magnetic current
Become elastomer, is made of high molecular polymer and the magnetic-particle being dispersed in the high molecular polymer.This is magnetorheological
The rigidity of elastomer can change with applied field strengths, and its rigidity is positively correlated with 3 externally-applied magnetic field size of aerofoil, i.e.,
When the magnetic field strength for being added to aerofoil 3 increases, the rigidity of aerofoil 3 increases, when being added to aerofoil 3
Magnetic field strength reduce when, aerofoil 3 rigidity reduce.So set, making it possible to through control aerofoil 3
Externally-applied magnetic field size, to adjust its rigidity, to play the effect for adjusting the rigidity of blade 1.
Further, in one embodiment, which is titanium alloy substrate material, which is
Hydroxy iron powder.Wherein, titanium alloy substrate material has the characteristics that intensity is high, corrosion resistance is good, heat resistance is high, is suitable as blade
Substrate.Hydroxy iron powder is a kind of particle with high magnetic permeability, the high and low remanent magnetism of high magnetic saturation intensity.Its high magnetic permeability and
The characteristics of high magnetic saturation intensity, provides biggish attraction between particle, to there is stronger magnetic rheology effect；Its low remanent magnetism
Feature to will not continue to inhale together, to there is reversible magnetic rheology effect after magnetic field is eliminated.When in magnetic field these
Molecule can be converted to magnetic dipole, biggish attraction be generated between extremely son, due to the mangneto mechanical property of basis material
It can change because the total magnetic energy and magnetic energy density of these magnetic dipoles change, therefore by changing the additional magnetic of aerofoil 3
The magnetic field strength of field, can change the magnetic-Induced shear modulus of basis material, to change the rigidity of basis material.Work as externally-applied magnetic field
When increase, the attraction extremely between son increases, and the magnetic-Induced shear modulus of titanium alloy substrate material increases, so that aerofoil 3
Rigidity increase.When externally-applied magnetic field reduces, extremely the attraction between son reduces, the magnetic-Induced shear modulus of titanium alloy substrate material
Reduce, so that the rigidity of aerofoil 3 reduces.
Further, in one embodiment, the diameter of hydroxy iron powder is between 5 to 10 microns.
Fig. 3 shows the diagrammatic cross-section of one embodiment of aero-engine comprising blade 1, casing 30 and electricity
Magnetic induction equipment 31, electromagnetic induction device 31
Fig. 4 shows the schematic diagram that blade 1 and electromagnetic induction device 31 are distributed in Fig. 3, in conjunction with Fig. 3 and Fig. 4 it is found that electromagnetism
Sensing apparatus 31 is 13 inside 42 of outside 32 and blade root for being separately positioned on the blade tip 15 of blade 1.When blade 1 is rotor leaf
Setting on the casing 30 in 15 outside 32 of blade tip and on the rotating disc of 13 inside 42 of blade root is arranged in piece, electromagnetic induction device 31
Electromagnetic induction device 31 in 13 inside 42 of blade root is rotated with the rotation of rotating disc.When blade 1 is stator blade, electromagnetic induction
Equipment 31 is arranged on the casing 30 in 15 outside 32 of blade tip and in the blade inner ring of 13 inside 42 of blade root.
When being passed through electric current in electromagnetic induction device 31, meeting externally-applied magnetic field, the magnetic field on the aerofoil 3 of blade 1
Magnetic induction line distribution can be as shown in Figure 5.
Fig. 6 shows the diagrammatic cross-section of another embodiment of aero-engine, and Fig. 7 shows blade 1 and electromagnetism in Fig. 6
The schematic diagram that sensing apparatus 31 is distributed, in conjunction with Fig. 6 and Fig. 7 it is found that electromagnetic induction device 31 is the blade tip for being provided only on blade 1
On 15 outside 32, such setting can equally play the role of the externally-applied magnetic field on the aerofoil 3 of blade 1.
