CN110005640A - A kind of fan blade, compressor and aero-engine - Google Patents
A kind of fan blade, compressor and aero-engine Download PDFInfo
- Publication number
- CN110005640A CN110005640A CN201810007222.4A CN201810007222A CN110005640A CN 110005640 A CN110005640 A CN 110005640A CN 201810007222 A CN201810007222 A CN 201810007222A CN 110005640 A CN110005640 A CN 110005640A
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- China
- Prior art keywords
- blade
- bound edge
- fan blade
- compressor
- memorial alloy
- Prior art date
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/002—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by varying geometry within the pumps, e.g. by adjusting vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
Abstract
The present invention relates to a kind of fan blade, compressor and aero-engines, wherein fan blade includes blade body (1), the blade body (1) is made or is made using metal with nonmetallic mixed material using nonmetallic materials, the up-front outer surface of the blade body (1) is enclosed with memorial alloy bound edge (2), the memorial alloy bound edge (2) can deform, so that the up-front geometry inlet angle of the fan blade changes.Memorial alloy bound edge is being wrapped up using the leading edge outer surface of blade body made of nonmetallic materials or metal and nonmetallic mixing material in fan blade embodiment of the present invention, pass through the deformation of memorial alloy bound edge, it can change the up-front geometry inlet angle of fan blade, and then change angle of attack when air-flow enters blade grid passage, it is reduced as far as air-flow separation, aerodynamic loss is reduced, Capability of Compressor is improved.
Description
Technical field
The present invention relates to aero-engine technology field more particularly to a kind of fan blade, compressor and aero-engine.
Background technique
Setting clocking requirement compressor in modern aeroengine has the characteristics that high pressure ratio and efficient, the every level-one of compressor
It is all made of movable vane and stator blade, main function is so that air is obtained kinetic energy by high-speed rotating movable vane compressed air to do work
And pressure energy, compressed air, which enters in stator blade channel, further to convert pressure energy for kinetic energy obtained, and to close
Suitable angle flows into next stage movable vane, thus can finally obtain high pressure-charging by way of improving air pressure step by step
Than.However, increase of the raising of pressure ratio along with compressor blade airload, the loss of compressor also can be corresponding at the same time
Increase, if not being controlled to loss, the performance of compressor can be greatly reduced instead in this way, or even will cause it is extremely serious after
Fruit.
When compressor works under design conditions, air can enter at an appropriate angle to be completed to increase in each row's blade
Journey is pressed through, the angle of attack is smaller at this time, and from the point of view of angle of attack characteristic, pitot loss is also smaller.However, when compressor is in off-design point operating condition
When lower work, compressor flow reduces, and the angle of attack that air-flow enters blade grid passage just will increase, when the angle of attack increases to a certain extent
Afterwards, air-flow can separate at blade back, and loss substantially increases, and the performance of compressor is substantially reduced.
Blade Properties are mainly improved by the method optimized to compressor blade at present, reduce loss, such as
Chinese patent literature CN106021681A, publication date are on October 12nd, 2016, disclose a kind of Compressor airfoil optimization method
And device is superimposed upon again by changing compressor leading edge point to the blade profile thickness distribution function of leading edge and blade phase contact
On camber line, carry out from several scheme preferably, so as to improve the loss of incidence characteristic of blade profile.However this can only be to a certain degree
On, comparing original design slightly reduces loss caused by the angle of attack increases, not in the case where fundamentally solving the big angle of attack at blade back
The problem of air-flow separates.When the angle of attack further increases, corresponding pitot loss increases this trend faster and is not resolved.
It should be noted that the information for being disclosed in background of invention part is merely intended to increase to totality of the invention
The understanding of background, and be not construed as recognizing or imply in any form the information constitute by those skilled in the art public affairs
The prior art known.
Summary of the invention
The purpose of the present invention is to propose to a kind of fan blade, compressor and aero-engines, in the prior art to solve
The problem of fan blade increases in the off-design behaviour downstream angle of attack, and aerodynamic loss increases.
To achieve the above object, the present invention provides a kind of fan blade, including blade body, blade body uses non-gold
Belong to material to be made or be made using metal with nonmetallic mixed material, the up-front outer surface of blade body is enclosed with memory
Alloy bound edge, memorial alloy bound edge can deform, so that the up-front geometry inlet angle of fan blade changes.
Further, on blade profile surface, the length ratio that memorial alloy bound edge extends on up-front pressure face is in leading edge
Suction surface on the length that extends it is big.
Further, the thickness distribution of memorial alloy bound edge is configured to make to wrap up the fan after memorial alloy bound edge
The outer profile of blade meets pneumatic demand.
Further, memorial alloy bound edge extends to blade root along the blade tip of blade body.
To achieve the above object, the present invention also provides a kind of compressors, including above-mentioned fan blade.
Further, compressor further includes temperature-adjusting device, and temperature-adjusting device is used to adjust the blade of fan blade
The temperature of memorial alloy bound edge on ontology.
Further, the inside or outer surface of blade body is arranged in temperature-adjusting device.
To achieve the above object, the present invention also provides a kind of aero-engines, including above-mentioned compressor.
Further, aero-engine further includes the control opened or closed for controlling temperature-adjusting device in compressor
Switch.
Further, aero-engine further includes detection device, and detection device is for detecting fan blade in compressor
Up-front pressure or flow, detection device are connect with control switch signal, so that control switch can be examined according to detection device
The pressure signal or flow signal of survey open or close to control temperature-adjusting device.
Based on the above-mentioned technical proposal, in fan blade embodiment of the present invention using nonmetallic materials or metal with it is nonmetallic
The leading edge outer surface package memorial alloy bound edge of blade body made of mixing material can by the deformation of memorial alloy bound edge
To change the up-front geometry inlet angle of fan blade, and then change angle of attack when air-flow enters blade grid passage, is reduced as far as
Air-flow separation, reduces aerodynamic loss, improves Capability of Compressor.
Detailed description of the invention
The drawings described herein are used to provide a further understanding of the present invention, constitutes part of this application, this hair
Bright illustrative embodiments and their description are used to explain the present invention, and are not constituted improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is flow separation schematic diagram of the common blade under non-zero-incidence state in the prior art.
Fig. 2 is blade profile loss of incidence performance plot under common blade different Mach number in the prior art.
Fig. 3 is the structural schematic diagram of fan blade one embodiment of the present invention
Fig. 4 be fan blade one embodiment of the present invention before being deformed with deformed structural schematic diagram.
In figure:
1, blade body；2, memorial alloy bound edge.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, is clearly and completely retouched to the technical solution in embodiment
It states.Obviously, described embodiment is only a part of the embodiments of the present invention, instead of all the embodiments.Based on this hair
Bright embodiment, every other implementation obtained by those of ordinary skill in the art without making creative efforts
Example, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that, term " center ", " transverse direction ", " longitudinal direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "upper", "lower", "vertical", "horizontal", "top", "bottom", "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as pair
The limitation of the scope of the present invention.
To achieve the purpose of the present invention, the present invention proposes a kind of improved fan blade of structure.
As shown in figure 3, fan blade includes in a kind of illustrative examples of fan blade provided by the invention
Blade body 1, blade body 1 are made or are made using metal with nonmetallic mixed material, blade using nonmetallic materials
The up-front outer surface of ontology 1 is enclosed with memorial alloy bound edge 2, and memorial alloy bound edge 2 can deform, so that fan blade
Up-front geometry inlet angle change.
Wherein, geometry inlet angle refers to camber line in fan blade blade profile in the tangential and leaf grating front of leading edge apex
Angle, leaf grating front refer to connecting the straight line on all blade inlet edge vertex.The angle of attack be air-flow flow inlet angle and geometry inlet angle it
Between angle, air-flow flow inlet angle be air-flow direction of flow and leaf grating front angle.Therefore, after the change of air-flow direction of flow,
Leading edge geometry inlet angle changes correspondingly, thus it is possible to vary angle of attack size.