Fig. 8 shows the diagrammatic cross-section of another embodiment of aero-engine, and Fig. 9 shows blade 1 and electromagnetism in Fig. 8
The schematic diagram that sensing apparatus 31 is distributed, in conjunction with Fig. 8 and Fig. 9 it is found that electromagnetic induction device 31 is the blade root for being provided only on blade 1
On 13 insides 42, such setting can equally play the role of the externally-applied magnetic field on the aerofoil 3 of blade 1.Simultaneously as setting
It sets the electromagnetic induction device 31 in 13 inside 42 of blade root to rotate with the rotation of rotating disc, so that being applied on aerofoil 3
Externally-applied magnetic field size will not also change because changing with the distance between electromagnetic induction device 31, to further reduce
Difference under 1 actual working state of blade with design shape.
Figure 10 shows the schematic diagram of 31 1 embodiments of electromagnetic induction device, and electromagnetic induction device 31 includes iron core
311, electromagnetic coil 312, coil baffle 313, outer housing 314 and field current controller 315.Wherein, electromagnetic coil 312
It is arranged on iron core 311 around ground, and is limited between coil baffle 313 and iron core 311, prevents electromagnetic coil 312
It is scattered.Outer housing is made for accommodating iron core 311, electromagnetic coil 312 and coil baffle 313 of permeability magnetic material, to keep away
The interference to produced magnetic field is exempted from.Field current controller 315 passes through conducting wire with electromagnetic coil 312 to being connected to, and is used for electricity
Magnetic coil 312 exports electric current.Wherein, in part not shown in the figure, also there is speed detector, this turn in aero-engine
Speed detector detects the revolving speed of the blade, and output signal, can be a kind of photoelectric sensor.Field current controller
315 adjust the size that electric current is exported to electromagnetic coil 312 according to the output signal of speed detector.To pass through change
Size of current is exported, to play the adjustment effect for generating magnetic field size to electromagnetic coil 312.Wherein, field current controller 315
It inside can be with a kind of control chip, for receiving the output signal of speed detector, and adjust to electromagnetic coil 312
Export electric current, which can be including one or more hardware processors, such as microcontroller, microprocessor (such as
MCU chip or 51 single-chip microcontrollers), it is Reduced Instruction Set Computer (RISC), specific integrated circuit (ASIC), integrated using specific instruction
Processor (ASIP), central processing unit (CPU), graphics processing unit (GPU), physical processing unit (PPU), microcontroller list
Member, digital signal processor (DSP), field programmable gate array (FPGA), advanced risc machine (ARM), programmable logic device
(PLD), one of any circuit or processor of one or more functions etc. or a variety of combinations are able to carry out.
In one embodiment, the revolving speed of the output size of current of field current controller 315 and rotating disc is positively correlated,
Since when the increase of the rotation disk rotating speed of engine, the power of engine becomes larger at this time, and extraneous load suffered by blade 1 is big
Small also to increase, the output size of current of field current controller 315 also will increase at this time, so that electromagnetic coil 312 generates magnetic field
Size increases, the rigidity reinforced of blade 1.When the rotation disk rotating speed of engine reduces, the power of engine reduces at this time, blade
Extraneous load size suffered by 1 also reduces, and the output size of current of field current controller 315 can also reduce at this time, so that
Electromagnetic coil 312 generates magnetic field size and reduces, and the rigidity of blade 1 reduces.To pass through regulative mode as above, so that blade
1 rigidity can change with the difference of working condition, ensure that shape and design shape of the blade 1 under each working condition
Consistency.
Although the utility model is disclosed as above with preferred embodiment, its be not for limiting the utility model, it is any
Those skilled in the art without departing from the spirit and scope of the utility model, can make possible variation and modification.Cause
This, all contents without departing from technical solutions of the utility model, according to the technical essence of the utility model to above embodiments institute
Any modification, equivalent variations and the modification made, each fall within the protection scope that the utility model claims are defined.
Claims (10)
1. a kind of blade of aviation engine has blade inlet edge, trailing edge, blade tip, blade root and aerofoil, the sky
Aerodynamic force face between the blade inlet edge and trailing edge it is tangential, with the tangential vertical exhibition Xiang Yanshen, and connect institute
State blade tip and the blade root, it is characterised in that:
The aerofoil is made of magnetically susceptible material, the rigid size with externally-applied magnetic field of the magnetically susceptible material
Change and changes.