In above-mentioned illustrative examples, improving object is using nonmetallic materials or metal and nonmetallic mixing material system
At blade body 1, be enclosed with memorial alloy bound edge 2 in the leading edge outer surface of this blade body 1, pass through memorial alloy bound edge
2 deformation, thus it is possible to vary the up-front geometry inlet angle of fan blade, and then change angle of attack when air-flow enters blade grid passage, to the greatest extent
Air-flow separation is possibly reduced, aerodynamic loss is reduced, improves Capability of Compressor.
In addition, integrally being used for scheme made of memory alloy material relative to blade, using in leading edge appearance bread
The scheme for wrapping up in memorial alloy bound edge 2 has more advantages, for example may be implemented to improve control characteristic to up-front Partial controll；
Deformation for nonmetallic blade or metal and nonmetallic hybrid blade provides technical support, can also improve nonmetallic blade or gold
Belong to the intensity with nonmetallic hybrid blade；Be conducive to save material, reduce cost etc..
Wherein, memorial alloy bound edge 2 is made of marmem (SMA), and this memorial alloy has shape memory
Effect, the deformation occurred at a lower temperature (low-temperature phase) can be original before being restored to deformation by eliminating after heat temperature raising
Shape (high-temperature-phase).Optionally, using the memory alloy material with double-pass memory effect, high-temperature-phase can be restored when heated
Shape can be restored to low-temperature phase shape again while cooling, such memorial alloy bound edge 2 can between at least two shapes into
Row switching, to meet the needs of different directions of flow, makes no matter the leading edge angle of attack of fan blade can reach under which kind of operating condition
The angle of attack is smaller, the lesser purpose of aerodynamic loss, to promote the overall performance of compressor.
Further, on blade profile surface, the length ratio that memorial alloy bound edge 2 extends on up-front pressure face is in leading edge
Suction surface on the length that extends it is big.Setting can preferably protect the leading edge pressure face of fan blade in this way, enhance pressure face
Impact resistance.
Optionally, the thickness distribution of memorial alloy bound edge 2 is configured to make to wrap up the fan after memorial alloy bound edge 2
The outer profile of blade meets pneumatic demand.Setting can change fan leaf to avoid the package due to memorial alloy bound edge 2 in this way
The whole blade profile of piece avoids the increase of the aerodynamic loss brought by blade profile changes.
Optionally, memorial alloy bound edge 2 extends to blade root along the blade tip of blade body 1, i.e. memorial alloy bound edge 2 covers
The up-front overall deformation of fan blade may be implemented in the entire radical length of blade body 1, in this way setting, improves deformability,
It is more convenient to the adjusting of the angle of attack, accurate and reliable.
Based on the fan blade in above-mentioned each embodiment, the present invention also provides a kind of compressor, which includes
Above-mentioned fan blade.
Further, compressor further includes temperature-adjusting device, and temperature-adjusting device is used to adjust the blade of fan blade
The temperature of memorial alloy bound edge 2 on ontology 1.By the way that temperature-adjusting device is arranged, can temperature to memorial alloy bound edge 2 into
Row is adjusted in real time, to enable memorial alloy bound edge 2 that corresponding deformation occurs, reaches the mesh for reducing geometry inlet angle and the angle of attack
's.
Thermostatic specific constructive form with no restriction, as long as memorial alloy bound edge 2 can be carried out heating or
Cooling.
Optionally, the inside or outer surface of blade body 1 is arranged in temperature-adjusting device.Temperature-adjusting device setting exists
The inside of blade body 1 can prevent temperature-adjusting device from interfering with the other component outside blade body 1, be conducive to protect
Temperature-adjusting device；And for the forms temperature-adjusting device such as resistance wire, be it is easy to operate, also can be set in blade body 1
Outer surface.
Based on the compressor in above-mentioned each embodiment, the present invention also provides a kind of aero-engine, the aeroplane engines
Machine includes above-mentioned compressor.
Further, aero-engine further includes the control opened or closed for controlling temperature-adjusting device in compressor
Switch.By the way that control switch is arranged, thermostatic opening and closing is controlled with can be convenient.The specific knot of control switch
Configuration formula with no restriction, acts on as long as can be realized its.
Optionally, aero-engine further includes detection device, and detection device is for detecting in compressor before fan blade
The pressure or flow of edge, detection device are connect with control switch signal, so that control switch can be detected according to detection device
Pressure signal or flow signal opened or closed to control temperature-adjusting device.By the way that detection device is arranged, temperature can be given
The opening and closing control of regulating device provides judgment criteria and foundation, improves the accuracy of control.
The work of one embodiment of 1~3 pair of fan blade of the present invention, compressor and aero-engine with reference to the accompanying drawing
Process is illustrated:
As shown in Figure 1, under design conditions, generally zero-incidence state.As shown in Fig. 2, in lesser negative angle of attack and just
In range of angles of attack, blade profile pitot loss remains at low levels；However under big positive incidence state, air-flow can occur in blade back
Separation leads to increased dramatically for loss.When compressor flow reduces, the angle of attack be will increase, traditional by optimizing blade profile molded line
Although mode can reduce pitot loss to a certain extent, can not change it is this because the angle of attack increase lead to pitot loss phase
The trend that should be increased dramatically.
As shown in figure 3, the fan blade of compressor includes blade body 1, it is enclosed on the leading edge outer surface of blade body 1
Memorial alloy bound edge 2, range is lighted from leading edge, wraps up the leading edge portion of blade body 1.Specifically, memorial alloy bound edge 2 includes
Leading edge bound edge, pressure face bound edge and suction surface bound edge, leading edge bound edge are wrapped in the leading edge front end of blade body 1, pressure face bound edge
It is wrapped in the leading edge of blade body 1 on the pressure side, suction surface bound edge is wrapped in the leading edge suction side of blade body 1.Optionally, leading edge
Bound edge, pressure face bound edge and suction surface bound edge are integrally formed.The basic phase of original blade profile of the shape of leading edge bound edge and blade body 1
Together, the thickness of pressure face bound edge is gradually reduced along the direction from leading edge to trailing edge, and the thickness of suction surface bound edge is also along in the past
The direction of edge to trailing edge is gradually reduced, so that the blade profile of the fan blade after package memorial alloy bound edge 2 is still met pneumatically
Demand is reduced due to blade profile change and possible aerodynamic loss.
The inside of blade body 1 be equipped with temperature-adjusting device, it is thermostatic open or close by control switch into
Row control, detection device can detecte the up-front pressure of fan blade or flow, when leading edge pressure or flow reach preset value,
Trigger control switch, start-up temperature regulating device.
As shown in figure 4, up-front memorial alloy bound edge 2 keeps low-temperature phase before reaching preset value, it is A type leading edge, makes
Blade operates in the design dotted state that Low Angle Of Attack supports loss；When flow changes, and the angle of attack is caused to increase, the up-front pressure of blade profile
Power variation triggers control switch, and temperature-adjusting device starting can heat memorial alloy bound edge 2, and temperature increases, memory
Alloy bound edge 2 forms memorial alloy bound edge 2 ' after deforming, and becomes high-temperature-phase, is Type B leading edge, blade geometry flow inlet angle changes at this time
Become, reduces the incoming flow angle of attack.When flow and operating status are restored to design point operating condition, temperature-adjusting device can be stopped to note
Recall the heating of alloy bound edge 2, blade profile is restored to original shape.
Pass through the explanation of multiple embodiments to fan blade of the present invention, compressor and aero-engine, it can be seen that this
Invention fan blade, compressor and aero-engine embodiment are by setting memorial alloy bound edge, and in temperature change, memory is closed
The shape of golden bound edge can change, so that the up-front shape of blade profile be made to change, and then change the geometry of fan blade blade profile
Inlet angle reduces the angle of attack, can also have the loss of incidence characteristic similar with design conditions under off-design behaviour；Moreover,
When compressor flow is restored to design conditions flow, blade profile shape can also be restored.It thus can be in small flow work
Under condition and design conditions two states, by the change and recovery of blade inlet edge shape, air-flow is made to operate in low angle of attack damage always
It loses in characteristic range, the generation of flow separation at blade back is avoided, to guarantee the operation of compressor stability and high efficiency.