2. blade of aviation engine as described in claim 1, which is characterized in that the magnetically susceptible material is magnetorheological elasticity
Body, the magnetic rheology elastic body are made of high molecular polymer and the magnetic-particle being dispersed in the high molecular polymer；
Wherein, the rigidity of the magnetic rheology elastic body and the aerofoil externally-applied magnetic field size are positively correlated.
3. blade of aviation engine as claimed in claim 2, which is characterized in that the high molecular polymer is titanium alloy substrate
Material, the magnetic-particle are hydroxy iron powder.
4. blade of aviation engine as claimed in claim 3, which is characterized in that the diameter of the hydroxy iron powder is 5 to 10 micro-
Rice.
5. a kind of aero-engine, including engine crankcase, rotating disc and the rotor blade being arranged in the casing and
Stator blade, the rotor blade are rotated by rotation axis of the rotating disc central axis, which is characterized in that the rotor blade
It is respectively blade according to any one of claims 1 to 4 with stator blade；
Wherein, the aero-engine further includes electromagnetic induction device, and the electromagnetic induction device is for applying magnetic field in described
Aerofoil.
6. aero-engine as claimed in claim 5, which is characterized in that the electromagnetic induction device is separately positioned on the leaf
On the inside of sharp outside and/or the blade root.
7. aero-engine as claimed in claim 6, which is characterized in that the blade is rotor blade, the blade tip outside
For the casing, the blade root inside is the rotating disc.
8. aero-engine as claimed in claim 6, which is characterized in that the blade is stator blade, the blade tip outside
For the casing, the blade root inside is blade inner ring.
9. aero-engine as claimed in claim 5, which is characterized in that the electromagnetic induction device includes:
Iron core；
Electromagnetic coil is arranged around the iron core；
Coil baffle, the electromagnetic coil are limited between the coil baffle and the iron core；
Outer housing accommodates the iron core, the electromagnetic coil and the coil baffle, is made of permeability magnetic material；And
Field current controller, Xiang Suoshu electromagnetic coil export electric current；
Wherein, also there is speed detector, the speed detector detects turning for the blade in the aero-engine
Speed, and output signal, the field current controller control the output size of current according to the signal.
10. aero-engine as claimed in claim 9, which is characterized in that the output size of current and the rotating disc
Revolving speed is positively correlated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822030160.7U CN209398455U (en) | 2018-12-05 | 2018-12-05 | A kind of aero-engine and its blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822030160.7U CN209398455U (en) | 2018-12-05 | 2018-12-05 | A kind of aero-engine and its blade |
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| Publication Number | Publication Date |
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| CN209398455U true CN209398455U (en) | 2019-09-17 |
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ID=67881710
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| Application Number | Title | Priority Date | Filing Date |
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| CN201822030160.7U Active CN209398455U (en) | 2018-12-05 | 2018-12-05 | A kind of aero-engine and its blade |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111005768A (en) * | 2019-11-21 | 2020-04-14 | 中国航发沈阳黎明航空发动机有限责任公司 | Electromagnetic counterweight device for rotor of aircraft engine |
| EP3845739A1 (en) * | 2020-01-02 | 2021-07-07 | The Boeing Company | Balancing systems and methods for an engine of an aircraft |
-
2018
- 2018-12-05 CN CN201822030160.7U patent/CN209398455U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111005768A (en) * | 2019-11-21 | 2020-04-14 | 中国航发沈阳黎明航空发动机有限责任公司 | Electromagnetic counterweight device for rotor of aircraft engine |
| EP3845739A1 (en) * | 2020-01-02 | 2021-07-07 | The Boeing Company | Balancing systems and methods for an engine of an aircraft |
| US11261740B2 (en) | 2020-01-02 | 2022-03-01 | The Boeing Company | Balancing systems and methods for an engine of an aircraft |
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