Finally it should be noted that: the above embodiments are merely illustrative of the technical scheme of the present invention and are not intended to be limiting thereof；To the greatest extent
The present invention is described in detail with reference to preferred embodiments for pipe, it should be understood by those ordinary skilled in the art that: still
It can modify to a specific embodiment of the invention or some technical features can be equivalently replaced；Without departing from this hair
The spirit of bright technical solution should all cover within the scope of the technical scheme claimed by the invention.
Claims (10)
1. a kind of fan blade, which is characterized in that including blade body (1), the blade body (1) uses nonmetallic materials system
It is made at or using metal with nonmetallic mixed material, the up-front outer surface of the blade body (1) is enclosed with memory
Alloy bound edge (2), the memorial alloy bound edge (2) can deform, so that the up-front geometry import of the fan blade
Angle changes.
2. fan blade according to claim 1, which is characterized in that on blade profile surface, the memorial alloy bound edge (2)
The length extended on the up-front pressure face is bigger than the length extended on the up-front suction surface.
3. fan blade according to claim 1, which is characterized in that the thickness distribution quilt of the memorial alloy bound edge (2)
The outer profile for being configured to make to wrap up the fan blade after the memorial alloy bound edge (2) meets pneumatic demand.
4. fan blade according to claim 1, which is characterized in that the memorial alloy bound edge (2) is along the blade sheet
The blade tip of body (1) extends to blade root.
5. a kind of compressor, which is characterized in that including the described in any item fan blade of such as Claims 1 to 4.
6. compressor according to claim 5, which is characterized in that the compressor further includes temperature-adjusting device, described
Temperature-adjusting device is used to adjust the temperature of the memorial alloy bound edge (2) in the blade body (1) of the fan blade.
7. compressor according to claim 6, which is characterized in that the temperature-adjusting device is arranged in the blade body
(1) inside or outer surface.
8. a kind of aero-engine, which is characterized in that including the described in any item compressors of such as claim 5~7.
9. aero-engine according to claim 8, which is characterized in that the aero-engine further includes for controlling
State the control switch that temperature-adjusting device in compressor opens or closes.
10. aero-engine according to claim 9, which is characterized in that the aero-engine further includes detection device,
The detection device is used to detect the up-front pressure or flow of fan blade in the compressor, the detection device with it is described
Control switch signal connection, so that the control switch can be believed according to detection device pressure signal detected or flow
It number is opened or closed to control the temperature-adjusting device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810007222.4A CN110005640B (en) | 2018-01-04 | 2018-01-04 | Fan blade, compressor and aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810007222.4A CN110005640B (en) | 2018-01-04 | 2018-01-04 | Fan blade, compressor and aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110005640A true CN110005640A (en) | 2019-07-12 |
| CN110005640B CN110005640B (en) | 2020-07-03 |
Family
ID=67164227
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810007222.4A Active CN110005640B (en) | 2018-01-04 | 2018-01-04 | Fan blade, compressor and aircraft engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN110005640B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112339217A (en) * | 2020-10-13 | 2021-02-09 | 武汉理工大学 | Variable-thickness blade metal edge covering forming and connecting integrated device and method |
| CN114961873A (en) * | 2021-02-25 | 2022-08-30 | 中国航发商用航空发动机有限责任公司 | Recoverable deformation blade and turbofan engine comprising same |
| CN116379001A (en) * | 2023-04-20 | 2023-07-04 | 沃杰(北京)科技有限公司 | High-performance turbine fan |
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| Publication number | Publication date |
|---|---|
| CN110005640B (en) | 2020-07-03 |
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